US20130087632A1 - Gas turbine engine exhaust ejector nozzle with de-swirl cascade - Google Patents
Gas turbine engine exhaust ejector nozzle with de-swirl cascade Download PDFInfo
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- US20130087632A1 US20130087632A1 US13/270,284 US201113270284A US2013087632A1 US 20130087632 A1 US20130087632 A1 US 20130087632A1 US 201113270284 A US201113270284 A US 201113270284A US 2013087632 A1 US2013087632 A1 US 2013087632A1
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- ejector nozzle
- fins
- exhaust
- ejector
- nozzle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the application relates generally to exhaust ejectors of gas turbine engines and, more particularly, to handling residual swirl in the turbine exhaust.
- Gas turbine exhaust ejectors typically consist of a high-velocity primary flow that leaves a primary component, referred to as a nozzle and transmits momentum to the surrounding medium by shear forces, thereby entraining the surrounding medium into a secondary flow.
- the primary and secondary flows then proceed into a secondary component having a larger diameter and referred to as a shroud.
- the nozzle is made integral to the engine, whereas the shroud is made integral to the aircraft.
- the entrainment of secondary flow with such ejectors is sensitive to residual swirl from the turbine exhaust.
- the residual swirl can be particularly high at operating conditions such as ground idle and rotor-locked (hotel mode) conditions, for instance. Beyond a certain threshold of swirl angle, the pumping process of the ejector can become unsatisfactory.
- Known methods to address this concern remained not completely satisfactory from the efficiency, cost and/or weight perspective. Accordingly, there remains room for improvement in addressing the ejector swirl.
- an exhaust ejector nozzle for a gas turbine engine, the exhaust ejector nozzle comprising a tubular wall having a radially inner surface delimiting an exhaust flow passage leading, along an exhaust flow direction, to an outlet plane of the exhaust ejector nozzle, the outlet plane being circumscribed by a downstream edge of the radially inner surface relative the exhaust flow direction, the radially inner surface of the tubular wall defining a central axis, the central axis and the radially inner surface being associated with an exhaust flow orientation; and a de-swirl cascade including a plurality of circumferentially interspaced fins each having a first end connected to the radially-inner surface of the tubular wall adjacent the downstream edge and associated outlet plane, a second end extending into the exhaust flow passage along a given span, and a chord oriented normal to the span.
- a gas turbine engine comprising an ejector having a nozzle and a cowl at an exhaust region, the nozzle extending from a turbine exhaust case of the gas turbine engine, the ejector nozzle having a tubular wall defining an exhaust flow passage leading to an outlet plane, and a de-swirl cascade including a plurality of circumferentially interspaced fins each having a first end connected to the wall adjacent the outlet plane and a second end extending into the exhaust flow passage.
- a method of de-swirling an external portion of an exhaust gas flow in an ejector nozzle of a gas turbine engine prior to mixing with a secondary flow in an ejector action including exposing at least the external portion of the exhaust flow inside the ejector nozzle to a de-swirl cascade including a plurality of circumferentially interspaced fins; the exhaust flow reaching an outlet plane of the ejector nozzle subsequently to said exposing.
- FIG. 1 is a schematic cross-sectional view of an example of a gas turbine engine
- FIG. 2 is an oblique schematic view showing an ejector nozzle connected to a turbine exhaust case
- FIG. 3 is an end view of the components of FIG. 2 .
- FIG. 4 is a side view of an alternate embodiment of an ejector nozzle.
- FIG. 1 illustrates an example of a turbine engine.
- the turbine engine 10 is a turboshaft engine generally comprising in serial flow communication, a multistage compressor 12 for pressurizing the air, a combustor 14 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 16 for extracting energy from the combustion gases.
- the turbine engine terminates in an exhaust section.
- the exhaust section includes an exhaust ejector 18 which is used to draw an external flow of air for ventilation, cooling, or the like.
- the exhaust ejector 18 in this embodiment generally includes a nozzle 22 and a shroud 27 .
- the nozzle 22 has a tubular wall 26 which guides a flow of exhaust gasses exiting the turbine section 16 .
- the exhaust gasses travelling through the nozzle 22 and subsequently exiting will be referred to in this specification as the primary flow 23 which travels in a direction generally indicated by the arrow.
- an inlet plane 44 of the nozzle 22 can be defined as being circumscribed by a first edge 46 of the tubular wall 26 , positioned upstream relative to the average flow direction of the primary flow 23 .
- An outlet plane 48 can be defined as being generally circumscribed by a second edge 50 of the tubular wall 26 , positioned downstream relative to an average flow direction of the primary flow 23 .
- the first edge 46 and second edge 50 can be circular, and can alternately be elliptical if the corresponding plane is slanted, for instance.
- the primary flow 23 can be annular around a center body 32 or circular, such as in alternate embodiments where the center body 32 is recessed for instance.
- the exact average orientation of respective portions of the primary flow 23 will be affected by the configuration of the tubular wall 26 , center body 32 as well as by other aerodynamic considerations known to those skilled in the art.
- the configuration of the exhaust flow path of the primary flow 23 through the nozzle 22 is affected by the shape of the radially-inner surface 31 of the tubular wall 26 .
