Compressor tip injector

Patent metadata

Field	Value
Publication number	US-10145387-B2
Application number	US-201615136409-A
Country	US
Kind code	B2
Filing date	Apr 22, 2016
Priority date	May 19, 2015
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system is disclosed. The compressor tip injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system. The compressor case comprises one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compressor as they rotate.

First claim

The invention claimed is:

1. A gas turbine engine comprising a compressor, a compressor case surrounding the compressor and a compressor tip injector system, the compressor tip injector system comprising a cabin blower system comprising a cabin blower compressor arranged in use to compress air used in a cabin of an aircraft and by the compressor tip injector system, the compressor case comprising one or more injectors of the compressor tip injector system through which in use air from the cabin blower compressor is injected towards blade tip ends of blades of the compressor as they rotate.

2. The gas turbine engine according to claim 1 where one or more of the injectors are upstream injectors located to inject air from upstream of the compressor.

3. The gas turbine engine according to claim 2 where the compressor tip injector system comprises a plurality of circumferentially distributed upstream injectors.

4. The gas turbine engine according to claim 1 where one or more of the injectors are radial injectors axially aligned with and radially outwards of the blade tips.

5. The gas turbine engine according to claim 4 where the compressor tip injector system comprises a compressor tip injection controller the controller being arranged to control injection from the radial injectors so that the air injected is pulsed.

6. The gas turbine engine according to claim 1 where the cabin blower system further comprises a transmission and the cabin blower compressor is drivable in use via the transmission, the transmission comprising a toroidal continuously variable transmission giving selectively variable control over the rate at which the cabin blower compressor is driven.

7. The gas turbine engine according to claim 6 where the toroidal continuously variable transmission comprises at least one traction drive through which in use drive is transmitted, the traction drive comprising first and second toroids, the first and second toroids each having one of a pair of opposed toroidal surfaces and there being a set of rotatable variators disposed between the opposed toriodal surfaces, the first and second toroids are separated and are drivingly engaged via a wheel of each variator, each wheel running in use on both of the opposed toroidal surfaces.

8. The gas turbine engine according to claim 6 where the transmission further comprises a bypass drive transmission parallel to the toroidal continuously variable transmission.

9. The gas turbine engine according to claim 8 where the transmission is arranged such that in use drive from the toroidal continuously variable transmission and the bypass drive transmission is combined and delivered to the cabin blower compressor.

10. The gas turbine engine according to claim 6 where drive to the transmission in use is provided by one or more shafts of the gas turbine engine.

11. The gas turbine engine according to claim 1 where the gas turbine engine does not have a variable area nozzle.

12. The gas turbine engine according to claim 1 where the blades of the compressor are not variable.

13. The gas turbine engine according to claim 1 where the compressor is a fan and the compressor case is a fan case.

14. An aircraft comprising a gas turbine engine according to claim 1 .

15. The aircraft according to claim 14 where the aircraft comprises at least two gas turbine engines according to 1 and the aircraft comprises at least one inter-engine duct via which air compressed by the cabin blower compressor of one of the engines is selectively deliverable to the compressor tip injector system injectors of another of the engines.

16. A method of operating an aircraft, the aircraft comprising at least two gas turbine engines according to claim 1 and at least one inter-engine duct via which air compressed by the cabin blower compressor of one of the engines is selectively deliverable to the compressor tip injector system injectors of another of the engines, the method comprising, delivering air from one of the engines having an operational cabin blower compressor to the injectors of the other engine via the inter-engine duct when the cabin blower compressor of that other engine is operating sub-normally and/or is inoperative.

Assignees

• Rolls Royce Plc

Inventors

• Knight Glenn A
• Maguire Alan R
• Robinson Daniel
• Bostock George
• Wilson Mark J

Classifications

• F16H37/084

  at least one power path being a continuously variable transmission, i.e. CVT · CPC title

• B64D13/06

  the air being conditioned (pressurising B64D13/02) · CPC title

• F16H2037/088

  Power-split transmissions with summing differentials, with the input of the CVT connected or connectable to the input shaft · CPC title

• F05D2270/101

  Compressor surge or stall · CPC title

• F04D19/00

  Axial-flow pumps (F04D21/00 takes precedence; {pump comprising axial flow and radial flow stages F04D17/025}) · CPC title