US3740948A - Hot gas generator employing rotary turbine - Google Patents

Hot gas generator employing rotary turbine Download PDF

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Publication number
US3740948A
US3740948A US00132429A US3740948DA US3740948A US 3740948 A US3740948 A US 3740948A US 00132429 A US00132429 A US 00132429A US 3740948D A US3740948D A US 3740948DA US 3740948 A US3740948 A US 3740948A
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combustion chamber
air
fuel mixture
turbine
dilution fluid
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US00132429A
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E Kellett
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CAV Ltd
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CAV Ltd
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    • 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
    • F02C7/22—Fuel supply systems
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output

Definitions

  • a hot gas generator includes a combustion chamber the heated gases from which drives a turbine the combustion chamber being provided with air/fuel mixture for burning therein by a compressor driven by the turbine.
  • a second compressor is provided to supply dilution fluid in the form of an air/fuel mixture.
  • the dilution fluid together with the heated gases leaving the combustion chamber are maintained at a speed which is higher than the flame speed and the combustion of the air/fuel mixture which constitutes the dilution fluid takes place in a second combustion chamber which includes a divergent portion whereby the velocity of the gases is reduced below the flame speed.
  • This invention relates to hot gas generators of the kind comprising a combustion chamber, a first compressor for delivering an air/fuel mixture to the combustion chamber, a second compressor for delivering dilution fluid to the combustion chamber, a turbine coupled to said compressors for driving same, said turbine being driven by the heated gases leaving said combustion chamber.
  • the object of the invention is to provide such a generator in a form in which for a given size of generator and a given inlet temperature, the heat release can be increased.
  • the dilution fluid is an air/fuel mixture and there is disposed downstream of the turbine a second combustion chamber having a divergent portion, the arrangement being such that the velocity of the hot gases after the mixing of dilution fluid therewith is higher than the flame speed of the air/fuel mixture constituting the dilution fluid, the velocity of the gases entering the second combustion chamber falling therein to a velocity lower than the flame speed thereby allowing combustion of the air/fuel mixture to take place within the second combustion chamber.
  • a first compressor having an inlet 11 and an outlet 12.
  • the inlet 11 communicates with a conduit communicating with the atmosphere and formed in the wall of the conduit is an aperture 27 through which gaseous fuel can be admitted to the air flowing to the compressor.
  • a second compressor 13 having an inlet 14 and an outlet 15.
  • the inlet 14 communicates with the atmosphere and a fuel supply nozzle 16 is disposed adjacent the inlet.
  • the compressors are each provided with a rotor, the rotors being mounted upon a common shaft 17 which is coupled to the rotor of a turbine 18.
  • the turbine includes an inlet 19 and an outlet 20 which opens into a diverging combustion chamber 21.
  • a combustion chamber 22 which is surrounded by a casing 23.
  • the combustion chamber 22 at one end mounts a burner 24 and the burner is coupled to the outlet 12 of the first compressor.
  • the dilution fluid consists of air/fuel mixture derived from the outlet 15 of the first compressor.
  • the outlet 15 for this purpose being connected to the aforesaid annular space.
  • the air/fuel mixture leaving the first compressor is ignited by the ignitor 25 and burns within the combustion chamber 22.
  • the temperature of the heated gases is reduced in known manner by the dilution fluid which enters the combustion chamber by way of the apertures 26 and the heated gases then pass through the turbine 18 into the combustion chamber 21.
  • the heated gases leaving the combustion chamber 22 drive the turbine and this in turn drives the compressors so that once started the apparatus is self sustaining providing fuel is supplied to the burner.
  • a hot gas generator comprising a combustion chamber, an air/fuel mixture burner disposed in the combustion chamber, a first compressor for delivering air/fuel mixture to said burner, a second compressor for delivering air as dilution fluid to the combustion chamber for cooling the heated gases produced by the burner, a turbine coupled to said compressors for driving same, said turbine being driven by the heated gases leaving the combustion chamber, means for mixing fuel with the air flowing through said second compressor, so that the dilution fluid is an air/fuel mixture, and a second combustionchamber disposed downstream of the turbine, said second combustion chamber having a divergent portion, the generator being so arranged that the velocity of the hot gases after the mixing of the dilution fluid therewith is higher than the flame speed of the air/fuel mixture constituting the dilution fluid, the velocity of the gases entering the second combustion chamber falling therein to a velocity lower than the flame speed thereby allowing combustion of the air/fuel mixture to take place within the second combustion chamber.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