- a central axis 29 can thus be defined relative the tubular wall 26 . Areas located nearer to the axis 29 can thus be referred to as being radially-inner, whereas areas located relatively farther to the axis are relatively radially-outer.
- tubular wall 26 can be said to have a radially-inner surface 31 ( FIG. 2 ) exposed to the primary flow 23 and an opposite radially-outer surface, a portion of which may be exposed to a radially-outer surrounding medium.
- the energy from the velocity of the primary flow 23 of exhaust gasses entrains a surrounding, radially-outer, secondary flow 25 of the surrounding medium by shear fluid friction forces into a secondary component of the exhaust ejector 18 referred to as the shroud 27 , which has a larger inlet plane 52 cross-sectional area than the cross-sectional area of the outlet plane 48 of the nozzle 22 to allow for entry of both the primary flow 23 and the secondary flow 25 .
- the inlet plane 52 of the shroud 27 can thus be said to radially exceed the inlet plane 48 of the nozzle 22 .
- FIGS. 2 and 3 show an example of an exhaust ejector nozzle 22 .
- the nozzle 22 is provided as an individual component shown connected to a turbine exhaust case 24 , but it will be understood that in an alternate embodiment, the nozzle 22 can be a portion or extension of the turbine case itself, for instance.
- the exhaust nozzle 22 can be seen to have a tubular wall 26 , being here generally cylindrical, and a radially-inner surface 31 of the tubular wall 26 defines an exhaust flow passage.
- the tubular wall 26 can be cambered, curved or bent to some extent depending on the intended use, in which case the central axis 29 follows the curve or camber; further, one end or both ends of the tubular wall 26 can be bent or slanted off the radial orientation, for instance.
- the nozzle inlet 28 which bears the upstream edge 46 of the tubular wall 26 , is connected to the turbine exhaust case 24 in this case.
- the tubular wall 26 also has an opposite outlet end 30 bearing the downstream edge 50 of the tubular wall 26 .
- the outlet end 30 is slanted, so the edge 50 of the tubular wall 26 is elliptical to some extent instead of being circular.
- An inlet plane 44 can be defined as the entry into the nozzle 22 whereas an outlet plane 48 can be defined as the exit, circumscribed by the downstream edge 50 .
- a centerbody 32 is shown connected to the turbine casing 24 by struts at the inlet plane 44 of the nozzle.
- centerbody 32 and struts are typical, the shape, position, and configuration thereof can vary in alternate embodiments. Typically, the struts and fins are independent of each other. However, in some cases, the designer may want to clock the fins such that no wake from the struts is aligned with any of the fins.
- Ejector pumping breakdown can result from high swirl angles in the shear layer between the primary and secondary flows.
- the breakdown is exacerbated by possible hub separation and migration of the flow towards the shroud 27 .
- the pumping breakdown is naturally to maintain conservation of angular momentum, with the separated flow near the hub substantially in a solid body rotation.
- a solution is to implement a partial cascade 34 before the nozzle exit plane 48 to reduce the swirl angle in the area where the pumping shear forces occur between the primary and secondary flows.
- the exhaust nozzle 22 further comprises a de-swirl cascade 34 including a plurality of circumferentially interspaced fins 36 each having a first end 38 connected to the wall 26 , and more particularly connected to the radially-inner surface 31 of the tubular wall 26 , and a second end 40 extending into the exhaust flow passage, in a direction which will be characterized here as being radially-inward from the radially inner surface 31 .
- the ducting is generally annular in shape and is positioned adjacent the outlet end 30 of the tubular wall 26 .
- the primary flow 23 exiting the nozzle 22 interacts with a surrounding medium to entrain a secondary flow into the shroud 27 .
- the inner peripheral portion 60 of the primary flow 23 (schematically shown here delimited on the one hand by an arbitrarily positioned dashed line and on the other hand by the inner surface 31 of the tubular wall 26 ) travelling inside the nozzle, i.e.
- the portion of the primary flow 23 which is adjacent the radially-inner surface 31 and in the inner periphery of the tubular wall 26 will have a significantly greater effect in the ejector pumping action onto the surrounding medium, once it has passed through the outlet plane 48 of the nozzle, than a more central, or radially-inner portion 42 of the primary flow 23 .
- the radially-inner portion 42 of the primary flow 23 which is located more radially inwardly is separated from the surrounding medium by the inner peripheral portion 60 layer of the primary flow 23 and interacts indirectly with the surrounding medium if at all. Addressing the swirl in a radially inner region is thus less likely to produce an effect on the ejector pumping action, just as partially addressing the swirl at an upstream position along the exhaust gas passage is less likely to be effective because subsequent mixing of the exhaust gasses may allow an unsatisfactory amount of swirl to return into the portions of the exhaust gas flow which contribute to the ejector action.
- annular critical region 62 of the exhaust flow passage in the nozzle is defined, being both adjacent the outlet plane 48 and adjacent the radially-inner surface 31 (as illustrated by numeral 60 in FIG. 3 ).
- Strategically controlling the swirl in this specific region inside the nozzle may be more susceptible to having a significant effect on the ejector pumping action than in regions located more radially inwardly or more upstream from the outlet plane, and thus may be achieved at satisfactory added weight, pressure, and costs.
