US20150059312A1 - Exhaust stack having a co-axial silencer - Google Patents

Exhaust stack having a co-axial silencer Download PDF

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Publication number
US20150059312A1
US20150059312A1 US14/013,525 US201314013525A US2015059312A1 US 20150059312 A1 US20150059312 A1 US 20150059312A1 US 201314013525 A US201314013525 A US 201314013525A US 2015059312 A1 US2015059312 A1 US 2015059312A1
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United States
Prior art keywords
exhaust stack
silencer
axial
exhaust
outlet
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Abandoned
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US14/013,525
Inventor
Prabhakaran Saraswathi Rajesh
Keshava Kumar Chilkunda Keshavamurthy
Rajkumar Jain
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General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US14/013,525 priority Critical patent/US20150059312A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: JAIN, RAJKUMAR, KESHAVAMURTHY, KESHAVA KUMAR CHILKUNDA, RAJESH, PRABHAKARAN SARASWATHI
Publication of US20150059312A1 publication Critical patent/US20150059312A1/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N1/00—Silencing apparatus characterised by method of silencing
    • F01N1/08—Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling
    • F01N1/085—Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling using a central core throttling gas passage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N1/00—Silencing apparatus characterised by method of silencing
    • F01N1/24—Silencing apparatus characterised by method of silencing by using sound-absorbing materials

