US3791759A - Turbine pressure attenuation plenum chambers - Google Patents

Turbine pressure attenuation plenum chambers Download PDF

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Publication number
US3791759A
US3791759A US00260645A US3791759DA US3791759A US 3791759 A US3791759 A US 3791759A US 00260645 A US00260645 A US 00260645A US 3791759D A US3791759D A US 3791759DA US 3791759 A US3791759 A US 3791759A
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United States
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turbine
vanes
apertures
plenum
plenum chamber
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US00260645A
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J Tetrault
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US Air Force
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US Air Force
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • a conventional gas turbine engine generally comprises of a compressor, a combustion products generation means, a turbine wheel, a duct connecting these elements and a shroud surrounding the turbine wheel.
  • pressurized air is supplied to the combustor and supports combustion of fuel to generate an annular hot gas stream.
  • This hot gas stream generally speaking, then drives a turbine which powers a compressor for pressurizing the air delivered to the combustor.
  • the hot gas stream may then power a second turbine or be discharged from a nozzle to obtain an energy output from the engine.
  • the turbine of this invention utilizes plenum chambers adjacent the turbine wheel in order to overcome the problems encountered heretofore by reducing the excess pressure within the turbine.
  • Chambers have been constructed within the turbine having a plurality of strategically located apertures therein in order to relieve this excess pressure build up. With the plenum chambers located adjacent the turbine wheel the circumferential pressure distortion is greatly reduced and the gas path air then breathes" to a common pressure.
  • FIGURE of this drawing is a side elevational view shown partly in cross-section of the turbine pressure attenuation plenum chambers of this invention.
  • the turbine 12 generally comprises of an air compressor, combustion products generation means, at least one turbine wheel having a plurality of blades 14 and stationary vanes 15, a duct connecting these elements and a rotating hub 16 surrounding blades 14 and vanes 15 of turbine 12.
  • Hub 16 supports and rotates with turbine blades 14.
  • Plenum chambers 20 and 22 are located opposite one another adjacent stationary vane 15 with plenum chamber 20 located above vanes 15, while the other chamber 22 is approximately at the midpoint thereof.
  • Each plenum chamber 20 and 22 is triangular in configuration and has strategically placed apertures 24 therein.
  • Upper chamber 20 having three such apertures, with lower chamber 22 having two such apertures 24. It is critical that apertures 24 be positioned adjacent vanes 15 as shown in the FIGURE in order to lower the circumferential pressure distortion and provide a gas path within turbine 12. By eliminating this excess pressure, turbine efficiency is greatly increased.
  • a turbine having a plurality of blades and vanes and a shroud surrounding said blades and vanes, the improvement therein comprising a means defining first and second plenum chambers located adjacent said vanes for reducing circumferential pressure distortion of said turbine, said first plenum chamber positioned above said vanes, said second plenum chamber positioned at substantially the midpoint of said vanes, said first plenum chamber having a plurality of apertures therein and said second plenum chamber having a pair of apertures therein wherein said apertures in said first plenum chamber oppose said apertures in said second plenum chamber.
  • each of said plenum chambers are of a triangular configuration.

Abstract

A turbine having a plurality of pressure attenuation plenum chambers. These chambers are located adjacent the vanes of a turbine thereby relieving the excess pressure by distributing it through a series of apertures in the plenum chamber walls.

