GB1310401A - Axial flow compressors - Google Patents
Axial flow compressorsInfo
- Publication number
- GB1310401A GB1310401A GB3069870A GB3069870A GB1310401A GB 1310401 A GB1310401 A GB 1310401A GB 3069870 A GB3069870 A GB 3069870A GB 3069870 A GB3069870 A GB 3069870A GB 1310401 A GB1310401 A GB 1310401A
- Authority
- GB
- United Kingdom
- Prior art keywords
- passageway
- bleed
- compressor
- flow path
- lip
- 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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1310401 Axial-flow compressors; gas turbine engines GENERAL ELECTRIC CO 24 June 1970 [30 Sept 1969] 30698/70 Headings F1C and F1G A multi-stage axial-flow compressor for a gas turbine engine comprises an annular bleed passageway 41 formed in the compressor casing with the outer surface of the bleed passageway forming a continuation of the outer surface of the compressor flow path at the downstream end of a row of stator vanes 38, an annular lip 39 spaced inwardly from the outer ends of the vanes 38 and defining the entrance to the bleed passageway, the lip being relatively sharp and having a small included angle whereby the divergence of the bleed passageway from the compressor flow path is at a relatively small angle, and flow path means 26 extending from the downstream end of the bleed passageway to a point where the bleed air is used, e. g. for cooling purposes or for sealing lubrication sumps. Preferably, the lip 39 and the initial portion of passageway 41 are formed by inserts 43. The passageway 41 acts as a diffuser.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US86219769A | 1969-09-30 | 1969-09-30 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1310401A true GB1310401A (en) | 1973-03-21 |
Family
ID=25337901
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB3069870A Expired GB1310401A (en) | 1969-09-30 | 1970-06-24 | Axial flow compressors |
Country Status (5)
Country | Link |
---|---|
US (1) | US3632223A (en) |
BE (1) | BE752584A (en) |
DE (1) | DE2031612A1 (en) |
FR (1) | FR2060529A5 (en) |
GB (1) | GB1310401A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2192229A (en) * | 1986-07-04 | 1988-01-06 | Rolls Royce Plc | A compressor and air bleed system |
GB2251031A (en) * | 1990-12-19 | 1992-06-24 | Rolls Royce Plc | Cooling air pick up for gas turbine engine |
EP2428648A2 (en) | 2010-09-10 | 2012-03-14 | Rolls-Royce plc | Gas turbine engine |
Families Citing this family (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1291943A (en) * | 1970-02-11 | 1972-10-04 | Secr Defence | Improvements in or relating to ducted fans |
US3826084A (en) * | 1970-04-28 | 1974-07-30 | United Aircraft Corp | Turbine coolant flow system |
GB1342590A (en) * | 1970-07-17 | 1974-01-03 | Secr Defence | Suppression of noise in gas turbine engines |
US3945759A (en) * | 1974-10-29 | 1976-03-23 | General Electric Company | Bleed air manifold |
US3966355A (en) * | 1975-06-24 | 1976-06-29 | Westinghouse Electric Corporation | Steam turbine extraction system |
US3976394A (en) * | 1975-07-18 | 1976-08-24 | The United States Of America As Represented By The Secretary Of The Air Force | Interstage bleed assembly |
US4156344A (en) * | 1976-12-27 | 1979-05-29 | The Boeing Company | Inlet guide vane bleed system |
US4155681A (en) * | 1977-02-14 | 1979-05-22 | General Electric Company | Manifold protection system |
US4512715A (en) * | 1980-07-22 | 1985-04-23 | Electric Power Research Institute, Inc. | Method and means for recapturing coolant in a gas turbine |
US4979587A (en) * | 1989-08-01 | 1990-12-25 | The Boeing Company | Jet engine noise suppressor |
US5160241A (en) * | 1991-09-09 | 1992-11-03 | General Electric Company | Multi-port air channeling assembly |
US5351478A (en) * | 1992-05-29 | 1994-10-04 | General Electric Company | Compressor casing assembly |
US5327716A (en) * | 1992-06-10 | 1994-07-12 | General Electric Company | System and method for tailoring rotor tip bleed air |
DE4326799A1 (en) * | 1993-08-10 | 1995-02-16 | Abb Management Ag | Device for extracting secondary air from an axial compressor |
GB9709086D0 (en) * | 1997-05-07 | 1997-06-25 | Rolls Royce Plc | Gas turbine engine cooling apparatus |
DE69936939T2 (en) * | 1998-02-26 | 2008-05-15 | Allison Advanced Development Co., Indianapolis | ZAPFSYSTEM FOR A COMPRESSOR WALL AND OPERATING PROCESS |