Definitions

  • the subject matter disclosed herein relates to the art of exhaust stacks and, more particularly, to an exhaust stack having a co-axial silencer.
  • exhaust stacks are fluidically connected to an internal combustion engine, a furnace or other system that produces exhaust gases.
  • the exhaust stack delivers the exhaust gases from the system to ambient.
  • the exhaust stack includes filters that entrap particulate in the exhaust gases.
  • the exhaust stack may be sized to affect a cooling of the exhaust gases prior to being expelled to ambient.
  • the exhaust stack includes a silencer that absorbs sounds produced by flowing exhaust gases.
  • the silencer includes a plurality of sound absorbing baffles arranged in parallel along a flow path of the exhaust stack.
  • an exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis.
  • a co-axial silencer is arranged in one of the inlet section and outlet section.
  • the co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
  • a turbomachine includes a compressor portion and a turbine portion operatively connected to the compressor portion.
  • the turbine portion includes an exhaust outlet.
  • a combustor assembly includes at least one combustor fluidically connected to the compressor portion and the turbine portion.
  • An exhaust stack is fluidically connected to the exhaust outlet of the turbine portion.
  • the exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis.
  • a co-axial silencer is arranged in one of the inlet section and outlet section.
  • the co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
  • a turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion.
  • the turbine portion includes an exhaust outlet.
  • a combustor assembly includes at least one combustor fluidically connected to the compressor portion and the turbine portion.
  • a generator is operatively connected to the compressor portion.
  • An exhaust stack is fluidically connected to the exhaust outlet of the turbine portion.
  • the exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis.
  • a co-axial silencer is arranged in one of the inlet section and outlet section.
  • the co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
  • FIG. 1 is schematic diagram of a turbomachine system including an exhaust stack having a co-axial silencer, in accordance with an exemplary embodiment
  • FIG. 2 is a perspective view of the exhaust stack of FIG. 1 ;
  • FIG. 3 is a perspective view of a co-axial silencer, in accordance with an aspect of the exemplary embodiment
  • FIG. 4 is a cross-sectional side view of the co-axial silencer of FIG. 3 ;
  • FIG. 5 is a cross-sectional side view of a co-axial silencer, in accordance with another aspect of an exemplary embodiment.
  • FIG. 6 is a perspective view of an exhaust stack having a co-axial silencer arranged in accordance with another aspect of an exemplary embodiment.
  • a turbomachine system in accordance with an exemplary embodiment, is indicated generally at 2 , in FIG. 1 .
  • Turbomachine system 2 includes a turbomachine 3 having a compressor portion 4 operatively connected to a turbine portion 6 through a common compressor/turbine shaft 8 .
  • Compressor portion 4 is also fluidically connected to turbine portion 6 through a combustor assembly 10 having one or more combustors 12 .
  • Compressor portion 4 includes a compressor inlet 16 that is fluidically connected to an air intake system 18 .
  • Compressor portion 4 may also be connected to a generator 20 .
  • Turbine portion 6 includes a turbine portion outlet 22 that delivers exhaust gas to an exhaust stack 30 .
  • exhaust stack 30 includes a base section 35 having an inlet section 38 and an outlet section 40 .
  • Inlet section 38 extends along a first axis 42 .
  • Outlet section 40 extends along a second axis 44 that is generally perpendicular to first axis 42 .
  • Inlet section 38 extends from a first end 48 to a second end 49 that is coupled to base section 35 .
  • First end 48 includes an opening 50 that receives exhaust gas from turbine portion outlet 22 .
  • Outlet section 40 extends from a first end 54 to a second end 55 .
  • First end 54 of outlet section 40 is coupled to base section 35 and second end 55 is provided with an opening 56 .
  • a transition section 60 is arranged between base section 35 and outlet section 40 .
  • Transition section 60 provides an interface between a generally rectangular section (base section 35 ) and a generally tubular section (outlet section 40 ).
  • exhaust stack 30 includes a co-axial silencer 70 arranged along inlet section 38 .
  • co-axial silencer 70 includes a plurality of concentric baffles 74 that are arranged about a central member 78 .
  • Concentric baffles 74 are spaced one, from another, and from central member 78 , to form a plurality of generally annular flow passages, one of which is indicated at 80 .
  • Central member 78 is formed from an acoustic attenuating material.
  • Co-axial silencer 70 extends from a first end 83 to a second end 84 .
  • First end 83 defines an inlet 85 and second end 84 defines an outlet 86 .
  • each concentric baffle 74 and central member 78 are generally circular and include a substantially constant cross-section. More specifically, a diameter of concentric baffles 74 is generally consistent between first and second ends 83 and 84 .
  • FIG. 5 illustrates a co-axial silencer 90 in accordance with another aspect of the exemplary embodiment.
  • Co-axial silencer 90 includes a plurality of concentric baffles 92 that are arranged about a central member 94 .
  • Concentric baffles 92 are spaced one, from another, and from central member 94 , to form a plurality of generally annular flow passages, one of which is indicated at 96 .
  • Co-axial silencer 90 extends from a first end 98 to a second end 99 .
  • First end 98 defines an inlet 104 and second end 99 defines an outlet 105 .
  • each concentric baffle 92 and central member 94 taper outwardly from first end 98 to second end 99 . More specifically, a diameter of co-axial silencer 90 at first end 98 is less than a diameter at second end 99 .
  • a co-axial silencer in accordance with the exemplary embodiments, leads to a lower pressure drop across an exhaust diffuser which provides enhanced turbomachine system performance.
  • the co-axial silencer has a smaller footprint while also providing an increase in effective sound attenuation surfaces by virtue of the concentric baffles. The reduced footprint enables an exhaust stack to have a shorter height without sacrificing performance.
  • the co-axial silencer in accordance with any of the embodiments, may be arranged along the outlet section, as shown in FIG. 6 , wherein like reference numbers represent corresponding parts in the respective views.
  • the exhaust stack may be used in a wide range of systems spanning any number of technologies.
  • the co-axial silencer may take on a variety of geometries including oblong, oval, elliptical, rectangular, and the like.

Abstract

An exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis. A co-axial silencer is arranged in one of the inlet section and outlet section. The co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.