- the fins 36 can extend only partially into the primary flow 23 in the direction extending across the flow, radially-inward from the tubular wall 26 , and can be positioned adjacent the outlet end 30 of the tubular wall 26 , i.e. adjacent the outlet plane 48 .
- This strategic positioning of the fins 36 connected to the tubular wall 26 of the nozzle 22 can strategically control the swirl in high swirl conditions to preserve the ejector pumping action with a limited amount of extra weight, pressure loss, and/or cost.
- the configuration of the de-swirl cascade 34 is designed to reduce the swirl in the exhaust gases strategically in order to maintain the ejector secondary flow pumping action even in conditions where there is a high degree of swirl in the exhaust gasses (such as a swirl angle of 40° or 50° for instance).
- the de-swirl cascade 34 and more specifically the fins thereof, is positioned near the critical region 62 of the ejector flow which eventually meets and shears with the secondary flow into the pumping action.
- the fins 36 in the direction of exhaust gas flow, have an upstream end 72 at a first longitudinal or axial position, and extend along their chord c ( FIG. 4 ) to a downstream end 74 .
- the downstream end of the fins 36 can be separated from the outlet plane 48 by a spacing distance d in this embodiment, but it will be understood that in alternate embodiments, the downstream end 74 of the fins can coincide with the downstream edge of the radially-inner surface 31 , i.e. the outlet plane 48 .
- the fins can be connected to the nozzle inner wall surface 31 and protrude past the outlet plane.
- the fins 36 can be designed to extend only partially into the primary flow 23 area, in the inner-peripheral region 60 , such as better seen in FIG. 3 , to favour the low-weight, low-pressure losses aspects.
- the span s of the fins 36 can represent only a fraction of the dimension of the primary flow area 42 . In this specific case, they can be seen to extend through around less than half of the primary flow area 42 which can be delimited between the center body 32 and the radially-inner surface 31 for instance.
- the fins 36 can extend across the entire primary flow area 42 and/or optionally be interconnected by a structural ring or centerbody, for instance.
- an aim was to sufficiently control the swirl to maintain the ejector pumping action in high-swirl conditions, while optimizing weight and pressure losses added by the fins 36 .
- the span I and chord c can be adjusted to minimum or optimum dimensions, and the fin count can also be adjusted to a minimum or optimum value yielding results considered as satisfactory.
- the stagger angle can be close to zero, but can alternately be adjusted to maintain low pressure losses.
- the fins 36 can be seen to extend more or less normal from the wall 26 , radially inward, and have their chord parallel to the central axis 29 , or alternately inclined therefrom by a stagger angle.
- the fins can be provided closer to nozzle inlet instead of being adjacent the nozzle outlet, and the span, chord, fin count and stagger angle can vary.
- the de-swirl cascade can be applied to exhaust ejector nozzles of any suitable turbine, such as turboshafts, turboprops and APUs for instance. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the scope of the appended claims.
Abstract
The exhaust ejector nozzle has a tubular wall defining an exhaust flow passage leading to an outlet plane, and a de-swirl cascade including a plurality of circumferentially interspaced fins each having a first end connected to the wall adjacent the outlet plane and a second end extending into the exhaust flow passage. The de-swirl cascade can maintain the pumping action of the ejector in high swirl exhaust conditions.
Description
- The application relates generally to exhaust ejectors of gas turbine engines and, more particularly, to handling residual swirl in the turbine exhaust.
- Gas turbine exhaust ejectors typically consist of a high-velocity primary flow that leaves a primary component, referred to as a nozzle and transmits momentum to the surrounding medium by shear forces, thereby entraining the surrounding medium into a secondary flow. The primary and secondary flows then proceed into a secondary component having a larger diameter and referred to as a shroud. Typically, the nozzle is made integral to the engine, whereas the shroud is made integral to the aircraft.
- The entrainment of secondary flow with such ejectors is sensitive to residual swirl from the turbine exhaust. The residual swirl can be particularly high at operating conditions such as ground idle and rotor-locked (hotel mode) conditions, for instance. Beyond a certain threshold of swirl angle, the pumping process of the ejector can become unsatisfactory. Known methods to address this concern remained not completely satisfactory from the efficiency, cost and/or weight perspective. Accordingly, there remains room for improvement in addressing the ejector swirl.
- In one aspect, there is provided an exhaust ejector nozzle for a gas turbine engine, the exhaust ejector nozzle comprising a tubular wall having a radially inner surface delimiting an exhaust flow passage leading, along an exhaust flow direction, to an outlet plane of the exhaust ejector nozzle, the outlet plane being circumscribed by a downstream edge of the radially inner surface relative the exhaust flow direction, the radially inner surface of the tubular wall defining a central axis, the central axis and the radially inner surface being associated with an exhaust flow orientation; and a de-swirl cascade including a plurality of circumferentially interspaced fins each having a first end connected to the radially-inner surface of the tubular wall adjacent the downstream edge and associated outlet plane, a second end extending into the exhaust flow passage along a given span, and a chord oriented normal to the span.
