GB1445415A - Compressor bleed-off device for gas turbine jet engines - Google Patents
Compressor bleed-off device for gas turbine jet enginesInfo
- Publication number
- GB1445415A GB1445415A GB4384773A GB4384773A GB1445415A GB 1445415 A GB1445415 A GB 1445415A GB 4384773 A GB4384773 A GB 4384773A GB 4384773 A GB4384773 A GB 4384773A GB 1445415 A GB1445415 A GB 1445415A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ring
- compressor
- air
- gas turbine
- sept
- 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
- 230000000740 bleeding effect Effects 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/023—Details or means for fluid extraction
Abstract
1445415 Axial-flow compressors MOTOREN-UND TURBINEN-UNION MUNCHEN GmbH 18 Sept 1973 [27 Sept 1972] 43847/73 Heading F1C A device for bleeding off compressor air in a gas turbine jet propulsion engine comprising a plurality of mechanically independent compressors, comprises an internal ring 20 provided with a first annular chamber 19 supplied with compressor air, the ring 20 being movable in axial and circumferential direction to expose openings of an external ring 22, thus permitting the air to flow into a second annular chamber 23 located outside the ring 22 and communicating with a by-pass duct 12 of the engine or with atmosphere, e.g. via hollow struts 16. As shown by arrows K, the air is bled from between the I.P. compressor 2 and the H.P. compressor 3. The ring 20 has inclined or helical guide slots 33 co-operating with guide rollers 34 mounted via eccentric adjustment pins 35 on the ring 22. Movement of ring 20 is effected by means of an actuating shaft 28 via levers 29, 30. Seals 25, 26, 27 and spherical bearings 31, 32 are provided.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE2247400A DE2247400C2 (en) | 1972-09-27 | 1972-09-27 | Device for blowing off compressed air from a compressor of a gas turbine jet engine |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1445415A true GB1445415A (en) | 1976-08-11 |
Family
ID=5857538
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB4384773A Expired GB1445415A (en) | 1972-09-27 | 1973-09-18 | Compressor bleed-off device for gas turbine jet engines |
Country Status (5)
Country | Link |
---|---|
US (1) | US3898799A (en) |
DE (1) | DE2247400C2 (en) |
FR (1) | FR2209044B1 (en) |
GB (1) | GB1445415A (en) |
IT (1) | IT993227B (en) |
Families Citing this family (27)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4055946A (en) * | 1976-03-29 | 1977-11-01 | United Technologies Corporation | Twin-spool gas turbine power plant with means to spill compressor interstage airflow |
US4086761A (en) * | 1976-04-26 | 1978-05-02 | The Boeing Company | Stator bypass system for turbofan engine |
DE2740904A1 (en) * | 1977-09-10 | 1979-03-22 | Motoren Turbinen Union | DEVICE FOR OPERATING SHUT-OFF ELEMENTS IN GAS TURBINE ENGINES, IN PARTICULAR GAS TURBINE JET |
US4232513A (en) * | 1977-10-19 | 1980-11-11 | Rolls-Royce Limited | Pressure relief panel for aircraft powerplant |
IL59497A (en) * | 1979-04-23 | 1984-08-31 | Gen Electric | Valve actuation system for use on a gas turbine engine |
US4463552A (en) * | 1981-12-14 | 1984-08-07 | United Technologies Corporation | Combined surge bleed and dust removal system for a fan-jet engine |
US5136840A (en) * | 1982-09-30 | 1992-08-11 | General Electric Company | Gas turbine engine actuation system |
US4546605A (en) * | 1983-12-16 | 1985-10-15 | United Technologies Corporation | Heat exchange system |
US4698964A (en) * | 1985-09-06 | 1987-10-13 | The Boeing Company | Automatic deflector for a jet engine bleed air exhaust system |
US4827713A (en) * | 1987-06-29 | 1989-05-09 | United Technologies Corporation | Stator valve assembly for a rotary machine |
FR2640685B1 (en) * | 1988-12-15 | 1991-02-08 | Snecma | TURBOREACTOR COMPRESSOR DISCHARGE VALVE |
US5177914A (en) * | 1989-06-19 | 1993-01-12 | Hilmer Elwyn P | Vertical section building construction |
US5231825A (en) * | 1990-04-09 | 1993-08-03 | General Electric Company | Method for compressor air extraction |
CA2048829C (en) * | 1990-11-19 | 2001-12-18 | William Francis Mcgreehan | High pressure compressor flowpath bleed valve extraction slot |
US5209633A (en) * | 1990-11-19 | 1993-05-11 | General Electric Company | High pressure compressor flowpath bleed valve extraction slot |