Description

    BACKGROUND OF THE INVENTION
  • The subject matter disclosed herein relates to the art of exhaust stacks and, more particularly, to an exhaust stack having a co-axial silencer.
  • In general, exhaust stacks are fluidically connected to an internal combustion engine, a furnace or other system that produces exhaust gases. The exhaust stack delivers the exhaust gases from the system to ambient. In some cases, the exhaust stack includes filters that entrap particulate in the exhaust gases. The exhaust stack may be sized to affect a cooling of the exhaust gases prior to being expelled to ambient. In some cases, the exhaust stack includes a silencer that absorbs sounds produced by flowing exhaust gases. The silencer includes a plurality of sound absorbing baffles arranged in parallel along a flow path of the exhaust stack.
    • BRIEF DESCRIPTION OF THE INVENTION
  • According to one aspect of an exemplary embodiment, an exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis. A co-axial silencer is arranged in one of the inlet section and outlet section. The co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
  • According to another aspect of an exemplary embodiment, a turbomachine includes a compressor portion and a turbine portion operatively connected to the compressor portion. The turbine portion includes an exhaust outlet. A combustor assembly includes at least one combustor fluidically connected to the compressor portion and the turbine portion. An exhaust stack is fluidically connected to the exhaust outlet of the turbine portion. The exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis. A co-axial silencer is arranged in one of the inlet section and outlet section. The co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
  • According to yet another aspect of an exemplary embodiment, a turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes an exhaust outlet. A combustor assembly includes at least one combustor fluidically connected to the compressor portion and the turbine portion. A generator is operatively connected to the compressor portion. An exhaust stack is fluidically connected to the exhaust outlet of the turbine portion. The exhaust stack includes an inlet section extending along a first axis and an outlet section extending along a second axis. A co-axial silencer is arranged in one of the inlet section and outlet section. The co-axial silencer includes a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
  • These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
    • BRIEF DESCRIPTION OF DRAWINGS
  • The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
  • FIG. 1 is schematic diagram of a turbomachine system including an exhaust stack having a co-axial silencer, in accordance with an exemplary embodiment;
  • FIG. 2 is a perspective view of the exhaust stack of FIG. 1;
  • FIG. 3 is a perspective view of a co-axial silencer, in accordance with an aspect of the exemplary embodiment;
  • FIG. 4 is a cross-sectional side view of the co-axial silencer of FIG. 3;
  • FIG. 5 is a cross-sectional side view of a co-axial silencer, in accordance with another aspect of an exemplary embodiment; and
  • FIG. 6 is a perspective view of an exhaust stack having a co-axial silencer arranged in accordance with another aspect of an exemplary embodiment.
    •
  • The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
    • DETAILED DESCRIPTION OF THE INVENTION
  • A turbomachine system, in accordance with an exemplary embodiment, is indicated generally at 2, in FIG. 1. Turbomachine system 2 includes a turbomachine 3 having a compressor portion 4 operatively connected to a turbine portion 6 through a common compressor/turbine shaft 8. Compressor portion 4 is also fluidically connected to turbine portion 6 through a combustor assembly 10 having one or more combustors 12. Compressor portion 4 includes a compressor inlet 16 that is fluidically connected to an air intake system 18. Compressor portion 4 may also be connected to a generator 20. Of course, the particular connection of generator 20 to turbomachine 2 may vary. Turbine portion 6 includes a turbine portion outlet 22 that delivers exhaust gas to an exhaust stack 30.
  • As shown in FIG. 2, exhaust stack 30 includes a base section 35 having an inlet section 38 and an outlet section 40. Inlet section 38 extends along a first axis 42. Outlet section 40 extends along a second axis 44 that is generally perpendicular to first axis 42. Inlet section 38 extends from a first end 48 to a second end 49 that is coupled to base section 35. First end 48 includes an opening 50 that receives exhaust gas from turbine portion outlet 22. Outlet section 40 extends from a first end 54 to a second end 55. First end 54 of outlet section 40 is coupled to base section 35 and second end 55 is provided with an opening 56. A transition section 60 is arranged between base section 35 and outlet section 40. Transition section 60 provides an interface between a generally rectangular section (base section 35) and a generally tubular section (outlet section 40). In accordance with an exemplary embodiment, exhaust stack 30 includes a co-axial silencer 70 arranged along inlet section 38.
  • As shown in FIGS. 3 and 4, co-axial silencer 70 includes a plurality of concentric baffles 74 that are arranged about a central member 78. Concentric baffles 74 are spaced one, from another, and from central member 78, to form a plurality of generally annular flow passages, one of which is indicated at 80. Central member 78 is formed from an acoustic attenuating material. Co-axial silencer 70 extends from a first end 83 to a second end 84. First end 83 defines an inlet 85 and second end 84 defines an outlet 86. In the exemplary embodiment shown, each concentric baffle 74 and central member 78 are generally circular and include a substantially constant cross-section. More specifically, a diameter of concentric baffles 74 is generally consistent between first and second ends 83 and 84.
  • FIG. 5 illustrates a co-axial silencer 90 in accordance with another aspect of the exemplary embodiment. Co-axial silencer 90 includes a plurality of concentric baffles 92 that are arranged about a central member 94. Concentric baffles 92 are spaced one, from another, and from central member 94, to form a plurality of generally annular flow passages, one of which is indicated at 96. Co-axial silencer 90 extends from a first end 98 to a second end 99. First end 98 defines an inlet 104 and second end 99 defines an outlet 105. In the exemplary embodiment shown, each concentric baffle 92 and central member 94 taper outwardly from first end 98 to second end 99. More specifically, a diameter of co-axial silencer 90 at first end 98 is less than a diameter at second end 99.
  • At this point it should be understood that the exemplary embodiments describe a co-axial silencer for an exhaust stack. A co-axial silencer, in accordance with the exemplary embodiments, leads to a lower pressure drop across an exhaust diffuser which provides enhanced turbomachine system performance. In addition to a lower pressure drop, the co-axial silencer has a smaller footprint while also providing an increase in effective sound attenuation surfaces by virtue of the concentric baffles. The reduced footprint enables an exhaust stack to have a shorter height without sacrificing performance. Further, it should be understood that while shown arranged at the inlet section, the co-axial silencer, in accordance with any of the embodiments, may be arranged along the outlet section, as shown in FIG. 6, wherein like reference numbers represent corresponding parts in the respective views. Also, while shown and described as being fluidically connected to a turbomachine system, the exhaust stack, with co-axial silencer, may be used in a wide range of systems spanning any number of technologies. Finally, while shown and described as being generally circular, the co-axial silencer may take on a variety of geometries including oblong, oval, elliptical, rectangular, and the like.
  • While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