- In a second aspect, there is provided a gas turbine engine comprising an ejector having a nozzle and a cowl at an exhaust region, the nozzle extending from a turbine exhaust case of the gas turbine engine, the ejector nozzle having a tubular wall defining an exhaust flow passage leading to an outlet plane, and a de-swirl cascade including a plurality of circumferentially interspaced fins each having a first end connected to the wall adjacent the outlet plane and a second end extending into the exhaust flow passage.
- In a third aspect, there is provided a method of de-swirling an external portion of an exhaust gas flow in an ejector nozzle of a gas turbine engine prior to mixing with a secondary flow in an ejector action, the method including exposing at least the external portion of the exhaust flow inside the ejector nozzle to a de-swirl cascade including a plurality of circumferentially interspaced fins; the exhaust flow reaching an outlet plane of the ejector nozzle subsequently to said exposing.
- Further details of these and other aspects of the present invention will be apparent from the detailed description and figures included below.
- Reference is now made to the accompanying figures, in which:
-
FIG. 1 is a schematic cross-sectional view of an example of a gas turbine engine; -
FIG. 2 is an oblique schematic view showing an ejector nozzle connected to a turbine exhaust case; -
FIG. 3 is an end view of the components ofFIG. 2 . -
FIG. 4 is a side view of an alternate embodiment of an ejector nozzle. -
FIG. 1 illustrates an example of a turbine engine. In this example, theturbine engine 10 is a turboshaft engine generally comprising in serial flow communication, amultistage compressor 12 for pressurizing the air, acombustor 14 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and aturbine section 16 for extracting energy from the combustion gases. The turbine engine terminates in an exhaust section. - In this example, the exhaust section includes an
exhaust ejector 18 which is used to draw an external flow of air for ventilation, cooling, or the like. Theexhaust ejector 18 in this embodiment generally includes anozzle 22 and ashroud 27. Thenozzle 22 has atubular wall 26 which guides a flow of exhaust gasses exiting theturbine section 16. The exhaust gasses travelling through thenozzle 22 and subsequently exiting will be referred to in this specification as theprimary flow 23 which travels in a direction generally indicated by the arrow. Henceforth, aninlet plane 44 of thenozzle 22 can be defined as being circumscribed by afirst edge 46 of thetubular wall 26, positioned upstream relative to the average flow direction of theprimary flow 23. Anoutlet plane 48 can be defined as being generally circumscribed by asecond edge 50 of thetubular wall 26, positioned downstream relative to an average flow direction of theprimary flow 23. Thefirst edge 46 andsecond edge 50 can be circular, and can alternately be elliptical if the corresponding plane is slanted, for instance. - The
primary flow 23 can be annular around acenter body 32 or circular, such as in alternate embodiments where thecenter body 32 is recessed for instance. The exact average orientation of respective portions of theprimary flow 23 will be affected by the configuration of thetubular wall 26,center body 32 as well as by other aerodynamic considerations known to those skilled in the art. The configuration of the exhaust flow path of theprimary flow 23 through thenozzle 22 is affected by the shape of the radially-inner surface 31 of thetubular wall 26. Acentral axis 29 can thus be defined relative thetubular wall 26. Areas located nearer to theaxis 29 can thus be referred to as being radially-inner, whereas areas located relatively farther to the axis are relatively radially-outer. Accordingly, thetubular wall 26 can be said to have a radially-inner surface 31 (FIG. 2 ) exposed to theprimary flow 23 and an opposite radially-outer surface, a portion of which may be exposed to a radially-outer surrounding medium. - During normal operation of the
ejector 18, the energy from the velocity of theprimary flow 23 of exhaust gasses entrains a surrounding, radially-outer,secondary flow 25 of the surrounding medium by shear fluid friction forces into a secondary component of theexhaust ejector 18 referred to as theshroud 27, which has alarger inlet plane 52 cross-sectional area than the cross-sectional area of theoutlet plane 48 of thenozzle 22 to allow for entry of both theprimary flow 23 and thesecondary flow 25. Theinlet plane 52 of theshroud 27 can thus be said to radially exceed theinlet plane 48 of thenozzle 22. -
FIGS. 2 and 3 show an example of anexhaust ejector nozzle 22. In this embodiment, thenozzle 22 is provided as an individual component shown connected to aturbine exhaust case 24, but it will be understood that in an alternate embodiment, thenozzle 22 can be a portion or extension of the turbine case itself, for instance. Further, referring to the illustrated embodiment, theexhaust nozzle 22 can be seen to have atubular wall 26, being here generally cylindrical, and a radially-inner surface 31 of thetubular wall 26 defines an exhaust flow passage. Thetubular wall 26 can be cambered, curved or bent to some extent depending on the intended use, in which case thecentral axis 29 follows the curve or camber; further, one end or both ends of thetubular wall 26 can be bent or slanted off the radial orientation, for instance. - The
