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Aircraft propulsion system and aircraft powered by such a propulsion system built into the rear of an aircraft fuselage

A propulsion system and aircraft technology, applied in the field of aircraft, can solve problems such as the robustness of the propulsion system, and achieve the effect of improving robustness and reducing size

Pending Publication Date: 2021-02-12
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, this architecture has problems maintaining a minimum level of thrust (equal to approximately 50% of the nominal total thrust) and the recklessness of the propulsion system in the event of a failure of a part of the propulsion system. Problems with stickiness

Method used

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  • Aircraft propulsion system and aircraft powered by such a propulsion system built into the rear of an aircraft fuselage
  • Aircraft propulsion system and aircraft powered by such a propulsion system built into the rear of an aircraft fuselage
  • Aircraft propulsion system and aircraft powered by such a propulsion system built into the rear of an aircraft fuselage

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Embodiment Construction

[0050] The invention relates to an aircraft powered by a propulsion system integrated into the rear of the aircraft fuselage.

[0051] image 3 Shown is a propulsion system 100 of an aircraft according to the invention comprising two independent gas generators 102a, 102b connected in parallel from upstream to downstream in the direction of air flow indicated by arrow F, the two independent gas The generator supplies the power turbine 104 . A separate air inlet 106a, 106b is arranged to supply each gas generator 102a, 102b. In order to optimize the thermal efficiency of the gas generator, the air inlets 106a, 106b are arranged such that the gas generator 102a, 102b does not ingest the boundary layer.

[0052] Each gas generator 102a, 102b may include at least one compressor (eg, a low pressure compressor and a high pressure compressor), a combustor, and at least one turbine (eg, a low pressure turbine and a high pressure turbine).

[0053] Each gas generator 102a, 102b is ho...

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PUM

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Abstract

The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of theenergy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drivedevice.

Description

technical field [0001] The invention relates to the field of aircraft, such as civil aircraft in particular, powered by a counter-rotating fan propulsion system integrated into the rear of the aircraft fuselage as an extension of the aircraft fuselage. More specifically, the present invention relates to a device integrated into a propulsion system to provide a combination of aerodynamic and electrical energy to the propulsion system. Background technique [0002] The prior art includes inter alia patent applications WO-A1-2016 / 020618, US-A1-2018 / 003071, DE-A1-102013 209538, US-A1-2017 / 320584, US-A1-2018 / 057150 and EP-A2- 2 730 501. [0003] In the applicant's patent application FR-A1-2 997 681, a new aircraft architecture has been proposed that limits aerodynamic drag by absorbing the boundary layer, thereby reducing aircraft noise pollution and fuel consumption . [0004] In such a structure, such as figure 1 As shown, the aircraft 1 is powered by a turbine (in this cas...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/14B64D27/20F02K3/072F02C6/02B64D27/24F01D15/10F02K3/04F02K3/062F02K3/12B64D27/02B64D33/02F01D13/02B64D27/00
CPCB64D27/02B64D27/14B64D27/20B64D27/24B64D33/02B64D2027/005B64D2033/0273B64D2033/0286F01D13/02F01D15/10F02K3/04F02K3/062F02K3/072F02K3/12F02C6/14F02C3/10F02C7/32F05D2220/76Y02T50/60B64D27/026F01D1/24F02C7/36F05D2220/323F05D2260/40311F05D2260/42
Inventor N·J·J·唐托弗朗索瓦·加莱特
Owner SAFRAN AIRCRAFT ENGINES SAS