Blower assembly

Patent metadata

Field	Value
Publication number	US-11988100-B2
Application number	US-202217988472-A
Country	US
Kind code	B2
Filing date	Nov 16, 2022
Priority date	Dec 14, 2021
Publication date	May 21, 2024
Grant date	May 21, 2024

Abstract

A blower assembly for providing air to an airframe system, including a rotor configured to be mechanically coupled to a spool of a gas turbine engine and a flow modifier configured to receive and/or direct flow to the rotor; wherein the blower assembly is configured to permit relative movement between the rotor and the flow modifier to move between: a compressor configuration in which the rotor is configured to be driven to rotate by the spool and to receive and compress air from the gas turbine engine, and discharge the compressed air for supply to the airframe system; and a turbine configuration in which the rotor is configured to receive air from an external air source to drive the spool to rotate.

First claim

The invention claimed is:

1. A blower assembly for providing air to an airframe system, comprising:
a rotor configured to be mechanically coupled to a spool of a gas turbine engine;
a flow modifier configured to receive and/or direct flow to the rotor;
wherein the blower assembly is configured to permit relative movement between the rotor and the flow modifier to move between:
a compressor configuration in which the rotor is configured to be driven to rotate by the spool and to receive and compress air from the gas turbine engine, and discharge the compressed air for supply to the airframe system; and
a turbine configuration in which the rotor is configured to receive air from an external air source to drive the spool to rotate;

wherein the flow modifier comprises:
a diffuser vane array comprising a plurality of diffuser vanes and configured to act together with the rotor to compress the air received at the rotor in the compressor configuration;
a nozzle guide vane array comprising a plurality of nozzle guide vanes and configured to act together with the rotor to expand the air received at the nozzle guide vane array in the turbine configuration; and
an actuator arrangement configured to:
cause relative axial movement between the rotor and the diffuser vane array so that the diffuser vane array is disposed around the rotor for operation in the compressor configuration; and
cause relative axial movement between the rotor and the nozzle guide vane array so that the nozzle guide vane array is disposed around the rotor for operation in the turbine configuration.

2. The blower assembly according to claim 1 , further comprising a variable transmission for mechanically coupling the rotor to the spool.

3. The blower assembly according to claim 1 , wherein the blower assembly is configured so that a direction of rotation of the rotor in the turbine configuration is the same as a direction of rotation of the rotor in the compressor configuration.

4. The blower assembly according to claim 1 , wherein the flow modifier comprises a plurality of vanes.

5. The blower assembly according to claim 1 , wherein the blower assembly comprises an actuator arrangement for causing the relative movement between the rotor and flow modifier to move the blower assembly between the compressor configuration and the turbine configuration.

6. The blower assembly according to claim 1 , wherein the actuator arrangement is configured to adjust an effective axial height of the diffuser vanes by varying an open area of an inlet interface between the rotor and the diffuser vane array, and/or by varying an open area of an outlet interface at a radially outer side of the diffuser vane array, wherein the effective axial height is with respect to a rotational axis of the rotor.

7. The blower assembly according to claim 6 , wherein the diffuser vane array and the nozzle guide vane array are rigidly connected so as to form a combined vane array assembly.

8. The blower assembly according to claim 7 , wherein the actuator arrangement comprises:
a mode actuator configured to cause relative movement between the rotor and the combined vane array assembly for moving the blower assembly between the compressor configuration and the turbine configuration; and
a diffuser height actuator configured to adjust the effective axial height of the diffuser vanes.

9. The blower assembly according to claim 7 , wherein the actuator arrangement comprises a driving actuator configured to cause relative movement between the combined vane array assembly and the rotor to move the blower assembly between the compressor configuration and the turbine configuration.

10. The blower assembly according to claim 9 , wherein the actuator arrangement is configured to cause relative movement between a diffuser vane array guide and the combined vane array assembly to adjust the effective axial height of the diffuser vanes in the compressor configuration.

11. The blower assembly according to claim 10 , wherein
the driving actuator is configured to act on the diffuser vane array guide to cause relative movement between the diffuser vane array guide and the rotor over an actuator travel range;
a first portion of the actuator travel range corresponds to movement between the turbine and compressor configurations;
the actuator arrangement further comprises a biasing member configured to bias the combined vane array assembly and the diffuser vane array guide to an open configuration throughout the first portion of the actuator travel range, the open configuration corresponding to unrestrained flow through the diffuser vane array; and
the actuator arrangement is configured so that a second non-overlapping portion of the actuator travel range corresponds to movement of the diffuser vane array guide relative to the combined vane array assembly away from the open configuration to vary the effective axial height of the diffuser vanes in the compressor configuration.

12. A gas turbine engine for an aircraft, the gas turbine engine comprising the blower assembly of claim 1 .

13. An aircraft comprising:
the blower assembly according to claim 1 .

14. An aircraft comprising:
a gas turbine engine comprising the blower assembly of claim 1 .

15. The blower assembly according to claim 1 , wherein the flow modifier is a fixed geometry flow modifier.

Assignees

• Rolls Royce Plc

Inventors

• Murray Christopher A

Classifications

• F01D17/16 Primary

  by means of nozzle vanes · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D17/143 Primary

  the shiftable member being a wall, or part thereof of a radial diffuser · CPC title

• F01D17/167

  of vanes moving in translation · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title