US20130115083A1 - Turbine engine having two unducted propellers - Google Patents

Turbine engine having two unducted propellers Download PDF

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Publication number
US20130115083A1
US20130115083A1 US13/810,833 US201113810833A US2013115083A1 US 20130115083 A1 US20130115083 A1 US 20130115083A1 US 201113810833 A US201113810833 A US 201113810833A US 2013115083 A1 US2013115083 A1 US 2013115083A1
Authority
US
United States
Prior art keywords
blades
fan
blade
turbine engine
downstream
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.)
Abandoned
Application number
US13/810,833
Other languages
English (en)
Inventor
Gaston Vuillemin Alexandre Alfred
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Assigned to SNECMA reassignment SNECMA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: VUILLEMIN, ALEXANDRE ALFRED GASTON
Publication of US20130115083A1 publication Critical patent/US20130115083A1/en
Abandoned legal-status Critical Current

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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
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/024—Multi-stage pumps with contrarotating parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/003—Variable-diameter propellers; Mechanisms therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/04—Blade mountings
    • B64C11/06—Blade mountings for variable-pitch blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/306—Blade pitch-changing mechanisms specially adapted for contrarotating propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B64C11/48—Units of two or more coaxial propellers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F04D29/36—Blade mountings adjustable
    • F04D29/362—Blade mountings adjustable during rotation
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
    • 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

