GAS TURBINE ENGINE

• US 20170191413A1
• Filed: 12/07/2016
• Published: 07/06/2017
• Est. Priority Date: 01/06/2016
• Status: Abandoned Application

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: KNIGHT, Glenn A., ROBINSON, Daniel, BOSTOCK, George, SHEAF, Christopher T. J., MAGUIRE, Alan R.
• Application Number:
  US15/372,289
• Publication Number:
  US 20170191413A1
• Time in Patent Office: Days
• CPC Class Codes: B64D 13/02 the air being pressurised
• CPC Class Codes: B64D 27/10 of gas-turbine type jet aircraft B64D27/16
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/04 Air intakes for gas-turbine plants or jet-propulsion plants
• CPC Class Codes: F02C 7/057 Control or regulation conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16
• CPC Class Codes: F02C 7/277 the starter being a separate turbine
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2270/102 caused by working fluid flow velocity profile distortion
• CPC Class Codes: F05D 2270/1022 due to high angle of attack of aircraft
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine including an intake, a fan and an injector system. The intake has an inner wall which defines an intake passage for the fan. The injector system includes a cabin blower system including a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and by the injector system. The intake includes an injector of the injector system through which in use fluid from the cabin blower compressor is injected into a main airflow for flow control of air on the way to the fan.

Claims

1. A gas turbine engine comprising an intake, a fan and an injector system, where the intake has an inner wall which defines an intake passage for the fan, and the injector system comprises a cabin blower system comprising a cabin blower compressor arranged in use to compress fluid used in a cabin of an aircraft and by the injector system, and where further the intake comprises an injector of the injector system through which in use fluid from the cabin blower compressor is injected into a main airflow for flow control of that airflow on the way to the fan and where the injector system comprises a controller arranged to control operation of the injector and the controller is further arranged to control the transmission to determine the rate at which the cabin blower compressor is driven in accordance with the requirements for cabin pressurisation and fluid injection by the injectors.

2. A gas turbine engine according to claim 1 where the injector is positioned to inject fluid into the airflow inside of the intake passage.

3. A gas turbine engine according to claim 1 where the intake comprises a lip region, a throat region and a diffuser region and the injector is positioned to inject fluid into the airflow inside of the intake passage downstream of the lip region.

4. A gas turbine engine according to claim 1 where the injector directs injected fluid towards the fan.

5. A gas turbine engine according to claim 1 where the injector directs injected fluid in a direction substantially parallel to the inner wall of the intake.

6. A gas turbine engine according to claim 1 where the injector is positioned to inject fluid into the airflow outside of the intake passage.

7. A gas turbine engine according to claim 6 where the intake comprises a lip region, a throat region and a diffuser region and the injector is positioned to inject fluid into the airflow outside of the intake passage proximate the throat region.

8. A 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.

9. A gas turbine engine according to claim 8 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 and where further 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.

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

11. A gas turbine engine according to claim 10 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.

12. A gas turbine engine according to claim 8 where drive to the transmission in use is provided by one or more shafts of the gas turbine engine.

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

14. An aircraft according to claim 13 where the aircraft comprises at least two of the gas turbine engines and the aircraft comprises at least one inter-engine duct via which fluid compressed by the cabin blower compressor of one of the engines is selectively deliverable to the injector system injectors of another of the engines.