Description

United States Patent 1191 Tetrault Feb. 12, 1974 [54] TURBINE PRESSURE ATTENUATION 2,225,398 12/1940 Hamblin 415/119 PLENUM CHAMBERS 2,674,845 4/1954 Pouchot 415/D1G. 1 2,682,363 6/1954 Lombard el al. 415/D1G. l [75] lnventor: Jose h A. T r l East Hartford, 2,720,356 1'0 1955 Erwin 415 144 Conn. 2,848,156 8/1958 Oppenheimer 415/144 3,303,997 2/1967 Welch et al, 415/144 [731] Ass1gnee: The United States of America as 3,398,881 8H9 Greenberg m a! 5/144 represented y the secreml'y the 3,690,786 9/1972 Silvestri 415/144 Air Force, Washington, DC. 22 F1 d J 7 1972 FOREIGN PATENTS OR APPLICATIONS 1 une 905,262 9/1962 Great Britain... 415/144 [21] Appl. No.: 260,645
. Primary ExaminerfHenry F. Raduazo [52] US. Cl. 415/119, 415/144, 415/219 R [51] Int. Cl. FOln- 27/02, F04d 29/68 57 ABSTRACT [58) Field of Search... 415/144, DIG. 1, 219 R, 119,
4]5/2|9 A turbme havmg a plurahty of pressure attenuanon plenum chambers. These chambers are located adja- [56] References Cited cent the vanes of a turbine thereby relieving the ex- UNITED STATES PATENTS cess pressure by distrlbutmg it through a senes of upertures 1n the plenum chamber walls. 3,572,960 3/1971 McBride 415/1 19 2,252,256 8/1941 Harris 415/119 3 Claims, 1 Drawing Figure TURBINE PRESSUREATTENUATION PLENUM CHAMBERS BACKGROUND OF THE INVENTION This invention relates generally to turbines and, more particularly to plenum chambers located within the turbine to eliminate pressure distortion.
A conventional gas turbine engine generally comprises of a compressor, a combustion products generation means, a turbine wheel, a duct connecting these elements and a shroud surrounding the turbine wheel. In this type of gas turbine engine pressurized air is supplied to the combustor and supports combustion of fuel to generate an annular hot gas stream. This hot gas stream, generally speaking, then drives a turbine which powers a compressor for pressurizing the air delivered to the combustor. The hot gas stream may then power a second turbine or be discharged from a nozzle to obtain an energy output from the engine.
It is well known that the efficiency of such a gas turbine engine is related to the operating temperature of the turbine and that the efficiency may be raised by increasing the operating temperature. A further consideration in the efficiency of such a turbine is the elimination of a pressure build up within the turbine which causes distortion thereof. With regard to the operating temperature much time and energy has been expended in the construction of complex cooling systems for the turbine itself. However, little consideration has been given to the elimination of the pressure build up within the turbines which also constitutes an essential factor in turbine efficiency.
SUMMARY OF THE INVENTION The turbine of this invention utilizes plenum chambers adjacent the turbine wheel in order to overcome the problems encountered heretofore by reducing the excess pressure within the turbine.
Chambers have been constructed within the turbine having a plurality of strategically located apertures therein in order to relieve this excess pressure build up. With the plenum chambers located adjacent the turbine wheel the circumferential pressure distortion is greatly reduced and the gas path air then breathes" to a common pressure.
It is therefore an object of this invention to provide turbine pressure attenuation plenum chambers which substantially reduce the pressure distortion within a turbine.
It is another object of this invention to provide turbine pressure attenuation plenum chambers which utilize conventional, currently available components which lend themselves to standard mass producing manufacturing techniques.
For a better understanding of this invention, together with other and further objects thereof, reference is made to the following description taken in connecting 2 with the accompanying drawing and its scope will be brought out in the appended claims.
DESCRIPTION OF THE DRAWING The only FIGURE of this drawing is a side elevational view shown partly in cross-section of the turbine pressure attenuation plenum chambers of this invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT Reference is now made to the only FIGURE of the drawing which represents a side elevation view of the turbine pressure attenuation plenum chambers 10 of this invention. The turbine 12 generally comprises of an air compressor, combustion products generation means, at least one turbine wheel having a plurality of blades 14 and stationary vanes 15, a duct connecting these elements and a rotating hub 16 surrounding blades 14 and vanes 15 of turbine 12.
Hub 16 supports and rotates with turbine blades 14. Plenum chambers 20 and 22 are located opposite one another adjacent stationary vane 15 with plenum chamber 20 located above vanes 15, while the other chamber 22 is approximately at the midpoint thereof. Each plenum chamber 20 and 22 is triangular in configuration and has strategically placed apertures 24 therein. Upper chamber 20 having three such apertures, with lower chamber 22 having two such apertures 24. It is critical that apertures 24 be positioned adjacent vanes 15 as shown in the FIGURE in order to lower the circumferential pressure distortion and provide a gas path within turbine 12. By eliminating this excess pressure, turbine efficiency is greatly increased.
Although this invention has been described with reference to a particular embodiment, it will be understood to those skilled in the art that this invention is capable of a variety of alternate embodiments within the spirit and scope of the appended claims.
I claim:
1. In a turbine having a plurality of blades and vanes and a shroud surrounding said blades and vanes, the improvement therein comprising a means defining first and second plenum chambers located adjacent said vanes for reducing circumferential pressure distortion of said turbine, said first plenum chamber positioned above said vanes, said second plenum chamber positioned at substantially the midpoint of said vanes, said first plenum chamber having a plurality of apertures therein and said second plenum chamber having a pair of apertures therein wherein said apertures in said first plenum chamber oppose said apertures in said second plenum chamber.
2. In a turbine as defined in claim 1 wherein there are three apertures in said first plenum chamber.
3. In a turbine as defined in claim 2 wherein each of said plenum chambers are of a triangular configuration.