Definitions

  • the present invention relates to the field of aircraft turbine engines having two unducted propellers or fans.
  • the two fans extend substantially radially on the outside of the nacelle of the turbine engine and are themselves coaxial and contra-rotating.
  • the two fans are driven either directly, in which case the two fans are mounted at the periphery of the two turbine rotors, or via a mechanical gearbox, the two fans then each being connected to one output of the gearbox.
  • Unducted fan turbine engines are being researched at the present time because they offer the advantage of performing well while being capable of supplying significant thrust and consuming less fuel than other equivalent ducted fan turbine engines.
  • One of the sources of this noise stems from the interaction of vortices, generated at the blade tips of the upstream fan, with the blades of the downstream fan.
  • the vortex generated by the upstream fan interacts with the downstream fan very vigorously, generating high levels of noise.
  • One solution for eliminating this noise is to use two fans of different diameters, the outside diameter of the downstream fan being smaller than that of the upstream fan so that the vortices generated by the upstream fan pass around the outside of the envelope of the downstream fan and do not interact with that fan.
  • Such a solution is unsatisfactory because it results in a reduction in the thrust produced by the downstream fan and therefore in reduction in engine performance. It might be possible to increase the load on the downstream fan to compensate for the reduction in diameter thereof, but that would also increase the aeromechanical difficulty in designing the pair of fans which would become very complicated and difficult to achieve.
  • a turbine engine comprising two coaxial and contra-rotating unducted external fans, these respectively being an upstream and a downstream fan, characterized in that the blades of the downstream fan are retractable in their longitudinal direction, so as to reduce the diameter of the downstream fan.
  • said two elements mounted so as to slide one relative to the other are formed at the free end of the blades.
  • said two elements are formed at the root end of the blades.
  • the noise emitted by the turbine engine during a phase of operation of this engine is thus reduced by reducing the length of the blades of the downstream fan during said phase of operation. Said phases of operation correspond to the take-off and landing of the aircraft.
  • the reduction of the blade length is advantageously compensated for by increasing the loading on the blades, notably by varying the blade pitch angle.
  • FIG. 1 is an axial section through a turbine engine with two unducted fans
  • FIG. 2 is a perspective view of an unducted fan of the prior art, illustrating the shape of the stream lines around the fan blades;
  • FIGS. 3 and 4 depict one embodiment of the invention whereby a blade of the downstream fan has a telescopic end, viewed in two positions, one extended and the other retracted.
  • FIG. 1 shows a turbomachine 10 of the “open rotor” type, this expression denoting a pair of unducted fans which comprises, from upstream to downstream, in the direction in which the gases flow inside the turbomachine, a compressor 12 , an annular combustion chamber 14 , a high-pressure upstream turbine 16 and two lower-pressure downstream turbines 18 , 20 which are contra-rotating, which means to say which rotate in two opposite directions about the longitudinal axis A of the turbomachine.
  • Each of these downstream turbines 18 , 20 rotates as one with an external fan 22 , 24 extending radially on the outside of the nacelle 26 of the turbomachine.
  • the nacelle is a substantially cylindrical envelope extending along the axis A around the compressor 12 , the combustion chamber 14 and the turbines 16 , 18 and 20 .
  • the flow of air 28 entering the compressor 12 is compressed and then mixed with fuel and burnt in the combustion chamber 14 .
  • the combustion gases are then injected into the turbines to drive the rotation of the fans 22 , 24 which supply most of the thrust generated by the turbomachine.
  • the combustion gases exit the turbines and are expelled through a jet pipe 30 (arrows 32 ) to increase the thrust.
  • each of these fans 22 , 24 is coaxial and arranged one behind the other.
  • each of these fans 22 , 24 comprises a plurality of blades 22 a and 24 a respectively, which are uniformly distributed about the axis A of the turbomachine.
  • Each blade extends substantially radially in a plane perpendicular to the axis of rotation and comprises an upstream edge forming the leading edge of the blade, a downstream edge forming the trailing edge, a radially internal end forming the root of the blade and a radially external end forming the tip of the blade.
  • the downstream fan 24 has substantially the same diameter as the upstream fan 22 so that these fans supply the same thrust during operation and so that all of the flow of air compressed by the upstream fan is compressed again by the downstream fan.
  • FIG. 2 is a partial and perspective schematic view of the upstream fan 22 of a turbomachine of the prior art, and shows how the stream lines evolve along a blade of this fan.
  • the stream lines 34 , 36 , 38 pass between the fan blades and more or less follow the profile of these blades, from the leading edges 40 to the trailing edges 42 of these blades.
  • the stream lines 34 which pass over the radially internal end parts of the blades are more or less parallel to one another.
  • the stream lines 36 , 38 that pass over the radially external end parts have a tendency to converge toward one another, the intensity of this phenomenon increasing with increasing closeness to the blade tips 44 .
  • the stream lines 36 at the blade tips 20 curl around one another and form vortices 46 which impinge on the blades of the downstream fan 24 , these impingements being what causes very significant acoustic disturbance.
  • FIGS. 3 and 4 depict one embodiment of the invention.
  • the invariable-geometry blades 24 a of the downstream fan are replaced by variable-length blades 124 a.
  • the blade 124 a is telescopic with two elements 124 a 1 and 123 a 2 sliding one inside the other along the longitudinal axis XX of the blade 124 .
  • the element 124 a 1 constitutes the main body of the blade and extends radially outward from the nacelle 26 starting from the blade root.
  • the blade root comprises a pivot 124 b mounted such as to rotate in a bearing of radial axis so as to allow the blade to be rotated about its longitudinal axis XX and the pitch angle of the blade to be altered as required.
  • the bearings for the blades of the fan are mounted in an annular cage 124 c.
  • the annular cage 124 c is driven by the turbine rotor set in rotation by the combustion gases.
  • a set up example is described in patent application FR 0 954 561 or FR 0 955 516 in the name of Snecma.
  • the distal end of the element 124 a 1 is hollow and forms a housing for the blade tip element 124 a 2 in which housing this element can slide between a deployed position shown in FIG. 3 , in which the overall length of the blade is at its maximum, and a retracted position shown in FIG. 4 .
  • An appropriate drive mechanism causes the end element 124 a 2 to move between the two positions, deployed and retracted.
  • An example of a drive mechanism 125 is a screw jack.
  • the latter comprises a threaded rod 125 a rotating on itself about the longitudinal axis of the blade element 124 a 1 and engaging with a threaded housing secured to the end element 124 a 2 .
  • the threaded rod is driven by a motor 125 b housed inside the nacelle 26 . Given that the tip element 124 a 2 slides inside the element 124 a 1 without rotating about the longitudinal axis of the blade, rotation of the threaded rod causes this element to move longitudinally.
  • the two possible configurations of the downstream fan thus allow either optimum-output operation or noise attenuation.
  • the diameter of the fan is reduced.
  • the stream lines run along the blade tip and give rise to blade tip vortices on the upstream fan but these vortices are prevented from impinging on the downstream noise and from being a source of noise.
  • the reduction in length of the blades is compensated for by increasing the load on these blades, notably by varying the blade pitch angle.
  • the two fans are deployed; in particular, the blades of the downstream fan extend in a radial direction with respect to the axis of the engine to substantially the same length as the blades of the upstream fan. It is on take-off or on landing that the retracted position of the blades of the downstream fan is activated, and that represents just 10% of the mission in general.
  • Mechanisms other than screw jacks allow the blades of the downstream fan to be retracted longitudinally.
  • the invention is not restricted to this mode of actuation.
  • other ways of modifying the geometry of the blades are equally possible.
  • the blades may be capable of moving radially inside a housing in the nacelle, the telescopic elements being not at the blade tip end but at the root end.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
US13/810,833 2010-07-23 2011-07-13 Turbine engine having two unducted propellers Abandoned US20130115083A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1056059A FR2963067B1 (fr) 2010-07-23 2010-07-23 Turbomoteur a double helice non carenee
FR1056059 2010-07-23
PCT/FR2011/051690 WO2012010782A1 (fr) 2010-07-23 2011-07-13 Turbomoteur a double helice non carenee