US5287697A (en) * | 1992-01-02 | 1994-02-22 | General Electric Company | Variable area bypass injector seal |
US5211003A (en) * | 1992-02-05 | 1993-05-18 | General Electric Company | Diffuser clean air bleed assembly |
GB2264984A (en) * | 1992-03-12 | 1993-09-15 | Bmw Rolls Royce Gmbh | A device for adjusting gas turbine guide vanes. |
US5380151A (en) * | 1993-10-13 | 1995-01-10 | Pratt & Whitney Canada, Inc. | Axially opening cylindrical bleed valve |
US5477673A (en) * | 1994-08-10 | 1995-12-26 | Pratt & Whitney Canada Inc. | Handling bleed valve |
US6048171A (en) * | 1997-09-09 | 2000-04-11 | United Technologies Corporation | Bleed valve system |
EP0936357B1 (en) * | 1998-02-13 | 2003-11-05 | Pratt & Whitney Canada Corp. | Gas turbine engine |
US6122905A (en) * | 1998-02-13 | 2000-09-26 | Pratt & Whitney Canada Corp. | Compressor bleed valve |
DE19907907A1 (en) * | 1999-02-24 | 2000-08-31 | Abb Alstom Power Ch Ag | Multi-stage turbo compressor |
US6742324B2 (en) * | 2002-09-13 | 2004-06-01 | General Electric Company | Methods and apparatus for supporting variable bypass valve systems |
US8388313B2 (en) * | 2009-11-05 | 2013-03-05 | General Electric Company | Extraction cavity wing seal |
US20130170966A1 (en) * | 2012-01-04 | 2013-07-04 | General Electric Company | Turbine cooling system |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3030006A (en) * | 1958-05-27 | 1962-04-17 | United Aircraft Corp | Circumferential bleed valve |
US3057541A (en) * | 1958-06-03 | 1962-10-09 | United Aircraft Corp | Circumferential bleed valve |
US3094270A (en) * | 1958-08-05 | 1963-06-18 | Rolls Royce | Annular valve device |
NL251063A (en) * | 1959-04-30 | 1900-01-01 | ||
US3688504A (en) * | 1970-11-27 | 1972-09-05 | Gen Electric | Bypass valve control |
GB1365491A (en) * | 1971-01-02 | 1974-09-04 | Dowty Rotol Ltd | Gas turbine ducted fan engines and fans therefor |
US3777489A (en) * | 1972-06-01 | 1973-12-11 | Gen Electric | Combustor casing and concentric air bleed structure |
-
1972
- 1972-09-27 DE DE2247400A patent/DE2247400C2/en not_active Expired
-
1973
- 1973-09-12 IT IT28845/73A patent/IT993227B/en active
- 1973-09-18 GB GB4384773A patent/GB1445415A/en not_active Expired
- 1973-09-27 US US401544A patent/US3898799A/en not_active Expired - Lifetime
- 1973-09-27 FR FR7334718A patent/FR2209044B1/fr not_active Expired
Also Published As
Publication number | Publication date |
---|---|
DE2247400C2 (en) | 1975-01-16 |
IT993227B (en) | 1975-09-30 |
US3898799A (en) | 1975-08-12 |
DE2247400B1 (en) | 1974-05-16 |
FR2209044B1 (en) | 1980-11-07 |
FR2209044A1 (en) | 1974-06-28 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1445415A (en) | Compressor bleed-off device for gas turbine jet engines | |
US3869221A (en) | Rotor wheel fan blade adjusting apparatus for turbojet engines and the like | |
GB1135129A (en) | Gas turbine engine | |
GB1281786A (en) | Turbine nozzles | |
GB1535681A (en) | Turbofan engine nacelle | |
GB1179797A (en) | Improvements in Gas Turbine Engines | |
GB958842A (en) | Ducted fan lift engine | |
US3434288A (en) | By-pass gas turbine engine | |
GB803137A (en) | Improvements in or relating to axial-flow fluid machines for example turbines and compressors of gas-turbine engines | |
GB2063366A (en) | Turbocharger and adaptions thereof | |
GB737473A (en) | Turbines and like machines having adjustable guide blades | |
GB585331A (en) | Improvements in or relating to internal-combustion turbines | |
GB981857A (en) | Gas turbine engine | |
GB737472A (en) | Turbines and like machines having adjustable guide blades | |
GB965465A (en) | Improvements relating to compressor thrust bearings | |
GB911160A (en) | Improvements in or relating to engines having gas compressors | |
GB736017A (en) | Improvements in or relating to gas turbine engines | |
GB744920A (en) | Improvements in or relating to gas turbine engines | |
GB803860A (en) | Improvements in or relating to gas turbine engines | |
GB1479408A (en) | Gas turbine engine | |
GB1218356A (en) | Improvements in or relating to scanning devices | |
GB951298A (en) | Improvements relating to gas turbine engines | |
US3309151A (en) | Gas bearing | |
GB1364458A (en) | Fluid flow compressors | |
GB1324240A (en) | Turbines |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PCNP | Patent ceased through non-payment of renewal fee |