Claims (3)

1. In a turbine having a plurality of blades and vanes and a shroud surrounding said blades and vanes, the improvement therein comprising a means defining first and second plenum chambers located adjacent said vanes for reducing circumferential pressure distortion of said turbine, said first plenum chamber positioned above said vanes, said second plenum chamber positioned at substantially the midpoint of said vanes, said first plenum chamber having a plurality of apertures therein and said second plenum chamber having a pair of apertures therein wherein said apertures in said first plenum chamber oppose said apertures in said second plenum chamber.
2. In a turbine as defined in claim 1 wherein there are three apertures in said first plenum chamber.
3. In a turbine as defined in claim 2 wherein each of said plenum chambers are of a triangular configuration.
US00260645A 1972-06-07 1972-06-07 Turbine pressure attenuation plenum chambers Expired - Lifetime US3791759A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6419448B1 (en) * 2000-03-20 2002-07-16 Jerzy A. Owczarek Flow by-pass system for use in steam turbine exhaust hoods

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2225398A (en) * 1939-09-13 1940-12-17 Clyde M Hamblin Construction of ventilating fans
US2252256A (en) * 1939-01-11 1941-08-12 Harris Eliot Huntington Sound attenuator for air impellers
US2674845A (en) * 1951-05-02 1954-04-13 Walter D Pouchot Diffuser apparatus with boundary layer control
US2682363A (en) * 1950-12-08 1954-06-29 Rolls Royce Gas turbine engine
US2720356A (en) * 1952-06-12 1955-10-11 John R Erwin Continuous boundary layer control in compressors
US2848156A (en) * 1956-12-18 1958-08-19 Gen Electric Fixed stator vane assemblies
GB905262A (en) * 1958-11-21 1962-09-05 Rolls Royce Improvements in or relating to structures having annular gas flow passages therein
US3303997A (en) * 1965-04-21 1967-02-14 United Aircraft Corp Compressor air seal
US3398881A (en) * 1967-01-10 1968-08-27 United Aircraft Corp Compressor bleed device
US3572960A (en) * 1969-01-02 1971-03-30 Gen Electric Reduction of sound in gas turbine engines
US3690786A (en) * 1971-05-10 1972-09-12 Westinghouse Electric Corp Low pressure end diffuser for axial flow elastic fluid turbines

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2252256A (en) * 1939-01-11 1941-08-12 Harris Eliot Huntington Sound attenuator for air impellers
US2225398A (en) * 1939-09-13 1940-12-17 Clyde M Hamblin Construction of ventilating fans
US2682363A (en) * 1950-12-08 1954-06-29 Rolls Royce Gas turbine engine
US2674845A (en) * 1951-05-02 1954-04-13 Walter D Pouchot Diffuser apparatus with boundary layer control
US2720356A (en) * 1952-06-12 1955-10-11 John R Erwin Continuous boundary layer control in compressors
US2848156A (en) * 1956-12-18 1958-08-19 Gen Electric Fixed stator vane assemblies
GB905262A (en) * 1958-11-21 1962-09-05 Rolls Royce Improvements in or relating to structures having annular gas flow passages therein
US3303997A (en) * 1965-04-21 1967-02-14 United Aircraft Corp Compressor air seal
US3398881A (en) * 1967-01-10 1968-08-27 United Aircraft Corp Compressor bleed device
US3572960A (en) * 1969-01-02 1971-03-30 Gen Electric Reduction of sound in gas turbine engines
US3690786A (en) * 1971-05-10 1972-09-12 Westinghouse Electric Corp Low pressure end diffuser for axial flow elastic fluid turbines

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6419448B1 (en) * 2000-03-20 2002-07-16 Jerzy A. Owczarek Flow by-pass system for use in steam turbine exhaust hoods

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