US3684857A - Air intakes - Google Patents

Air intakes Download PDF

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Publication number
US3684857A
US3684857A US110973A US3684857DA US3684857A US 3684857 A US3684857 A US 3684857A US 110973 A US110973 A US 110973A US 3684857D A US3684857D A US 3684857DA US 3684857 A US3684857 A US 3684857A
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US
United States
Prior art keywords
air
air intake
outer casing
engine
leading edge
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
US110973A
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English (en)
Inventor
Frederick William Walto Morley
George Henry Bennett
Richard George Harvey
Alan Wilson
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of US3684857A publication Critical patent/US3684857A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles

Definitions

  • ABSTRACT A gas turbine engine air intake designed to prevent ingestion into the engine of a substantial proportion of [21] Appl' 110373 any ice or slush present in the incoming air.
  • the air in- 7 take comprises a central bullet and an outer casing 30 F i li i priority Data defining an annular passage therebetween through a which air flows to the engine compressor.
  • the central Feb. 5, Great Blltaln bullet is enlarged at upstream end to a mushroom shape whose outer periphery lies upstream of and is at 1.8- CI.
  • the present invention relates to an improved construction of air intake for a gas turbine powerplant wherein a substantial proportion of any ice or slush present in the air is not ingested.
  • an air intake for a gas turbine engine comprising an outer casing having a leading edge, a central bullet having an upstream end portion which is enlarged, an annular passage defined between said central bullet and said outer casing and adapted to receive a flow therethrough of air in a determined direction, said enlarged portion having an outer periphery which is forward of the leading edge of the outer casing and every point on which lies a greater distance from the central axis of the intake than its corresponding point in the same axial plane on the leading edge of the outer casmg.
  • the enlarged portion of the nose bullet is of circular cross-section and its upstream surface is convex so as to form a dome.
  • the words upstream and downstream in this context refer to the direction in which the air flows through the intake.
  • Means are preferably provided for heating the surfaces of the intake which are exposed to the air flow.
  • FIG. 1 is a part sectional side elevation of a gas turbine engine fitted with an air intake designed according to the invention.
  • FIG. 2 is a longitudinal section of an air intake according to the invention.
  • the gas turbine engine 1 in FIG. 1 includes compressor system 2, a combustion system 3 and a turbine system 4 all in flow series as shown and surrounded by an engine cowl 25.
  • An air intake is attached to the compressor system and profiled to blend with the engine cowl.
  • the air intake 11 comprises a central bullet 12 and an outer casing 13 havinginner and outer walls, 14 and 15 respectively, meeting at the leading edge of the outer casing which throughout the specification should be taken as the most upstream point 16 of the casing.
  • the outer casing is supported 7 from the central bullet by struts 17 to define an annular passage 18 therebetween.
  • the direction of. air entering the air intake is indicated by arrows 19.
  • the central bullet 12 is enlarged at its upstream end into a shape, which will hereinafter be referred to as the mushroom 21, which is of circular cross-section and of which the upstream surface is convex to form a dome.
  • the outer periphery 22 of the mushroom 21 lies upstream of the leading edge 16 of the outer casing 13 and every point on the outer periphery 22 lies at a greater distance from the central axis 23 of the air intake than its corresponding point in the same axial plane on the leading edge 16 of the outer casing.
  • the surfaces are heated by electric resistance coils 26 placed on the surfaces and held in position by a matting 27.
  • the matting 27 which may be of rubber or plastics material is bonded to the air intake surfaces.
  • the air intake shown in this example is for a gas turbine powerplant mounted on top of the fuselage of a helicopter and is of particular advantage where ice and slush formed on top of the fuselage forward of the powerplant breaks away and is urged towards the air intake. If two powerplants each fitted with this air intake are mounted side by side a gutter could be formed between the powerplants to facilitate the easy removal of ice and slush deflected by the mushrooms to the space between them.
  • an air intake constructed according to the invention would in operation also remove a substantial proportion .of other particulate matter, for example sand, from the incoming air.
  • An air intake for a gas turbine engine comprising an outer casing having a leading edge, a central bullet having an upstream end portion which is enlarged, an annular passage defined between said central bullet and said outer casing and adapted to receive a flow therethrough of air in a determined direction, said enlarged portion having an upstream surface which is convex forming a dome and having an outer periphery which is forward of the leading edge of the outer casing and every point on said periphery lies at a greater distance from the central axis of the intake than its corresponding point in the same axial: plane on the leading edge of the outer casing.
  • heating means comprise electrical resistance coils which are held in position on said surfaces by a matting material which is bonded to said surfaces.