nozzle inlet 28, which bears theupstream edge 46 of thetubular wall 26, is connected to theturbine exhaust case 24 in this case. Thetubular wall 26 also has anopposite outlet end 30 bearing thedownstream edge 50 of thetubular wall 26. In this embodiment, theoutlet end 30 is slanted, so theedge 50 of thetubular wall 26 is elliptical to some extent instead of being circular. Aninlet plane 44 can be defined as the entry into thenozzle 22 whereas anoutlet plane 48 can be defined as the exit, circumscribed by thedownstream edge 50. In this embodiment, acenterbody 32 is shown connected to theturbine casing 24 by struts at theinlet plane 44 of the nozzle. Although the presence of thecenterbody 32 and struts are typical, the shape, position, and configuration thereof can vary in alternate embodiments. Typically, the struts and fins are independent of each other. However, in some cases, the designer may want to clock the fins such that no wake from the struts is aligned with any of the fins. - Ejector pumping breakdown can result from high swirl angles in the shear layer between the primary and secondary flows. The breakdown is exacerbated by possible hub separation and migration of the flow towards the
shroud 27. The pumping breakdown is naturally to maintain conservation of angular momentum, with the separated flow near the hub substantially in a solid body rotation. A solution is to implement apartial cascade 34 before thenozzle exit plane 48 to reduce the swirl angle in the area where the pumping shear forces occur between the primary and secondary flows. - To this end, in this embodiment, the
exhaust nozzle 22 further comprises ade-swirl cascade 34 including a plurality of circumferentially interspaced fins 36 each having afirst end 38 connected to thewall 26, and more particularly connected to the radially-inner surface 31 of thetubular wall 26, and asecond end 40 extending into the exhaust flow passage, in a direction which will be characterized here as being radially-inward from the radiallyinner surface 31. It will be noted here that the ducting is generally annular in shape and is positioned adjacent theoutlet end 30 of thetubular wall 26. - To provide the ejector function, the
primary flow 23 exiting thenozzle 22 interacts with a surrounding medium to entrain a secondary flow into theshroud 27. Referring toFIG. 3 , the innerperipheral portion 60 of the primary flow 23 (schematically shown here delimited on the one hand by an arbitrarily positioned dashed line and on the other hand by theinner surface 31 of the tubular wall 26) travelling inside the nozzle, i.e. the portion of theprimary flow 23 which is adjacent the radially-inner surface 31 and in the inner periphery of thetubular wall 26, will have a significantly greater effect in the ejector pumping action onto the surrounding medium, once it has passed through theoutlet plane 48 of the nozzle, than a more central, or radially-inner portion 42 of theprimary flow 23. This is because although a certain amount of mixing can occur, at least a high percentage of the innerperipheral portion 60 of theprimary flow 23 which travels close to the radiallyinner surface 31 of thetubular wall 26 near theoutlet plane 48 will remain in a radial position allowing it to interact with the surrounding medium, which is located radially-outwardly. The radially-inner portion 42 of theprimary flow 23 which is located more radially inwardly is separated from the surrounding medium by the innerperipheral portion 60 layer of theprimary flow 23 and interacts indirectly with the surrounding medium if at all. Addressing the swirl in a radially inner region is thus less likely to produce an effect on the ejector pumping action, just as partially addressing the swirl at an upstream position along the exhaust gas passage is less likely to be effective because subsequent mixing of the exhaust gasses may allow an unsatisfactory amount of swirl to return into the portions of the exhaust gas flow which contribute to the ejector action. - Referring more particularly to
FIG. 4 , an annularcritical region 62 of the exhaust flow passage in the nozzle is defined, being both adjacent theoutlet plane 48 and adjacent the radially-inner surface 31 (as illustrated bynumeral 60 inFIG. 3 ). Strategically controlling the swirl in this specific region inside the nozzle may be more susceptible to having a significant effect on the ejector pumping action than in regions located more radially inwardly or more upstream from the outlet plane, and thus may be achieved at satisfactory added weight, pressure, and costs. - Even if high swirl is present across the entire cross-section of the exhaust gasses of the primary flow inside the nozzle, it can be satisfactory to control the swirl only partially, and strategically in the inner
peripheral portion 60 of theprimary flow 23 and in theannular region 62 near theoutlet plane 48. Rreferring back toFIG. 3 , thefins 36 can extend only partially into theprimary flow 23 in the direction extending across the flow, radially-inward from thetubular wall 26, and can be positioned adjacent the outlet end 30 of thetubular wall 26, i.e. adjacent theoutlet plane 48. This strategic positioning of thefins 36 connected to thetubular wall 26 of thenozzle 22 can strategically control the swirl in high swirl conditions to preserve the ejector pumping action with a limited amount of extra weight, pressure loss, and/or cost. - In the illustrated embodiment, the configuration of the
de-swirl cascade 34 is designed to reduce the swirl in the exhaust gases strategically in order to maintain the ejector secondary flow pumping action even in conditions where there is a high degree of swirl in the exhaust gasses (such as a swirl angle of 40° or 50° for instance). Thede-swirl cascade 34, and more specifically the fins thereof, is positioned near thecritical region 62 of the ejector flow which eventually meets and shears with the secondary flow into the pumping action. - In the illustrated embodiment, and referring to
FIG. 4 , in the direction of exhaust gas flow, thefins 36 have anupstream end 72 at a first longitudinal or axial position, and extend along their chord c (FIG. 4 ) to adownstream end 74. For practical purposes, the downstream end of thefins 36 can be separated from theoutlet plane 48 by a spacing distance d in this embodiment, but it will be understood that in alternate embodiments, thedownstream end 74 of the fins can coincide with the downstream edge of the radially-inner surface 31, i.e. theoutlet plane 48. If the distance d is too long, the deswirl action through the fins will be partially lost as the high swirl near the center will migrate radially outwards, thereby favouring the breakdown of ejector pumping. In an alternate embodiment, the fins can be connected to the nozzleinner wall surface 31 and protrude past the outlet plane. - Because the region of the