A hot gas generator includes a combustion chamber the heated gases from which drives a turbine the combustion chamber being provided with air/fuel mixture for burning therein by a compressor driven by the turbine. A second compressor is provided to supply dilution fluid in the form of an air/fuel mixture. The dilution fluid together with the heated gases leaving the combustion chamber are maintained at a speed which is higher than the flame speed and the combustion of the air/fuel mixture which constitutes the dilution fluid takes place in a second combustion chamber which includes a divergent portion whereby the velocity of the gases is reduced below the flame speed.

Description

United States Patent 1191 1111 3,740,948 Kellett June 26, 1973 HOT GAS GENERATOR EMPLOYING 2,679,137 5/1954 Probert (SO/39.65
ROTARY TURBINE 1,700,592 1/1929 Loepsinger 431/346 Inventor: Eric Kellett, London, England C.A.V. Limited, Birmingham, England Filed: Apr. 8, 1971 Appl. No.: 132,429
Assignee:
Foreign Application Priority Data Apr. l4, 1970 Great Britain 17,561/70 References Cited UNITED STATES PATENTS 5/1971 Schmidt 60/261 7/1962 Seifferlein 60/261 4/1958 Ogilvie .1 (JO/39.65
Primary Examiner-Carlton R. Croyle Assistant ExaminerWarren Olsen Attorney-Holman & Stern [57] ABSTRACT A hot gas generator includes a combustion chamber the heated gases from which drives a turbine the combustion chamber being provided with air/fuel mixture for burning therein by a compressor driven by the turbine. A second compressor is provided to supply dilution fluid in the form of an air/fuel mixture. The dilution fluid together with the heated gases leaving the combustion chamber are maintained at a speed which is higher than the flame speed and the combustion of the air/fuel mixture which constitutes the dilution fluid takes place in a second combustion chamber which includes a divergent portion whereby the velocity of the gases is reduced below the flame speed.
1 Claim, 1 Drawing Figure HOT GAS GENERATOR EMPLOYING ROTARY TURBINE This invention relates to hot gas generators of the kind comprising a combustion chamber, a first compressor for delivering an air/fuel mixture to the combustion chamber, a second compressor for delivering dilution fluid to the combustion chamber, a turbine coupled to said compressors for driving same, said turbine being driven by the heated gases leaving said combustion chamber.
The object of the invention is to provide such a generator in a form in which for a given size of generator and a given inlet temperature, the heat release can be increased.
According to the invention in a generator of the kind specified the dilution fluid is an air/fuel mixture and there is disposed downstream of the turbine a second combustion chamber having a divergent portion, the arrangement being such that the velocity of the hot gases after the mixing of dilution fluid therewith is higher than the flame speed of the air/fuel mixture constituting the dilution fluid, the velocity of the gases entering the second combustion chamber falling therein to a velocity lower than the flame speed thereby allowing combustion of the air/fuel mixture to take place within the second combustion chamber.
One example of a hot gas generator in accordance with the invention will now be described with reference to the accompanying drawing which shows a sectional side elevation of the generator.
Referring to the drawing there is provided a first compressor having an inlet 11 and an outlet 12. The inlet 11 communicates with a conduit communicating with the atmosphere and formed in the wall of the conduit is an aperture 27 through which gaseous fuel can be admitted to the air flowing to the compressor.
There is also provided a second compressor 13 having an inlet 14 and an outlet 15. The inlet 14 communicates with the atmosphere and a fuel supply nozzle 16 is disposed adjacent the inlet.