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)
  • Supercharger (AREA)
  • Filtering Of Dispersed Particles In Gases (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
US110973A 1970-02-05 1971-01-29 Air intakes Expired - Lifetime US3684857A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB547670 1970-02-05

Publications (1)

Publication Number Publication Date
US3684857A true US3684857A (en) 1972-08-15

Family

ID=9796916

Family Applications (1)

Application Number Title Priority Date Filing Date
US110973A Expired - Lifetime US3684857A (en) 1970-02-05 1971-01-29 Air intakes

Country Status (4)

Country Link
US (1) US3684857A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE (1) DE2103035C3 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
FR (1) FR2079257B1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
GB (1) GB1328993A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)

Cited By (50)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3103603A1 (de) * 1980-02-09 1982-01-07 Rolls-Royce Ltd., London Lufteinlass fuer ein gasturbinentriebwerk
DE3104005A1 (de) * 1980-02-09 1982-01-14 Rolls-Royce Ltd., London Lufteinlass fuer ein gasturbinentriebwerk
WO2006059987A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Particle separator for tip turbine engine
US20070101696A1 (en) * 2005-11-09 2007-05-10 Pratt & Whitney Canada Corp. Gas turbine engine with power transfer and method
US20080014078A1 (en) * 2004-12-01 2008-01-17 Suciu Gabriel L Ejector Cooling of Outer Case for Tip Turbine Engine
US20080093174A1 (en) * 2004-12-01 2008-04-24 Suciu Gabriel L Tip Turbine Engine with a Heat Exchanger
US20080124211A1 (en) * 2004-12-01 2008-05-29 Suciu Gabriel L Diffuser Aspiration For A Tip Turbine Engine
US20090071162A1 (en) * 2004-12-01 2009-03-19 Suciu Gabriel L Peripheral combustor for tip turbine engine
US20090142184A1 (en) * 2004-12-01 2009-06-04 Roberge Gary D Vectoring transition duct for turbine engine
US20090148273A1 (en) * 2004-12-01 2009-06-11 Suciu Gabriel L Compressor inlet guide vane for tip turbine engine and corresponding control method
US20090145136A1 (en) * 2004-12-01 2009-06-11 Norris James W Tip turbine engine with multiple fan and turbine stages
US20090155079A1 (en) * 2004-12-01 2009-06-18 Suciu Gabriel L Stacked annular components for turbine engines
US20090232650A1 (en) * 2004-12-01 2009-09-17 Gabriel Suciu Tip turbine engine and corresponding operating method
US7607286B2 (en) 2004-12-01 2009-10-27 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
US7631480B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7887296B2 (en) 2004-12-01 2011-02-15 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US7927075B2 (en) 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8061968B2 (en) 2004-12-01 2011-11-22 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US9857017B2 (en) * 2015-10-30 2018-01-02 Akron Brass Company Debris diverting inlet
CN109339948A (zh) * 2018-11-23 2019-02-15 江西洪都航空工业集团有限责任公司 弹用燃气涡轮发动机进气装置
RU218689U1 (ru) * 2023-03-03 2023-06-06 Владимир Викторович Брокерт Устройство защиты газотурбинных двигателей самолёта от птиц
US12326114B2 (en) 2023-08-15 2025-06-10 Rtx Corporation Gas turbine engine with core debris protection

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2791668A (en) * 1951-08-21 1957-05-07 Napier & Son Ltd Electrically heated de-icing or antifreezing apparatus
US3063031A (en) * 1959-12-28 1962-11-06 Gen Motors Corp Electrical aircraft heater
US3534548A (en) * 1969-06-30 1970-10-20 Avco Corp Separator apparatus for engine air inlets

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2791668A (en) * 1951-08-21 1957-05-07 Napier & Son Ltd Electrically heated de-icing or antifreezing apparatus
US3063031A (en) * 1959-12-28 1962-11-06 Gen Motors Corp Electrical aircraft heater
US3534548A (en) * 1969-06-30 1970-10-20 Avco Corp Separator apparatus for engine air inlets

