Propulsion assembly, aircraft including propulsion assembly and ventilation method thereof

A technology for propulsion components and aircraft, which is applied in the cooling of turbine/propulsion units, jet propulsion units, aircraft parts, etc. Small design constraints, the effect of reducing stamping resistance

Active Publication Date: 2019-11-05
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0029] However, the ventilation air flow 60 through the internal compartment 54 of the internal fairing device 48 may be insufficient, especially in turbojet engines with a large dilution ratio
[0030] However, the solution consisting of enlarging the size of the intake orifice 56 and the outlet orifice 58 is detrimental to the performance of the turbojet engine and also has the disadvantages described above with regard to the risk of fire

Method used

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  • Propulsion assembly, aircraft including propulsion assembly and ventilation method thereof
  • Propulsion assembly, aircraft including propulsion assembly and ventilation method thereof
  • Propulsion assembly, aircraft including propulsion assembly and ventilation method thereof

Examples

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Embodiment Construction

[0071] figure 2 shows the first embodiment of the present invention with figure 1 The propulsion assembly in is similar to the propulsion assembly 10 , but in this propulsion assembly 10 a fan 70 is housed in the inner compartment 28 of the outer fairing 14 in a rearward direction from the air intake aperture 42 .

[0072] The fan 70 includes a fan propeller 74, a first shaft 76 fixed to the fan propeller 74, an electromagnetic clutch 78, a second shaft 80 carrying a first gear 82 engaged with a rotor shaft 84 of an electric motor 86, and a first gear 89 engaged with a gear 89. Two gears 88 and 89 form part of the auxiliary gearbox 36 and are driven in rotation by the intermediate shaft 40 .

[0073] In the terminology of the present invention, the first shaft 76, the electromagnetic clutch 78, the second shaft 80 and the second gear 88 form a "coupling and decoupling" for coupling and decoupling the fan propeller 74 and the gear 89 of the auxiliary gearbox 36. Disconnect c...

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Abstract

The invention relates to a propulsion assembly for an aircraft, an aircraft comprising a propulsion assembly and a method of ventilating an internal compartment in a fairing of a propulsion assembly comprising a turbine engine comprising a rotor and equipped with an auxiliary gearbox comprising at least one gear mechanically coupled to said rotor, the propulsion assembly further comprising a fairing device comprising an outer annular wall and an inner annular wall which together define an inner compartment, the inner compartment is fitted with an air inlet port and an air outlet port, the propulsion assembly includes at least one fan unit housed in the inner compartment and includes a fan propeller and a gear for coupling the fan propeller to the gear and disconnecting coupling and disconnecting devices.

Description

technical field [0001] The invention relates to an aircraft propulsion assembly comprising at least one fairing and is particularly suitable for cooling a defined compartment located inside the fairing. [0002] The invention is equally applicable to a propulsion assembly comprising a turbojet engine and to a propulsion assembly comprising a turboprop engine or to a propulsion assembly comprising an open rotor turbojet engine. [0003] More precisely, the rectification device according to the invention may be a rectification device of the type that delimits the outer boundaries of the bypass flow channel of the twin-flow turbojet engine, or of the type that divides the The bypass airflow channel of the jet engine is separated from the core, or this type of fairing delimits the outer boundary of the turboprop or open rotor turbojet. [0004] The invention also relates to an aircraft equipped with such a propulsion assembly and a method of ventilating an internal compartment in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D33/08B64D29/06B64D27/16
CPCB64D33/08F02C7/32B64D2033/024B64D2033/0286F05D2260/608F02C7/18Y02T50/60
Inventor 奥利维耶·韦尔瑟
Owner AIRBUS OPERATIONS (SAS)
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