Gas turbine engine

Patent metadata

Field	Value
Publication number	US-2016138478-A1
Application number	US-201514936062-A
Country	US
Kind code	A1
Filing date	Nov 9, 2015
Priority date	Nov 13, 2014
Publication date	May 19, 2016
Grant date	—

Abstract

A gas turbine engine is disclosed comprising a shaft driven by a turbine, the turbine directly driving a lower speed compressor via a shaft and driving a higher speed compressor via the shaft and a multiplier power gearbox. The gearbox comprises a ring gear, a plurality of planet gears and planet carrier and a sun gear. The input from the turbine to the gearbox is to the carrier and the output from the gearbox to drive the higher speed compressor is from the sun gear or the ring gear.

First claim

1 . A gas turbine engine comprising a shaft driven by a turbine, the turbine directly driving a lower speed compressor via a shaft and indirectly driving a higher speed compressor via the shaft and a multiplier power gearbox, the gearbox comprising a ring gear, a plurality of planet gears and planet carrier and a sun gear, the input from the turbine to the gearbox being to the carrier and the output from the gearbox to drive the higher speed compressor being from the sun gear or the ring gear.

2 . A gas turbine engine according to claim 1 where the output from the gearbox to drive the higher speed compressor is from the sun gear and the ring gear is static.

3 . A gas turbine engine according to claim 2 where the driving link between the shaft and the planet carrier is located forward of the gearbox

4 . A gas turbine engine according to claim 1 where the output from the gearbox to drive the higher speed compressor is from the ring gear and the sun gear is static.

5 . A gas turbine engine according to claim 1 where the gearbox is forward of the higher speed compressor.

6 . A gas turbine engine according to claim 1 further comprising a stator array substantially axially aligned with and radially outward of the gearbox.

7 . A gas turbine engine according to claim 6 where the stators are immediately upstream of aerofoils of the higher speed compressor and are arranged in use to condition the air entering the aerofoils.

8 . A gas turbine engine according to claim 1 where the gas turbine engine is a turbofan engine comprising a core duct and a bypass duct.

9 . A gas turbine engine according to claim 8 where an air passage is provided through an intercase between the core and bypass ducts, through one or more of the stators in the stator array which is located in the core duct and into a region radially inward of the core duct.

10 . A gas turbine engine according to claim 1 where the lower speed compressor is a fan.

11 . A gas turbine engine according to claim 10 where the gearbox is located within a casing between a module for the fan and a forward main bearing for the shaft.

12 . A gas turbine engine according to claim 10 where the higher speed compressor is a compressor immediately downstream of the fan.

13 . A gas turbine engine according to claim 1 where the gas turbine engine is a two shaft engine further comprising a high pressure turbine, high pressure shaft and high pressure compressor.

Assignees

• Rolls Royce Deutschland

Inventors

• Negulescu Dimitrie

Classifications

• F02C3/107

  with two or more rotors connected by power transmission · CPC title

• F05D2260/4031

  as in toothed gearing · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2220/323

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

• F02K3/06

  with front fan · CPC title