GB1345835A - Air intake devices for fans or compressors - Google Patents
Air intake devices for fans or compressorsInfo
- Publication number
- GB1345835A GB1345835A GB2567172A GB2567172A GB1345835A GB 1345835 A GB1345835 A GB 1345835A GB 2567172 A GB2567172 A GB 2567172A GB 2567172 A GB2567172 A GB 2567172A GB 1345835 A GB1345835 A GB 1345835A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- trailing edge
- leading
- membrane
- compressors
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/148—Blades with variable camber, e.g. by ejection of fluid
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1345835 Axial flow fans and compressors; gas turbine plant SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 1 June 1972 [3 June 1971] 25671/72 Headings F1C F1G and FIT [Also in Division F2] A fan or compressor intake comprises a series of blades whose flanks are constituted by elastic walls deformable under the action of an inflatable body so as to create between adjacent blades a sonic throat acting to attenuate noise propagating upstream. The blades may constitute fixed inlet guides (7) to the compressor or fan (1) of a gas turbine aircraft engine Figs.1, 9 (not shown). Each blade 8 may comprise, Fig.6, an elastic membrane 13 which is maintained in contact with metal leading and trailing edge portions 9, 10a by bars 11, 12 respectively which support a nose cone (3) at their inner ends. When silencing is required a valve (17) is opened to supply compressed air to inflate internal bladder 14, thus causing the flanks of membrane 13 to deform to the dotted profile 18a, 19a defining a sonic throat between adjacent blades 8. Each trailing edge portion 10a may include a passage 23 supplying a stream of air 25 through slot 24 to reduce wake noise. In a modification, Fig.7, leading and trailing edge portions 9b, 10b are connected by a rigid web 26 and membrane 13 is replaced by two membranes 28, 29 each provided with two beads 30 retained in grooves 27 by bars 31, 32. Three pairs 33, 34, 35 of bladders are provided each of which can be independently supplied with compressed air to permit differential inflation. In a further modification, Fig.8 (not shown) only one pair of bladders is provided but the membranes (28a, 29a) have a thickness which varies from the leading to the trailing edge. A relief valve (37) controls bladder inflation pressure. The blades 8 may or may not have a diffusing function The intake may include boundary layer suction devices.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR7120104A FR2139741B1 (en) | 1971-06-03 | 1971-06-03 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1345835A true GB1345835A (en) | 1974-02-06 |
Family
ID=9078043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2567172A Expired GB1345835A (en) | 1971-06-03 | 1972-06-01 | Air intake devices for fans or compressors |
Country Status (2)
| Country | Link |
|---|---|
| FR (1) | FR2139741B1 (en) |
| GB (1) | GB1345835A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2235733A (en) * | 1989-09-07 | 1991-03-13 | Gen Electric | Damper assembly for a jet engine strut |
| GB2397855A (en) * | 2003-01-30 | 2004-08-04 | Rolls Royce Plc | Damping vibrations in turbomachine aerofoils |
| WO2005056984A1 (en) * | 2003-12-06 | 2005-06-23 | Eads Deutschland Gmbh | Method for reducing the noise of turbo generators by modifying the surface circulation of a stator |
| EP1574668A2 (en) * | 2004-03-10 | 2005-09-14 | General Electric Company | Bifurcated outlet guide vanes |
| DE102007002518B3 (en) * | 2007-01-17 | 2008-07-31 | Air Fertigung-Technologie Gmbh & Co.Kg | Vane for e.g. water turbine, of ship machine, has blowing medium formed between cover and carrying structure, where measures are met to enable transfer of blowing medium from side of vane blade to other side of blade |