Publications (1)

Publication Number Publication Date
US20130115083A1 true US20130115083A1 (en) 2013-05-09

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Application Number Title Priority Date Filing Date
US13/810,833 Abandoned US20130115083A1 (en) 2010-07-23 2011-07-13 Turbine engine having two unducted propellers

Country Status (8)

Country Link
US (1) US20130115083A1 (de)
EP (1) EP2596247B1 (de)
CN (1) CN103003573A (de)
BR (1) BR112013001333A2 (de)
CA (1) CA2805757A1 (de)
FR (1) FR2963067B1 (de)
RU (1) RU2013102502A (de)
WO (1) WO2012010782A1 (de)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2018501142A (ja) * 2014-12-17 2018-01-18 サフラン・エアクラフト・エンジンズ 複数の直径プロペラを備えたターボ機械
US20180093754A1 (en) * 2016-09-30 2018-04-05 General Electric Company Translating fan blades for an aircraft tail mounted fan assembly
WO2018125622A1 (en) * 2016-12-30 2018-07-05 X Development Llc Rotor units having asymmetric rotor blades
US10137982B1 (en) 2014-05-11 2018-11-27 Wing Aviation Llc Propeller units
US10414486B2 (en) 2015-11-30 2019-09-17 General Electric Company Airfoil for a rotary machine including a propellor assembly
US10640198B2 (en) * 2016-04-28 2020-05-05 Airbus Operations Sas Propeller for an aircraft turbo engine, including safety means for controlling blade angle of attack
US11286795B2 (en) 2019-10-15 2022-03-29 General Electric Company Mount for an airfoil
US11401824B2 (en) 2019-10-15 2022-08-02 General Electric Company Gas turbine engine outlet guide vane assembly
US11506067B2 (en) 2019-10-15 2022-11-22 General Electric Company Gas turbine engine with clutch assembly
US11814174B2 (en) 2019-10-15 2023-11-14 General Electric Company Layered fuselage shield
US11834196B2 (en) 2019-10-15 2023-12-05 General Electric Company System and method for control for unducted engine
US12215596B2 (en) 2023-06-30 2025-02-04 General Electric Company Unducted airfoil assembly
US12275532B2 (en) 2022-08-15 2025-04-15 General Electric Company Gas turbine engine noise reduction
US12352181B2 (en) 2023-01-30 2025-07-08 General Electric Company Turbine airfoils
US12410758B2 (en) 2022-01-10 2025-09-09 General Electric Company Three-stream gas turbine engine control
US12466544B1 (en) * 2024-05-10 2025-11-11 Rtx Corporation SRV open rotor with core inlet forward of rotor
US12480449B2 (en) 2022-08-22 2025-11-25 General Electric Company Propulsion system including an electric machine for starting a gas turbine engine
US12624645B2 (en) 2023-04-18 2026-05-12 General Electric Company Active clearance control assembly

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UA81006U (ru) * 2013-04-22 2013-06-10 Юрий Григорьевич Сидоренко Система повышения эффективности и управляемости авиационного движителя
CN107905883A (zh) * 2018-01-12 2018-04-13 浙江元盛塑业股份有限公司 一种硅油风扇离合器
CN107975495A (zh) * 2018-01-12 2018-05-01 浙江元盛塑业股份有限公司 一种硅油风扇叶片
CN108087095A (zh) * 2018-01-12 2018-05-29 浙江元盛塑业股份有限公司 硅油风扇离合器
FR3125090B1 (fr) 2021-07-06 2024-03-29 Safran Aircraft Engines Propulseur aeronautique
FR3125089B1 (fr) * 2021-07-06 2024-07-19 Safran Aircraft Engines Propulseur aeronautique
FR3125091B1 (fr) * 2021-07-06 2024-06-28 Safran Aircraft Engines Propulseur aeronautique
CN116044809B (zh) * 2023-01-03 2025-11-18 潍柴动力股份有限公司 一种直径可变的发动机冷却风扇及发动机

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US3811791A (en) * 1971-08-12 1974-05-21 R Cotton Thrust augmenting device for jet aircraft
US4976102A (en) * 1988-05-09 1990-12-11 General Electric Company Unducted, counterrotating gearless front fan engine
US5190441A (en) * 1990-08-13 1993-03-02 General Electric Company Noise reduction in aircraft propellers
US8382430B2 (en) * 2007-02-10 2013-02-26 Rolls-Royce Plc Aeroengine
US8821118B2 (en) * 2009-12-21 2014-09-02 The Boeing Company Optimization of downstream open fan propeller position