The compressors are each provided with a rotor, the rotors being mounted upon a common shaft 17 which is coupled to the rotor of a turbine 18. The turbine includes an inlet 19 and an outlet 20 which opens into a diverging combustion chamber 21.
Also provided is a combustion chamber 22 which is surrounded by a casing 23. The combustion chamber 22 at one end mounts a burner 24 and the burner is coupled to the outlet 12 of the first compressor. Projecting into the combustion chamber is an electrical ignitor 25 and the combustion chamber downstream of the burner is provided with apertures 26 through which dilution fluid from the space defined intermediate the combustion chamber 22 and its casing 23 can pass. The dilution fluid consists of air/fuel mixture derived from the outlet 15 of the first compressor. The outlet 15 for this purpose being connected to the aforesaid annular space.
In operation, the air/fuel mixture leaving the first compressor is ignited by the ignitor 25 and burns within the combustion chamber 22. The temperature of the heated gases is reduced in known manner by the dilution fluid which enters the combustion chamber by way of the apertures 26 and the heated gases then pass through the turbine 18 into the combustion chamber 21. The heated gases leaving the combustion chamber 22 drive the turbine and this in turn drives the compressors so that once started the apparatus is self sustaining providing fuel is supplied to the burner.
In order to obtain a greater heat release fuel is mixed with the air flowing through the second compressor but in order to prevent this fuel burning until it has passed through the turbine, it is arranged that the velocity of the dilution fluid and the gases leaving the combustion chamber 22 are higher than the flame speed of the air/fuel mixture constituting the dilution fluid. In view of this no combustion will take place until the gases enter the combustion chamber 21. This combustion chamber diverges and therefore the velocity of the gases falls below the flame speed. Once the velocity has fallen to a value below the flame speed spontaneous combustion takes place and the fuel which flows through the nozzle 16 burns within the combustion chamber 21.
In the manner described above a high heat release can be obtained for a given size of generator and for a given temperature of the hot gases entering the turbine, than can be achieved in the case where all the fuel is burnt within the combustion chamber 22.
Having thus described my invention what I claim as new and desire to secure by Letters Patent is:
l. A hot gas generator comprising a combustion chamber, an air/fuel mixture burner disposed in the combustion chamber, a first compressor for delivering air/fuel mixture to said burner, a second compressor for delivering air as dilution fluid to the combustion chamber for cooling the heated gases produced by the burner, a turbine coupled to said compressors for driving same, said turbine being driven by the heated gases leaving the combustion chamber, means for mixing fuel with the air flowing through said second compressor, so that the dilution fluid is an air/fuel mixture, and a second combustionchamber disposed downstream of the turbine, said second combustion chamber having a divergent portion, the generator being so arranged that the velocity of the hot gases after the mixing of the dilution fluid therewith is higher than the flame speed of the air/fuel mixture constituting the dilution fluid, the velocity of the gases entering the second combustion chamber falling therein to a velocity lower than the flame speed thereby allowing combustion of the air/fuel mixture to take place within the second combustion chamber. v

