Aircraft propulsion assembly comprising an air flow valve with a variable flow rate

Patent metadata

Field	Value
Publication number	US-9835050-B2
Application number	US-201514634212-A
Country	US
Kind code	B2
Filing date	Feb 27, 2015
Priority date	Apr 14, 2014
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

A propulsion assembly having a heat exchanger and a system for supplying cold air including an air inlet in a stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate inside the duct, the valve including a hub having blades projecting radially from the hub forming a helix, each blade having a root mounted rotatably on the hub, the valve comprising an electric motor to drive the hub by a motor shaft, and structure for varying pitch angle of the blades, the extremity of each blade being flush with a wall of the duct, the valve controllable to a closed configuration where pitch angle of the blades is 0° and the valve prevents passage of air, an open configuration where pitch angle is 90°, and/or a charge configuration where pitch angle is between 0° and 90°.

First claim

The invention claimed is:

1. A propulsion assembly comprising a turbomachine and a pylon, the turbomachine comprising an engine attached to the pylon, an annular interstream shroud surrounding the engine and an annular nacelle arranged coaxially around and radially towards the exterior in relation to the interstream shroud in such a way as to delimit, together with the latter, a stream of air, the turbomachine comprising a heat exchanger and a system for the supply of cold air, the system comprising an air inlet placed in the stream of air, an air duct connecting the air inlet fluidly to the exchanger, and an air flow valve with a variable flow rate placed inside the air duct, wherein the air flow valve comprises a hub, on which there are mounted at least three blades projecting radially from the hub in order to form a helix, each blade having a root mounted rotatably on the hub, the air flow valve in addition comprising an electric motor configured to drive the hub by a motor shaft, and structure for varying the pitch angle of the blades, the extremity of each blade being flush with a wall of the air duct, the air flow valve being controllable to adopt one of the following configurations:
a closed configuration, in which the pitch angle of the blades is 0° and in which the valve prevents the passage of the air through the duct;
an open configuration, in which the pitch angle of the blades is 90° and in which the valve completely opens the access to the air duct;
a charge configuration, in which the pitch angle of the blades lies in the range between 0° and 90°.

2. The propulsion assembly as claimed in claim 1 , wherein, in the charge configuration, the pitch angle of the blades lies in the range between 35° and 50°.

3. The propulsion assembly as claimed in claim 1 , wherein the structure for varying the pitch angle of the blades comprises a ring attached to a foot of each of the blades and movably mounted in translation on the motor shaft, an actuating lever, and a servomotor configured to cause the actuating lever to rotate.

4. The propulsion assembly as claimed in claim 3 , wherein the actuating lever is rotatably mounted in an axis perpendicular to an axis of rotation of the motor shaft and is supported by two support arms that are spaced apart from one another and are each attached to the motor casing, the actuating lever comprising in addition two actuating arms that are spaced apart from one another, each of the actuating arms comprising at its free extremity a roller that is capable of rotation and is intended to roll in a throat made in the ring.

5. The propulsion assembly as claimed in claim 3 , wherein, for each blade, the ring is attached to the foot of the blade via a lever having a pivoting linkage with a transmission rod parallel to the axis of rotation of the motor shaft, the lever being attached to the root of the blade.

6. The propulsion assembly as claimed in claim 1 , wherein the hub is situated downstream in a direction of flow of a flow of air passing through the duct, while the motor is situated upstream in the direction of flow.

7. The propulsion assembly as claimed in claim 1 , wherein the hub is situated upstream in a direction of flow of a flow of air passing through the duct, while the motor is situated downstream in the direction of flow.

8. The propulsion assembly as claimed in claim 1 , wherein the exchanger is arranged inside the pylon, the air duct being arranged inside a space situated between the nacelle and the pylon.

Assignees

• Airbus Operations Sas

Inventors

• Marche Jacques Hervé

Classifications

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F01D17/00

  Regulating or controlling by varying flow (for reversing F01D1/30; by varying rotor-blade position F01D7/00; specially for starting F01D19/00; shutting-down F01D21/00; regulating or controlling in general G05 {; specially adapted for hand-held tools or the like F01D15/06}) · CPC title

• F01D25/12 Primary

  Cooling · CPC title

• F02K3/115

  by means of indirect heat exchange · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title