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aircraft including turbine engines integrated into the rear fuselage

一种涡轮发动机、航空器的技术，应用在航空器领域，能够解决损失扇叶、不平衡等问题

Active Publication Date: 2019-02-19
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] However, the possibility of one of the fans failing, eg becoming unbalanced or even losing blades must be taken into account

Method used

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  • aircraft including turbine engines integrated into the rear fuselage
  • aircraft including turbine engines integrated into the rear fuselage
  • aircraft including turbine engines integrated into the rear fuselage

Examples

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Embodiment Construction

[0027] The present invention is particularly suitable for such as aircraft, including figure 1 Aircraft with turbine engines of the type shown.

[0028] Such as figure 1 As shown, the turbine engine is centered on the longitudinal axis XX of the fuselage 1 of the aircraft. The turbine engine includes two separate gas generators 2a, 2b from upstream to downstream along the direction of gas flow, and these two gas generators simultaneously supply a single power turbine 3. The turbine engine is installed at the downstream end of the fuselage 1 of the aircraft.

[0029] In a manner known per se, each gas generator 2a, 2b includes at least a compressor, a combustion chamber and a turbine (not shown in the drawings).

[0030] In this document, the terms axial and radial refer to the axis XX of the fuselage and the turbine engine. Likewise, the terms upstream and downstream refer to the main direction of flow along the axis.

[0031] Each gas generator 2a, 2b is received inside the main fl...

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Abstract

The invention relates to an aircraft comprising a fuselage (1) and being propelled by a turbine engine having two coaxial and counter-rotating blowers (7, 8), the turbine engine comprising a power turbine (3) having two Two counter-rotating rotors, one rotor (5) of the rotor drives the fan (7) upstream of the turbine (3), and the other rotor (6) drives the fan (8) downstream of the turbine (3), each A fan comprises a ring of blades, and the assembly of the fans (7, 8) and the power turbine (3) is integrated at the rear of the fuselage (1), in an extension of the fuselage, the aircraft's characterized in that, for at least one of the wind turbines (7, 8), the aircraft comprises a device (28, 27) for preventing the rotation of the wind turbine (7, 8) and a device configured to change said wind turbine (7, 8) The means (33, 17) of the pitch of the blades to operate the fan as a flow straightener relative to another fan.

Description

Technical field [0001] The invention relates to the field of aircraft propelled by turbine engines, such as aircraft, especially commercial aircraft, which have counter-rotating fans integrated in the downstream extension of the fuselage. The present invention more specifically relates to a device for adjusting the fan of a turbine engine of this type of architecture for specific operating conditions that must be considered for safety reasons. Background technique [0002] FR-A1-2 997 681 proposes a new aircraft architecture, which makes it possible to reduce aircraft noise pollution and fuel consumption by absorbing the boundary layer to limit aerodynamic drag. [0003] In this architecture, the aircraft is propelled by a turbine engine with a ducted counter-rotating fan, which is integrated in the rear of the aircraft's fuselage. Generally, a turbine engine includes two gas generators, which supply a power turbine with two counter-rotating rotors to drive two fans arranged downs...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K3/065F01D21/06F02K3/072
CPCF01D21/06F02K3/072F01D17/16B64C11/325F01D17/167B64C11/002F01D1/24F01D1/023B64C11/385F01D17/14F01D17/162B64C11/306B64D27/14B64D29/04B64D27/20F02K3/12
Inventor 弗朗索瓦·加莱特
Owner SAFRAN AIRCRAFT ENGINES SAS
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