Bypass turbomachine for an aircraft

Patent metadata

Field	Value
Publication number	US-12291978-B2
Application number	US-202017753045-A
Country	US
Kind code	B2
Filing date	Aug 26, 2020
Priority date	Aug 29, 2019
Publication date	May 6, 2025
Grant date	May 6, 2025

Abstract

The invention relates to a bypass turbomachine ( 2 ) for an aircraft, comprising a gas generator ( 5 ) and a ducted fan ( 4 ) comprising variable pitch blades ( 18 ) configured to take a reverse thrust position driving a reverse flow ( 24 ) of air within a secondary duct ( 16 ), the gas generator ( 5 ) being connected to a fan casing ( 3 ) by a stator blade assembly ( 40 ) that passes through the secondary duct, first openings ( 28 ) for letting in air from the reverse flow being located on an outer casing ( 17 ) at least partially internally delimiting the outer duct, and second openings ( 29 ) for letting said air out being located on an inner casing ( 14 ) at least partially externally delimiting an inner duct ( 12 ). The first openings are located within a plane that is perpendicular to a longitudinal axis (C) of the turbomachine and passes substantially through the middle of the blade assembly.

First claim

The invention claimed is:

1. A bypass turbomachine for an aircraft, the turbomachine comprising a ducted fan and a gas generator, the fan being configured to generate a primary flow of air in a primary duct inside the gas generator and a secondary flow in a secondary duct extending around the gas generator and inside a fan casing, the fan comprising variable pitch vanes which are able to adopt a reverse thrust position driving a flow of a reverse flow of air in the secondary duct the gas generator being connected to the fan casing by a stator vane assembly which passes through the secondary duct, the gas generator comprising two annular casings, outer and inner respectively, extending around each other, the outer casing at least partially internally delimiting the secondary duct and being connected to the stator vane assembly, and the inner casing at least partially externally delimiting the primary duct, the turbomachine further comprising first openings for letting in air from the reverse flow being located on the outer casing, and second openings for letting this air out being located on the inner casing, characterised in that at least one portion of said first openings is located in a plane perpendicular to a longitudinal axis of the turbomachine passing through an area located in the middle of said vane assembly along an axial direction, and in that first flaps and second flaps are provided respectively at the level of said first and second openings and are movable between positions of closure and of release of these openings, said first flaps being pivotably mounted to the outer casing, said seconds flaps being pivotably mounted to the inner casing, said first flaps and second flaps being pivotally movable, having a scooping function and being configured to extend respectively at least partially into said secondary duct and said primary duct when in the release position and so that the radially outer ends of the first flaps are located at a radial dimension in the secondary duct that is between 20 and 30% of the total radial dimension of said secondary duct, said dimensions being measured from the outer casing in line with these ends,
wherein the stator vane assembly comprises structural arms and flow straightening vanes, the arms comprising trailing edges downstream of the trailing edges of the vanes with respect to said primary flow, said first openings being located between the arms and at least partially downstream of the trailing edges of the vanes, and
wherein the first openings are located circumferentially between the structural arms and also between the structural arms and the flow straightening vanes.

2. The turbomachine according to claim 1 , wherein guide fins are located in said first openings and/or in said second openings and/or between said first and second openings.

Assignees

• Safran Aircraft Engines

Inventors

• Lebeault Eva Julie
• Binder Anthony
• Soulat Laurent

Classifications

• F05D2260/606

  Bypassing the fluid · CPC title

• F05D2240/30

  Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K3/075

  controlling flow ratio between flows · CPC title