primary flow 23 which is responsible for the pumping action of thesecondary flow 25 is more importantly theregion 60 thereof which is located adjacent to the wall, thefins 36 can be designed to extend only partially into theprimary flow 23 area, in the inner-peripheral region 60, such as better seen inFIG. 3 , to favour the low-weight, low-pressure losses aspects. The span s of thefins 36 can represent only a fraction of the dimension of theprimary flow area 42. In this specific case, they can be seen to extend through around less than half of theprimary flow area 42 which can be delimited between thecenter body 32 and the radially-inner surface 31 for instance. In alternate embodiments, thefins 36 can extend across the entireprimary flow area 42 and/or optionally be interconnected by a structural ring or centerbody, for instance. - In the illustrated embodiment, an aim was to sufficiently control the swirl to maintain the ejector pumping action in high-swirl conditions, while optimizing weight and pressure losses added by the
fins 36. To this end, the span I and chord c can be adjusted to minimum or optimum dimensions, and the fin count can also be adjusted to a minimum or optimum value yielding results considered as satisfactory. The stagger angle can be close to zero, but can alternately be adjusted to maintain low pressure losses. Thefins 36 can be seen to extend more or less normal from thewall 26, radially inward, and have their chord parallel to thecentral axis 29, or alternately inclined therefrom by a stagger angle. The final adjustment of these design parameters will be typically be selected to achieve a trade-off between the ejector ability to function at both high swirl and aero design conditions (SFC), in which the swirl is typically low. Other design aspects are to be considered such as structural integrity and manufacturability. - The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departing from the scope of the invention disclosed. For example, the fins can be provided closer to nozzle inlet instead of being adjacent the nozzle outlet, and the span, chord, fin count and stagger angle can vary. The de-swirl cascade can be applied to exhaust ejector nozzles of any suitable turbine, such as turboshafts, turboprops and APUs for instance. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the scope of the appended claims.
Claims (20)
1. An exhaust ejector nozzle for a gas turbine engine, the exhaust ejector nozzle comprising a tubular wall having a radially inner surface delimiting an exhaust flow passage leading, along an exhaust flow direction, to an outlet plane of the exhaust ejector nozzle, the outlet plane being circumscribed by a downstream edge of the radially inner surface relative the exhaust flow direction, the radially inner surface of the tubular wall defining a central axis, the central axis and the radially inner surface being associated with an exhaust flow orientation; and a de-swirl cascade including a plurality of circumferentially interspaced fins each having a first end connected to the radially-inner surface of the tubular wall adjacent the downstream edge and associated outlet plane, a second end extending into the exhaust flow passage along a given span, and a chord oriented normal to the span.
2. The ejector nozzle of claim 1 wherein the span of the fins extends only partially into the exhaust flow passage.
3. The ejector nozzle of claim 2 wherein the span extends less than halfway into the primary flow area.
4. The ejector nozzle of claim 2 wherein the span extends along an inner peripheral region of the exhaust flow passage.
5. The ejector nozzle of claim 1 wherein the chord is inclined by a stagger angle relative to the central axis.
6. The ejector nozzle of claim 1 wherein the span, the chord, the stagger angle, and an interspacing between the fins are selected to sustain a pumping action of the ejector in high swirl conditions.
7. The ejector nozzle of claim 1 wherein the fins extend normal to the radially-inner surface.
8. The ejector nozzle of claim 1 wherein the second end of the fins is a free end.
9. The ejector nozzle of claim 1 wherein the fins are immediately adjacent the outlet plane.
10. The ejector nozzle of claim 1 wherein the fins are spaced from the downstream edge by a spacing distance which is small relative to the span and the chord.
11. The ejector nozzle of claim 1 wherein the span and the chord are of the same order of magnitude.
12. The ejector nozzle of claim 1 wherein the tubular wall is cambered and the central axis is correspondingly curved.
13. A gas turbine engine comprising an ejector having a nozzle and a cowl at an exhaust region, the nozzle extending from a turbine exhaust case of the gas turbine engine, the ejector nozzle having a tubular wall defining an exhaust flow passage leading to an outlet plane, and a de-swirl cascade including a plurality of circumferentially interspaced fins each having a first end connected to the wall adjacent the outlet plane and a second end extending into the exhaust flow passage.
14. The ejector nozzle of claim 13 wherein the fins extend partially into a primary flow area of the exhaust flow passage.
15. The ejector nozzle of claim 14 wherein the fins extend less than halfway into the primary flow area.
16. The ejector nozzle of claim 13 wherein the fins are oriented in an axial orientation relative the tubular wall.
17. The ejector nozzle of claim 13 wherein the free end of the fins extends normal to the wall.
18. The ejector nozzle of claim 13 wherein the fins are immediately adjacent the outlet plane.
19. The ejector nozzle of claim 13 wherein the fins have a span, chord, stagger angle, and interspacing selected to sustain a pumping action of the ejector in high swirl conditions.