Claims (20)

What is claimed is:
1. An exhaust stack comprising:
an inlet section extending along a first axis;
an outlet section extending along a second axis; and
a co-axial silencer arranged in one of the inlet section and outlet section, the co-axial silencer including a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
2. The exhaust stack according to claim 1, wherein each of the plurality of concentric baffles includes a substantially constant diameter.
3. The exhaust stack according to claim 1, wherein each of the plurality of concentric baffles taper from a first end to a second end.
4. The exhaust stack according to claim 3, wherein each of the plurality of concentric baffles taper outwardly from the first end to the second end.
5. The exhaust stack according to claim 4, wherein the first end defines an inlet of the co-axial silencer.
6. The exhaust stack according to claim 1, wherein the plurality of concentric baffles extend about a central member.
7. The exhaust stack according to claim 6, wherein the central member is formed from an acoustic attenuating material.
8. The exhaust stack according to claim 6, wherein the central member includes a substantially constant diameter.
9. The exhaust stack according to claim 1, wherein the co-axial silencer is arranged in the inlet section.
10. The exhaust stack according to claim 1, wherein the co-axial silencer is arranged in the outlet section.
11. A turbomachine comprising:
a compressor portion;
a turbine portion operatively connected to the compressor portion, the turbine portion including an exhaust outlet;
a combustor assembly including at least one combustor fluidically connected to the compressor portion and the turbine portion; and
an exhaust stack fluidically connected to the exhaust outlet of the turbine portion, the exhaust stack comprising:
an inlet section extending along a first axis;
an outlet section extending along a second axis; and
a co-axial silencer arranged in one of the inlet section and outlet section, the co-axial silencer including a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
12. The turbomachine according to claim 11, wherein each of the plurality of concentric baffles includes a substantially constant diameter.
13. The turbomachine according to claim 11, wherein each of the plurality of concentric baffles taper from a first end to a second end.
14. The turbomachine according to claim 13, wherein each of the plurality of concentric baffles taper outwardly from the first end to the second end.
15. The turbomachine according to claim 11, wherein the co-axial silencer is arranged in the inlet section.
16. A turbomachine system comprising:
a compressor portion;
a turbine portion operatively connected to the compressor portion, the turbine portion including an exhaust outlet;
a combustor assembly including at least one combustor fluidically connected to the compressor portion and the turbine portion;
a generator operatively connected to the compressor portion; and
an exhaust stack fluidically connected to the exhaust outlet of the turbine portion, the exhaust stack comprising:
an inlet section extending along a first axis;
an outlet section extending along a second axis; and
a co-axial silencer arranged in one of the inlet section and outlet section, the co-axial silencer including a plurality of concentric baffles configured and disposed to absorb acoustics generated by fluid flow through the exhaust stack.
17. The turbomachine system according to claim 16, wherein each of the plurality of concentric baffles includes a substantially constant diameter.
18. The turbomachine system according to claim 16, wherein each of the plurality of concentric baffles taper from a first end to a second end.
19. The turbomachine system according to claim 18, wherein each of the plurality of concentric baffles taper outwardly from the first end to the second end.
20. The turbomachine system according to claim 16, wherein the co-axial silencer is arranged in the inlet section.
US14/013,525 2013-08-29 2013-08-29 Exhaust stack having a co-axial silencer Abandoned US20150059312A1 (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150069763A1 (en) * 2013-09-10 2015-03-12 General Electric Company Load cover
US20160348584A1 (en) * 2015-05-26 2016-12-01 General Electric Company Turbomachine load coupling device having a natural convection ventilation system
US20190120143A1 (en) * 2017-10-19 2019-04-25 General Electric Company Modular acoustic blocks and acoustic liners constructed therefrom
US10704464B2 (en) 2016-02-16 2020-07-07 General Electric Company Acoustic nozzles for inlet bleed heat systems