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FR2938502B1 (fr) * 2008-11-14 2010-12-10 Snecma Turbomachine comportant une helice non carenee equipee de moyens de guidage d'air
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Publication number Priority date Publication date Assignee Title
US3128829A (en) * 1964-04-14 Variable diameter propeller
US3811791A (en) * 1971-08-12 1974-05-21 R Cotton Thrust augmenting device for jet aircraft
US4976102A (en) * 1988-05-09 1990-12-11 General Electric Company Unducted, counterrotating gearless front fan engine
US5190441A (en) * 1990-08-13 1993-03-02 General Electric Company Noise reduction in aircraft propellers
US8382430B2 (en) * 2007-02-10 2013-02-26 Rolls-Royce Plc Aeroengine
US8821118B2 (en) * 2009-12-21 2014-09-02 The Boeing Company Optimization of downstream open fan propeller position

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10137982B1 (en) 2014-05-11 2018-11-27 Wing Aviation Llc Propeller units
US11066156B2 (en) 2014-05-11 2021-07-20 Wing Aviation Llc Propeller units
JP2018501142A (ja) * 2014-12-17 2018-01-18 サフラン・エアクラフト・エンジンズ 複数の直径プロペラを備えたターボ機械
US10494086B2 (en) 2014-12-17 2019-12-03 Safran Aircraft Engines Turbomachine with multi-diameter propeller
US10414486B2 (en) 2015-11-30 2019-09-17 General Electric Company Airfoil for a rotary machine including a propellor assembly
US11136109B2 (en) 2015-11-30 2021-10-05 General Electric Company Airfoil for a rotary machine including a propellor assembly
US10640198B2 (en) * 2016-04-28 2020-05-05 Airbus Operations Sas Propeller for an aircraft turbo engine, including safety means for controlling blade angle of attack
US20180093754A1 (en) * 2016-09-30 2018-04-05 General Electric Company Translating fan blades for an aircraft tail mounted fan assembly
US10814959B2 (en) * 2016-09-30 2020-10-27 General Electric Company Translating fan blades for an aircraft tail mounted fan assembly
WO2018125622A1 (en) * 2016-12-30 2018-07-05 X Development Llc Rotor units having asymmetric rotor blades
US10604245B2 (en) 2016-12-30 2020-03-31 Wing Aviation Llc Rotor units having asymmetric rotor blades
US11059576B2 (en) 2016-12-30 2021-07-13 Wing Aviation Llc Rotor units having asymmetric rotor blades
US11506067B2 (en) 2019-10-15 2022-11-22 General Electric Company Gas turbine engine with clutch assembly
US12320315B2 (en) 2019-10-15 2025-06-03 General Electric Company Unducted single rotor engine and method for operation
US11286795B2 (en) 2019-10-15 2022-03-29 General Electric Company Mount for an airfoil
US11814174B2 (en) 2019-10-15 2023-11-14 General Electric Company Layered fuselage shield
US11834196B2 (en) 2019-10-15 2023-12-05 General Electric Company System and method for control for unducted engine
US20230415914A1 (en) * 2019-10-15 2023-12-28 General Electric Company Advance ratio for single unducted rotor engine
US12103702B2 (en) 2019-10-15 2024-10-01 General Electric Company Removeable fuselage shield for an aircraft
US11401824B2 (en) 2019-10-15 2022-08-02 General Electric Company Gas turbine engine outlet guide vane assembly
US12410758B2 (en) 2022-01-10 2025-09-09 General Electric Company Three-stream gas turbine engine control
US12275532B2 (en) 2022-08-15 2025-04-15 General Electric Company Gas turbine engine noise reduction
US12480449B2 (en) 2022-08-22 2025-11-25 General Electric Company Propulsion system including an electric machine for starting a gas turbine engine
US12352181B2 (en) 2023-01-30 2025-07-08 General Electric Company Turbine airfoils
US12624645B2 (en) 2023-04-18 2026-05-12 General Electric Company Active clearance control assembly
US12215596B2 (en) 2023-06-30 2025-02-04 General Electric Company Unducted airfoil assembly
US12560088B2 (en) 2023-06-30 2026-02-24 General Electric Company Unducted airfoil assembly
US12466544B1 (en) * 2024-05-10 2025-11-11 Rtx Corporation SRV open rotor with core inlet forward of rotor
US20250346345A1 (en) * 2024-05-10 2025-11-13 Rtx Corporation Srv open rotor with core inlet forward of rotor

Also Published As

Publication number Publication date
WO2012010782A1 (fr) 2012-01-26
BR112013001333A2 (pt) 2016-05-17
CN103003573A (zh) 2013-03-27
EP2596247A1 (de) 2013-05-29
FR2963067B1 (fr) 2012-08-24
CA2805757A1 (fr) 2012-01-26
RU2013102502A (ru) 2014-08-27
EP2596247B1 (de) 2015-09-02
FR2963067A1 (fr) 2012-01-27

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