| EP1898055A3 (en) * | 2006-09-01 | 2011-06-15 | United Technologies Corporation | Variable geometry guide vane for a gas turbine engine |
| EP2383442A3 (en) * | 2010-04-30 | 2014-04-02 | Rolls-Royce plc | Gas turbine engine |
| CN113518704A (en) * | 2019-02-27 | 2021-10-19 | 赛峰飞机发动机公司 | Assembly of outlet guide blades for aircraft turbines using inflatable bladders |
| CN113863991A (en) * | 2021-10-20 | 2021-12-31 | 中国航发沈阳黎明航空发动机有限责任公司 | Active control flexible surface blade with high pneumatic efficiency |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4820117A (en) * | 1987-07-09 | 1989-04-11 | United Technologies Corporation | Crossed I-beam structural strut |
| FR2696210B1 (en) * | 1992-09-25 | 1994-10-28 | Turbomeca | System for adjusting the air supply conditions of a turbomachine, centrifugal compressor comprising an adjustment system and auxiliary power unit comprising such a compressor. |
| US10280759B2 (en) * | 2016-05-25 | 2019-05-07 | United Technologies Corporation | Mechanically retained fan blade cover |
| US11379629B2 (en) | 2020-02-21 | 2022-07-05 | Raytheon Technologies Corporation | System and process for designing internal components for a gas turbine engine |
-
1971
- 1971-06-03 FR FR7120104A patent/FR2139741B1/fr not_active Expired
-
1972
- 1972-06-01 GB GB2567172A patent/GB1345835A/en not_active Expired
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5056738A (en) * | 1989-09-07 | 1991-10-15 | General Electric Company | Damper assembly for a strut in a jet propulsion engine |
| GB2235733A (en) * | 1989-09-07 | 1991-03-13 | Gen Electric | Damper assembly for a jet engine strut |
| GB2397855A (en) * | 2003-01-30 | 2004-08-04 | Rolls Royce Plc | Damping vibrations in turbomachine aerofoils |
| GB2397855B (en) * | 2003-01-30 | 2006-04-05 | Rolls Royce Plc | A turbomachine aerofoil |
| US7025568B2 (en) | 2003-01-30 | 2006-04-11 | Rolls-Royce Plc | Turbomachine aerofoil |
| US7758296B2 (en) | 2003-12-06 | 2010-07-20 | Eads Deutschland Gmbh | Method for reducing the noise of turbo engines |
| WO2005056984A1 (en) * | 2003-12-06 | 2005-06-23 | Eads Deutschland Gmbh | Method for reducing the noise of turbo generators by modifying the surface circulation of a stator |
| EP1574668A2 (en) * | 2004-03-10 | 2005-09-14 | General Electric Company | Bifurcated outlet guide vanes |
| EP1574668A3 (en) * | 2004-03-10 | 2012-12-12 | General Electric Company | Bifurcated outlet guide vanes |
| EP1898055A3 (en) * | 2006-09-01 | 2011-06-15 | United Technologies Corporation | Variable geometry guide vane for a gas turbine engine |
| DE102007002518B3 (en) * | 2007-01-17 | 2008-07-31 | Air Fertigung-Technologie Gmbh & Co.Kg | Vane for e.g. water turbine, of ship machine, has blowing medium formed between cover and carrying structure, where measures are met to enable transfer of blowing medium from side of vane blade to other side of blade |
| EP2383442A3 (en) * | 2010-04-30 | 2014-04-02 | Rolls-Royce plc | Gas turbine engine |
| US8870530B2 (en) | 2010-04-30 | 2014-10-28 | Rolls-Royce Plc | Gas turbine engine |
| CN113518704A (en) * | 2019-02-27 | 2021-10-19 | 赛峰飞机发动机公司 | Assembly of outlet guide blades for aircraft turbines using inflatable bladders |
| CN113518704B (en) * | 2019-02-27 | 2023-11-24 | 赛峰飞机发动机公司 | Assembly of outlet guide vanes for an aircraft turbine using an inflatable bladder |
| CN113863991A (en) * | 2021-10-20 | 2021-12-31 | 中国航发沈阳黎明航空发动机有限责任公司 | Active control flexible surface blade with high pneumatic efficiency |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2139741B1 (en) | 1975-01-17 |
| FR2139741A1 (en) | 1973-01-12 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PCNP | Patent ceased through non-payment of renewal fee |