US6109868A (en) * | 1998-12-07 | 2000-08-29 | General Electric Company | Reduced-length high flow interstage air extraction |
FR2823532B1 (en) * | 2001-04-12 | 2003-07-18 | Snecma Moteurs | DISCHARGE SYSTEM FOR A TURBO-JET OR TURBO-PROPELLER WITH SIMPLIFIED CONTROL |
US6438941B1 (en) | 2001-04-26 | 2002-08-27 | General Electric Company | Bifurcated splitter for variable bleed flow |
US20050141991A1 (en) * | 2001-10-17 | 2005-06-30 | Frutschi Hans U. | Method for conditioning a compressor airflow and device therefor |
US6732530B2 (en) * | 2002-05-31 | 2004-05-11 | Mitsubishi Heavy Industries, Ltd. | Gas turbine compressor and clearance controlling method therefor |
JP4893110B2 (en) * | 2006-05-31 | 2012-03-07 | 株式会社Ihi | Axial fluid device |
US8292567B2 (en) * | 2006-09-14 | 2012-10-23 | Caterpillar Inc. | Stator assembly including bleed ports for turbine engine compressor |
US8388308B2 (en) * | 2007-10-30 | 2013-03-05 | General Electric Company | Asymmetric flow extraction system |
US8307943B2 (en) | 2010-07-29 | 2012-11-13 | General Electric Company | High pressure drop muffling system |
US8430202B1 (en) | 2011-12-28 | 2013-04-30 | General Electric Company | Compact high-pressure exhaust muffling devices |
US9399951B2 (en) | 2012-04-17 | 2016-07-26 | General Electric Company | Modular louver system |
US8511096B1 (en) | 2012-04-17 | 2013-08-20 | General Electric Company | High bleed flow muffling system |
US8550208B1 (en) | 2012-04-23 | 2013-10-08 | General Electric Company | High pressure muffling devices |
US20140338360A1 (en) * | 2012-09-21 | 2014-11-20 | United Technologies Corporation | Bleed port ribs for turbomachine case |
US9689315B2 (en) * | 2015-02-13 | 2017-06-27 | Hamilton Sundstrand Corporation | Full-area bleed valves |
US10934943B2 (en) * | 2017-04-27 | 2021-03-02 | General Electric Company | Compressor apparatus with bleed slot and supplemental flange |
US20180313364A1 (en) * | 2017-04-27 | 2018-11-01 | General Electric Company | Compressor apparatus with bleed slot including turning vanes |
US10626879B2 (en) * | 2017-11-13 | 2020-04-21 | United Technologies Corporation | Gas turbine engine with mid-compressor bleed |
US10823069B2 (en) * | 2018-11-09 | 2020-11-03 | Raytheon Technologies Corporation | Internal heat exchanger system to cool gas turbine engine components |
US11828226B2 (en) * | 2022-04-13 | 2023-11-28 | General Electric Company | Compressor bleed air channels having a pattern of vortex generators |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US25253A (en) * | 1859-08-30 | Faucet | ||
US2314058A (en) * | 1941-06-23 | 1943-03-16 | Edward A Stalker | Pump |
US2693904A (en) * | 1950-11-14 | 1954-11-09 | A V Roe Canada Ltd | Air bleed for compressors |
US2738921A (en) * | 1950-11-22 | 1956-03-20 | United Aircraft Corp | Boundary layer control apparatus for compressors |
GB869576A (en) * | 1958-05-15 | 1961-05-31 | Rolls Royce | Improvements in compressors for gas turbine engines |
US3142438A (en) * | 1961-04-21 | 1964-07-28 | Rolls Royce | Multi-stage axial compressor |
-
1969
- 1969-09-30 US US862197A patent/US3632223A/en not_active Expired - Lifetime
-
1970
- 1970-06-23 FR FR7023215A patent/FR2060529A5/fr not_active Expired
- 1970-06-24 GB GB3069870A patent/GB1310401A/en not_active Expired
- 1970-06-26 BE BE752584D patent/BE752584A/en unknown
- 1970-06-26 DE DE19702031612 patent/DE2031612A1/en active Pending
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2192229A (en) * | 1986-07-04 | 1988-01-06 | Rolls Royce Plc | A compressor and air bleed system |
US4844689A (en) * | 1986-07-04 | 1989-07-04 | Rolls-Royce Plc | Compressor and air bleed system |
GB2192229B (en) * | 1986-07-04 | 1990-05-02 | Rolls Royce Plc | A compressor and air bleed system |
GB2251031A (en) * | 1990-12-19 | 1992-06-24 | Rolls Royce Plc | Cooling air pick up for gas turbine engine |
GB2251031B (en) * | 1990-12-19 | 1995-01-18 | Rolls Royce Plc | Cooling air pick up |
EP2428648A2 (en) | 2010-09-10 | 2012-03-14 | Rolls-Royce plc | Gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
DE2031612A1 (en) | 1971-04-15 |
US3632223A (en) | 1972-01-04 |
BE752584A (en) | 1970-12-01 |
FR2060529A5 (en) | 1971-06-18 |
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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 |