Claims (1)

1. A hot gas generator comprising a combustion chamber, an air/fuel mixture burner disposed in the combustion chamber, a first compressor for delivering air/fuel mixture to said burner, a second compressor for delivering air as dilution fluid to the combustion chamber for cooling the heated gases produced by the burner, a turbine coupled to said compressors for driving same, said turbine being driven by the heated gases leaving the combustion chamber, means for mixing fuel with the air flowing through said second compressor, so that the dilution fluid is an air/fuel mixture, and a second combustion chamber disposed downstream of the turbine, said second combustion chamber having a divergent portion, the generator being so arranged that the velocity of the hot gases after the mixing of the dilution fluid therewith is higher than the flame speed of the air/fuel mixture constituting the dilution fluid, the velocity of the gases entering the second combustion chamber falling therein to a velocity lower than the flame speed thereby allowing combustion of the air/fuel mixture to take place within the second combustion chamber.
US00132429A 1970-04-14 1971-04-08 Hot gas generator employing rotary turbine Expired - Lifetime US3740948A (en)

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GB1756170 1970-04-14

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DE (1) DE2117219A1 (en)
FR (1) FR2086063B1 (en)
GB (1) GB1331446A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3971209A (en) * 1972-02-09 1976-07-27 Chair Rory Somerset De Gas generators
EP0405730A1 (en) * 1989-06-28 1991-01-02 ROLLS-ROYCE plc Gas turbine engine power unit
US5048298A (en) * 1989-07-10 1991-09-17 Sundstrand Corporation Low cost fuel system for a gas turbine engine
US5111655A (en) * 1989-12-22 1992-05-12 Sundstrand Corporation Single wall combustor assembly
US5970715A (en) * 1997-03-26 1999-10-26 San Diego State University Foundation Fuel/air mixing device for jet engines
US6192668B1 (en) * 1999-10-19 2001-02-27 Capstone Turbine Corporation Method and apparatus for compressing gaseous fuel in a turbine engine
US6205770B1 (en) 1999-03-10 2001-03-27 Gregg G. Williams Rocket engine
WO2002008592A1 (en) * 2000-07-21 2002-01-31 Siemens Aktiengesellschaft Gas turbine and method for operating a gas turbine
US20040119291A1 (en) * 1998-04-02 2004-06-24 Capstone Turbine Corporation Method and apparatus for indirect catalytic combustor preheating
US20040148942A1 (en) * 2003-01-31 2004-08-05 Capstone Turbine Corporation Method for catalytic combustion in a gas- turbine engine, and applications thereof
US6960840B2 (en) 1998-04-02 2005-11-01 Capstone Turbine Corporation Integrated turbine power generation system with catalytic reactor

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3971209A (en) * 1972-02-09 1976-07-27 Chair Rory Somerset De Gas generators
EP0405730A1 (en) * 1989-06-28 1991-01-02 ROLLS-ROYCE plc Gas turbine engine power unit
US5085038A (en) * 1989-06-28 1992-02-04 Rolls-Royce Plc Gas turbine engine
US5048298A (en) * 1989-07-10 1991-09-17 Sundstrand Corporation Low cost fuel system for a gas turbine engine
US5111655A (en) * 1989-12-22 1992-05-12 Sundstrand Corporation Single wall combustor assembly
US5970715A (en) * 1997-03-26 1999-10-26 San Diego State University Foundation Fuel/air mixing device for jet engines
US6960840B2 (en) 1998-04-02 2005-11-01 Capstone Turbine Corporation Integrated turbine power generation system with catalytic reactor
US20040119291A1 (en) * 1998-04-02 2004-06-24 Capstone Turbine Corporation Method and apparatus for indirect catalytic combustor preheating
US6220016B1 (en) 1999-03-10 2001-04-24 Guido D. Defever Rocket engine cooling system
US6269647B1 (en) 1999-03-10 2001-08-07 Robert S. Thompson, Jr. Rotor system
US6205770B1 (en) 1999-03-10 2001-03-27 Gregg G. Williams Rocket engine
US6381944B2 (en) * 1999-10-19 2002-05-07 Capstone Turbine Corporation Method and apparatus for compressing gaseous fuel in a turbine engine
US20020073713A1 (en) * 1999-10-19 2002-06-20 Capstone Turbine Corporation Method and apparatus for compressing gaseous fuel in a turbine engine
US6192668B1 (en) * 1999-10-19 2001-02-27 Capstone Turbine Corporation Method and apparatus for compressing gaseous fuel in a turbine engine
WO2002008592A1 (en) * 2000-07-21 2002-01-31 Siemens Aktiengesellschaft Gas turbine and method for operating a gas turbine
US20040040309A1 (en) * 2000-07-21 2004-03-04 Manfred Ziegner Gas turbine and method for operating a gas turbine
US6840049B2 (en) 2000-07-21 2005-01-11 Siemens Aktiengesellschaft Gas turbine and method for operating a gas turbine
US20040148942A1 (en) * 2003-01-31 2004-08-05 Capstone Turbine Corporation Method for catalytic combustion in a gas- turbine engine, and applications thereof

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Publication number Publication date
DE2117219A1 (en) 1971-11-04
GB1331446A (en) 1973-09-26
FR2086063B1 (en) 1974-09-27
FR2086063A1 (en) 1971-12-31

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