Cited By (72)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3103603A1 (de) * 1980-02-09 1982-01-07 Rolls-Royce Ltd., London Lufteinlass fuer ein gasturbinentriebwerk
DE3104005A1 (de) * 1980-02-09 1982-01-14 Rolls-Royce Ltd., London Lufteinlass fuer ein gasturbinentriebwerk
US4389227A (en) * 1980-02-09 1983-06-21 Rolls-Royce Limited Gas turbine engine air intake
US4493185A (en) * 1980-02-09 1985-01-15 Rolls-Royce Limited Gas turbine engine air intake
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US20080014078A1 (en) * 2004-12-01 2008-01-17 Suciu Gabriel L Ejector Cooling of Outer Case for Tip Turbine Engine
US20080093174A1 (en) * 2004-12-01 2008-04-24 Suciu Gabriel L Tip Turbine Engine with a Heat Exchanger
WO2006059987A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Particle separator for tip turbine engine
US20090071162A1 (en) * 2004-12-01 2009-03-19 Suciu Gabriel L Peripheral combustor for tip turbine engine
US20090142184A1 (en) * 2004-12-01 2009-06-04 Roberge Gary D Vectoring transition duct for turbine engine
US20090148273A1 (en) * 2004-12-01 2009-06-11 Suciu Gabriel L Compressor inlet guide vane for tip turbine engine and corresponding control method
US20090145136A1 (en) * 2004-12-01 2009-06-11 Norris James W Tip turbine engine with multiple fan and turbine stages
US20090155079A1 (en) * 2004-12-01 2009-06-18 Suciu Gabriel L Stacked annular components for turbine engines
US20090232650A1 (en) * 2004-12-01 2009-09-17 Gabriel Suciu Tip turbine engine and corresponding operating method
US7607286B2 (en) 2004-12-01 2009-10-27 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
US7631480B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
US7631485B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Tip turbine engine with a heat exchanger
US10760483B2 (en) 2004-12-01 2020-09-01 Raytheon Technologies Corporation Tip turbine engine composite tailcone
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7887296B2 (en) 2004-12-01 2011-02-15 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7921636B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
US7927075B2 (en) 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US20080124211A1 (en) * 2004-12-01 2008-05-29 Suciu Gabriel L Diffuser Aspiration For A Tip Turbine Engine
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
US20110142601A1 (en) * 2004-12-01 2011-06-16 Suciu Gabriel L Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US20110200424A1 (en) * 2004-12-01 2011-08-18 Gabriel Suciu Counter-rotating gearbox for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8061968B2 (en) 2004-12-01 2011-11-22 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8087885B2 (en) 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8104257B2 (en) 2004-12-01 2012-01-31 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8276362B2 (en) 2004-12-01 2012-10-02 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8468795B2 (en) 2004-12-01 2013-06-25 United Technologies Corporation Diffuser aspiration for a tip turbine engine
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8672630B2 (en) 2004-12-01 2014-03-18 United Technologies Corporation Annular turbine ring rotor
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US8631655B2 (en) 2005-11-09 2014-01-21 Pratt & Whitney Canada Corp. Gas turbine engine including apparatus to transfer power between multiple shafts
US20070101696A1 (en) * 2005-11-09 2007-05-10 Pratt & Whitney Canada Corp. Gas turbine engine with power transfer and method
US20110036093A1 (en) * 2005-11-09 2011-02-17 Pratt & Whitney Canada Corp. Gas turbine engine including apparatus to transfer power between multiple shafts
US7690186B2 (en) * 2005-11-09 2010-04-06 Pratt & Whitney Canada Corp. Gas turbine engine including apparatus to transfer power between multiple shafts
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US9857017B2 (en) * 2015-10-30 2018-01-02 Akron Brass Company Debris diverting inlet
CN109339948A (zh) * 2018-11-23 2019-02-15 江西洪都航空工业集团有限责任公司 弹用燃气涡轮发动机进气装置
RU218689U1 (ru) * 2023-03-03 2023-06-06 Владимир Викторович Брокерт Устройство защиты газотурбинных двигателей самолёта от птиц
US12326114B2 (en) 2023-08-15 2025-06-10 Rtx Corporation Gas turbine engine with core debris protection

Also Published As

Publication number Publication date
GB1328993A (en) 1973-09-05
DE2103035C3 (de) 1975-03-27
FR2079257A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1971-11-12
DE2103035B2 (de) 1974-08-01
FR2079257B1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1975-06-06
DE2103035A1 (de) 1971-08-26

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