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US20130086906A1 (en) * 2010-07-06 2013-04-11 Turbomeca Heat-exchange architecture built into the exhaust of a turbine engine
US20140023493A1 (en) * 2011-03-29 2014-01-23 Mitsubishi Heavy Industries, Ltd. Turbine exhaust structure and gas turbine
US9133733B2 (en) * 2009-12-16 2015-09-15 MDS Aero Support Corporation Turbine detuner for recovering kinetic energy from gas turbine engine exhaust gases
US9309842B2 (en) * 2013-02-07 2016-04-12 General Electric Company Air inlet silencer for turbomachines

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US2720935A (en) * 1950-08-30 1955-10-18 Jarvis C Marble Silencing of sound
US3802187A (en) * 1972-06-01 1974-04-09 Avco Corp Exhaust system for rear drive engine
US4802821A (en) * 1986-09-26 1989-02-07 Bbc Brown Boveri Ag Axial flow turbine
US5160080A (en) * 1990-10-01 1992-11-03 General Electric Company Gas turbine engine and method of operation for providing increased output shaft horsepower
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US5728979A (en) * 1993-04-05 1998-03-17 Air Handling Engineering Ltd. Air handling structure for fan inlet and outlet
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US20040118102A1 (en) * 2002-12-10 2004-06-24 Ingersoll-Rand Energy Systems Corporation Wide-angle concentric diffuser
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US9309842B2 (en) * 2013-02-07 2016-04-12 General Electric Company Air inlet silencer for turbomachines

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150069763A1 (en) * 2013-09-10 2015-03-12 General Electric Company Load cover
US20160348584A1 (en) * 2015-05-26 2016-12-01 General Electric Company Turbomachine load coupling device having a natural convection ventilation system
US10704464B2 (en) 2016-02-16 2020-07-07 General Electric Company Acoustic nozzles for inlet bleed heat systems
US20190120143A1 (en) * 2017-10-19 2019-04-25 General Electric Company Modular acoustic blocks and acoustic liners constructed therefrom
US10815894B2 (en) * 2017-10-19 2020-10-27 General Electric Company Modular acoustic blocks and acoustic liners constructed therefrom

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Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

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