GB1331446A - Hot gas generators - Google Patents
Hot gas generatorsInfo
- Publication number
- GB1331446A GB1331446A GB1756170A GB1331446DA GB1331446A GB 1331446 A GB1331446 A GB 1331446A GB 1756170 A GB1756170 A GB 1756170A GB 1331446D A GB1331446D A GB 1331446DA GB 1331446 A GB1331446 A GB 1331446A
- Authority
- GB
- United Kingdom
- Prior art keywords
- combustion chamber
- compressor
- air
- fuel mixture
- 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
Links
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
Abstract
1331446 Gas turbine type gas generator C A V Ltd 19 April 1971 [14 April 1970] 17561/70 Heading F1G The invention relates to a hot gas generator which comprises a first compressor 10 which supplies an air/fuel mixture to the burner 24 of a combustion chamber 22, a second compressor 13 which supplies dilution fluid to the combustion chamber, and a turbine 20 drivingly connected to the compressors through shaft 17 and driven by gases from the combustion chamber. The dilution fluid supplied by the second compressor is an air/fuel mixture, a fuel injection device 16 being disposed in the inlet 14 of the compressor. A second combustion chamber 21 is disposed downstream of the turbine 20, the chamber having a divergent inlet. It is arranged that the velocity of the gases in the combustion chamber 22 after the mixture of the dilution fluid therein is greater than the flame speed of the air/fuel mixture constituting the dilution fluid. The velocity of the gases entering the second combustion chamber 21 falls to a value lower than the flame speed whereby combustion of the air/fuel mixture may take place within the second combustion chamber. (For Figure see next page)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1756170 | 1970-04-14 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1331446A true GB1331446A (en) | 1973-09-26 |
Family
ID=10097352
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1756170A Expired GB1331446A (en) | 1970-04-14 | 1971-04-19 | Hot gas generators |
Country Status (4)
Country | Link |
---|---|
US (1) | US3740948A (en) |
DE (1) | DE2117219A1 (en) |
FR (1) | FR2086063B1 (en) |
GB (1) | GB1331446A (en) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3971209A (en) * | 1972-02-09 | 1976-07-27 | Chair Rory Somerset De | Gas generators |
GB8914825D0 (en) * | 1989-06-28 | 1989-08-16 | 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 |
WO1998042968A2 (en) * | 1997-03-26 | 1998-10-01 | San Diego State University Foundation | Fuel/air mixing device for jet engines |
US20020166324A1 (en) | 1998-04-02 | 2002-11-14 | Capstone Turbine Corporation | Integrated turbine power generation system having low pressure supplemental catalytic reactor |
US20040119291A1 (en) * | 1998-04-02 | 2004-06-24 | Capstone Turbine Corporation | Method and apparatus for indirect catalytic combustor preheating |
US6192668B1 (en) * | 1999-10-19 | 2001-02-27 | Capstone Turbine Corporation | Method and apparatus for compressing gaseous fuel in a turbine engine |
US6269647B1 (en) | 1999-03-10 | 2001-08-07 | Robert S. Thompson, Jr. | Rotor system |
DE10035676A1 (en) * | 2000-07-21 | 2002-02-07 | Siemens Ag | 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 |
-
1971
- 1971-04-08 DE DE19712117219 patent/DE2117219A1/en active Pending
- 1971-04-08 US US00132429A patent/US3740948A/en not_active Expired - Lifetime
- 1971-04-14 FR FR7113193A patent/FR2086063B1/fr not_active Expired
- 1971-04-19 GB GB1756170A patent/GB1331446A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
US3740948A (en) | 1973-06-26 |
FR2086063A1 (en) | 1971-12-31 |
FR2086063B1 (en) | 1974-09-27 |
DE2117219A1 (en) | 1971-11-04 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PCNP | Patent ceased through non-payment of renewal fee |