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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US
United States
Prior art keywords
combustion chamber
air
fuel mixture
turbine
dilution fluid
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00132429A
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English (en)
Inventor
E Kellett
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
CAV Ltd
Original Assignee
CAV Ltd
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Filing date
Publication date
Application filed by CAV Ltd filed Critical CAV Ltd
Application granted granted Critical
Publication of US3740948A publication Critical patent/US3740948A/en
Anticipated expiration legal-status Critical
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Classifications

    • 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)
US00132429A 1970-04-14 1971-04-08 Hot gas generator employing rotary turbine Expired - Lifetime US3740948A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1756170 1970-04-14

Publications (1)

Publication Number Publication Date
US3740948A true US3740948A (en) 1973-06-26

Family

ID=10097352

Family Applications (1)

Application Number Title Priority Date Filing Date
US00132429A Expired - Lifetime US3740948A (en) 1970-04-14 1971-04-08 Hot gas generator employing rotary turbine

Country Status (4)

Country Link
US (1) US3740948A (en:Method)
DE (1) DE2117219A1 (en:Method)
FR (1) FR2086063B1 (en:Method)
GB (1) GB1331446A (en:Method)

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 (de) * 2000-07-21 2002-01-31 Siemens Aktiengesellschaft Gasturbine und verfahren zum betrieb einer gasturbine
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 (de) * 2000-07-21 2002-01-31 Siemens Aktiengesellschaft Gasturbine und verfahren zum betrieb einer gasturbine
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

Also Published As

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

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