20. A method of de-swirling an external portion of an exhaust gas flow in an ejector nozzle of a gas turbine engine prior to mixing with a secondary flow in an ejector action, the method including
exposing at least the external portion of the exhaust flow inside the ejector nozzle to a de-swirl cascade including a plurality of circumferentially interspaced fins;
the exhaust flow reaching an outlet plane of the ejector nozzle subsequently to said exposing.
Priority Applications (1)
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US13/270,284 US20130087632A1 (en) | 2011-10-11 | 2011-10-11 | Gas turbine engine exhaust ejector nozzle with de-swirl cascade |
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Application Number | Priority Date | Filing Date | Title |
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US13/270,284 US20130087632A1 (en) | 2011-10-11 | 2011-10-11 | Gas turbine engine exhaust ejector nozzle with de-swirl cascade |
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US20130087632A1 true US20130087632A1 (en) | 2013-04-11 |
Family
ID=48041447
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US13/270,284 Abandoned US20130087632A1 (en) | 2011-10-11 | 2011-10-11 | Gas turbine engine exhaust ejector nozzle with de-swirl cascade |
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170030213A1 (en) * | 2015-07-31 | 2017-02-02 | Pratt & Whitney Canada Corp. | Turbine section with tip flow vanes |
US10207812B2 (en) | 2015-09-02 | 2019-02-19 | Jetoptera, Inc. | Fluidic propulsive system and thrust and lift generator for aerial vehicles |
US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
USD868627S1 (en) | 2018-04-27 | 2019-12-03 | Jetoptera, Inc. | Flying car |
US10612421B2 (en) | 2015-03-04 | 2020-04-07 | Sikorsky Aircraft Corporation | Gas turbine exhaust assembly |
US10730636B2 (en) * | 2016-07-18 | 2020-08-04 | Rolls-Royce North American Technologies Inc. | Integrated aircraft cooling system |
Citations (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1493753A (en) * | 1923-10-25 | 1924-05-13 | Boris T Koleroff | Propulsion device |
US2648192A (en) * | 1949-09-27 | 1953-08-11 | United Aircraft Corp | Variable capacity jet exhaust augmenter |
US2940252A (en) * | 1956-02-07 | 1960-06-14 | Boeing Co | Gas stream thrust reaction propulsion engines with noise-suppression and thrust-reversing nozzle means |
US3161257A (en) * | 1959-05-01 | 1964-12-15 | Young Alec David | Jet pipe nozzle silencers |
GB1045295A (en) * | 1964-03-25 | 1966-10-12 | Peter Bradshaw | Improvements in or relating to a jet noise suppression device |
US3613996A (en) * | 1969-07-03 | 1971-10-19 | Rohr Corp | Ejector with suppressor chutes |
US3667680A (en) * | 1970-04-24 | 1972-06-06 | Boeing Co | Jet engine exhaust nozzle system |
US3910375A (en) * | 1973-08-21 | 1975-10-07 | Bertin & Cie | Jet engine silencer |
US3982696A (en) * | 1975-07-01 | 1976-09-28 | Grumman American Aviation Corporation | Jet noise suppressor nozzle |
US4175640A (en) * | 1975-03-31 | 1979-11-27 | Boeing Commercial Airplane Company | Vortex generators for internal mixing in a turbofan engine |
US4215536A (en) * | 1978-12-26 | 1980-08-05 | The Boeing Company | Gas turbine mixer apparatus |
US4298089A (en) * | 1976-12-23 | 1981-11-03 | The Boeing Company | Vortex generators for internal mixing in a turbofan engine |
EP0119732A1 (en) * | 1983-02-15 | 1984-09-26 | The Commonwealth Of Australia | Thrust augmentor |
US5462088A (en) * | 1992-10-26 | 1995-10-31 | Societe Anonyme Dite: European Gas Turbines Sa | Gas turbine exhaust diffuser |
US5463866A (en) * | 1993-12-30 | 1995-11-07 | The Boeing Company | Supersonic jet engine installation and method with sound suppressing nozzle |
US20030154720A1 (en) * | 2002-02-20 | 2003-08-21 | John Boehnlein | Ejector based engines |
US6662548B1 (en) * | 2000-09-27 | 2003-12-16 | The Boeing Company | Jet blade ejector nozzle |
US20040025513A1 (en) * | 2002-05-16 | 2004-02-12 | Walsh Philip P. | Gas turbine engine |
US6988674B2 (en) * | 2004-06-08 | 2006-01-24 | General Electric Company | Method and apparatus for suppressing infrared signatures |
US20070089396A1 (en) * | 2005-10-25 | 2007-04-26 | Honeywell International, Inc. | Eductor swirl buster |
US20070119985A1 (en) * | 2005-10-19 | 2007-05-31 | Gm Global Technology Operations, Inc. | Fluid Entrainment Apparatus |
