Aircraft propulsion assembly equipped with a main fan and with a least one offset fan

Patent metadata

Field	Value
Publication number	US-2018266316-A1
Application number	US-201615764864-A
Country	US
Kind code	A1
Filing date	Oct 5, 2016
Priority date	Oct 5, 2015
Publication date	Sep 20, 2018
Grant date	—

Abstract

The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY′) offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.

First claim

1 . Powerplant assembly of an aircraft comprising:
at least one twin-spool gas generator of longitudinal axis (XX); at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, said main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY′) offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator comprising at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system comprising a differential gear system incorporating a bevel gear.

2 . Powerplant assembly according to claim 1 , characterized in that the differential gear system comprises a planetary gear train comprising at least one ring gear driving the main fan and a planet carrier driving the auxiliary fan.

3 . Powerplant assembly according to claim 1 , wherein the power transmission system comprises a second power transmission system comprising the differential gear system arranged between the gas generator and the main fan.

4 . Powerplant assembly according to claim 3 , wherein the power transmission system comprises a first power transmission system connected to the auxiliary fan, the second power transmission system being connected to the first power transmission system.

5 . Powerplant ( 1 ) assembly according to claim 1 , wherein the first and/or second power transmission system comprises, in series, two double universal joints with a slide connection.

6 . Powerplant ( 1 ) assembly according to claim 1 , wherein the auxiliary fan is driven by the low-pressure turbine via an intermediate layshaft.

7 . Powerplant ( 1 ) assembly according to claim 6 , wherein the intermediate layshaft comprises a first shaft and a second shaft, which are connected to one another by a coupling.

8 . Powerplant assembly according to claim 1 , wherein the main housing is separate and distinct from the auxiliary housing so as to generate a main secondary airflow and an auxiliary secondary airflow, respectively, which are independent until they are discharged to atmosphere.

9 . Powerplant assembly according to claim 1 , wherein it comprises stator blades arranged downstream of the main fan, the stator blades each having a top end fixed to the fan housing and a structural nature of transmission of forces so as to hook up the first or the second power transmission system.

10 . Powerplant assembly according to claim 1 , wherein the main fan and the gas generator form a turbine engine, the turbine engine being fixed under the wing and the auxiliary fan being fixed on the wing, the axis of the turbine engine and of the auxiliary fan being located in one and the same vertical plane.

11 . Powerplant assembly according to claim 1 , wherein it comprises two auxiliary fans driven by the low-pressure turbine.

12 . Powerplant assembly according to claim 1 , wherein the turbine engine is a multiflow turbojet.

13 . Powerplant assembly according to claim 10 , wherein the turbine engine and the auxiliary fan are mounted on the wing by means of a pylon.

Assignees

• Safran Aircraft Engines

Inventors

• Soulat Laurent
• Lemarchand Kevin Morgane
• Boudebiza Tewfik
• Charier Gilles Alain
• Nowakowski Nathalie
• Curlier Augustin Marc Michel
• Pertat Adrien Pierre Jean
• Reigner Pierre-Alain Jean Philippe

Classifications

• F02K3/06

  with front fan · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2250/312

  the axes being parallel to each other · CPC title

• F05D2240/60

  Shafts · CPC title

• B64D35/04

  characterised by the transmission driving a plurality of propellers or rotors · CPC title