US20090309364A1 (en) * | 2006-06-27 | 2009-12-17 | Turbomeca | Power generation system for an aircraft using a fuel cell |
US8087250B2 (en) * | 2008-06-26 | 2012-01-03 | General Electric Company | Duplex tab exhaust nozzle |
US8146342B2 (en) * | 2006-10-31 | 2012-04-03 | Honeywell International Inc. | Exhaust eductor system with a recirculation baffle |
EP2497934A1 (en) * | 2011-03-07 | 2012-09-12 | EADS Construcciones Aeronauticas, S.A. | Flow evacuation system for an aircraft engine |
-
2011
- 2011-10-11 US US13/270,284 patent/US20130087632A1/en not_active Abandoned
Patent Citations (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1493753A (en) * | 1923-10-25 | 1924-05-13 | Boris T Koleroff | Propulsion device |
US2648192A (en) * | 1949-09-27 | 1953-08-11 | United Aircraft Corp | Variable capacity jet exhaust augmenter |
US2940252A (en) * | 1956-02-07 | 1960-06-14 | Boeing Co | Gas stream thrust reaction propulsion engines with noise-suppression and thrust-reversing nozzle means |
US3161257A (en) * | 1959-05-01 | 1964-12-15 | Young Alec David | Jet pipe nozzle silencers |
GB1045295A (en) * | 1964-03-25 | 1966-10-12 | Peter Bradshaw | Improvements in or relating to a jet noise suppression device |
US3613996A (en) * | 1969-07-03 | 1971-10-19 | Rohr Corp | Ejector with suppressor chutes |
US3667680A (en) * | 1970-04-24 | 1972-06-06 | Boeing Co | Jet engine exhaust nozzle system |
US3910375A (en) * | 1973-08-21 | 1975-10-07 | Bertin & Cie | Jet engine silencer |
US4175640A (en) * | 1975-03-31 | 1979-11-27 | Boeing Commercial Airplane Company | Vortex generators for internal mixing in a turbofan engine |
US3982696A (en) * | 1975-07-01 | 1976-09-28 | Grumman American Aviation Corporation | Jet noise suppressor nozzle |
US4298089A (en) * | 1976-12-23 | 1981-11-03 | The Boeing Company | Vortex generators for internal mixing in a turbofan engine |
US4215536A (en) * | 1978-12-26 | 1980-08-05 | The Boeing Company | Gas turbine mixer apparatus |
EP0119732A1 (en) * | 1983-02-15 | 1984-09-26 | The Commonwealth Of Australia | Thrust augmentor |
US5462088A (en) * | 1992-10-26 | 1995-10-31 | Societe Anonyme Dite: European Gas Turbines Sa | Gas turbine exhaust diffuser |
US5463866A (en) * | 1993-12-30 | 1995-11-07 | The Boeing Company | Supersonic jet engine installation and method with sound suppressing nozzle |
US6662548B1 (en) * | 2000-09-27 | 2003-12-16 | The Boeing Company | Jet blade ejector nozzle |
US20030154720A1 (en) * | 2002-02-20 | 2003-08-21 | John Boehnlein | Ejector based engines |
US20040025513A1 (en) * | 2002-05-16 | 2004-02-12 | Walsh Philip P. | Gas turbine engine |
US6988674B2 (en) * | 2004-06-08 | 2006-01-24 | General Electric Company | Method and apparatus for suppressing infrared signatures |
US20070119985A1 (en) * | 2005-10-19 | 2007-05-31 | Gm Global Technology Operations, Inc. | Fluid Entrainment Apparatus |
US20070089396A1 (en) * | 2005-10-25 | 2007-04-26 | Honeywell International, Inc. | Eductor swirl buster |
US20090309364A1 (en) * | 2006-06-27 | 2009-12-17 | Turbomeca | Power generation system for an aircraft using a fuel cell |
US8146342B2 (en) * | 2006-10-31 | 2012-04-03 | Honeywell International Inc. | Exhaust eductor system with a recirculation baffle |
US8087250B2 (en) * | 2008-06-26 | 2012-01-03 | General Electric Company | Duplex tab exhaust nozzle |
EP2497934A1 (en) * | 2011-03-07 | 2012-09-12 | EADS Construcciones Aeronauticas, S.A. | Flow evacuation system for an aircraft engine |
US20120279225A1 (en) * | 2011-03-07 | 2012-11-08 | Eads Construcciones Aeronauticas, S.A. | Flow evacuation system for an aircraft engine |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10612421B2 (en) | 2015-03-04 | 2020-04-07 | Sikorsky Aircraft Corporation | Gas turbine exhaust assembly |
US20170030213A1 (en) * | 2015-07-31 | 2017-02-02 | Pratt & Whitney Canada Corp. | Turbine section with tip flow vanes |
US10207812B2 (en) | 2015-09-02 | 2019-02-19 | Jetoptera, Inc. | Fluidic propulsive system and thrust and lift generator for aerial vehicles |
US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
US10800538B2 (en) | 2015-09-02 | 2020-10-13 | Jetoptera, Inc. | Ejector and airfoil configurations |
US10730636B2 (en) * | 2016-07-18 | 2020-08-04 | Rolls-Royce North American Technologies Inc. | Integrated aircraft cooling system |
USD868627S1 (en) | 2018-04-27 | 2019-12-03 | Jetoptera, Inc. | Flying car |
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