Three spool geared turbofan with low pressure compressor drive gear system and mechanical controller

Patent metadata

Field	Value
Publication number	US-2016195096-A1
Application number	US-201414912105-A
Country	US
Kind code	A1
Filing date	Aug 21, 2014
Priority date	Aug 29, 2013
Publication date	Jul 7, 2016
Grant date	—

Abstract

A turbofan engine is disclosed that includes a fan rotatable about an axis, a compressor section including a high pressure compressor, a medium pressure compressor and a low pressure compressor and a turbine section including a high pressure turbine, an intermediate turbine and a fan drive turbine. A fan drive gear system is driven by the fan drive turbine for driving the fan. A compressor drive gear system is driven by the intermediate turbine for driving the low pressure compressor. A gear controller controls rotation of at least one of the fan drive gear system and the compressor drive gear system relative to a static structure to vary an effective speed reduction ratio of one of the fan drive gear system and the compressor drive gear system.

First claim

What is claimed is:

1 . A turbofan engine comprising:
a fan; a compressor section including: a first compressor; and a second compressor; a turbine section including: a first turbine; a second turbine; and a third turbine; a plurality of gear systems, including: a first gear system; and a second gear system; wherein the first turbine drives the first compressor through the first gear system, and the second turbine drives the second compressor through the second gear system; and the engine further comprises a gear controller for controlling rotation of at least one of the plurality of gear systems relative to a static structure, thereby varying an effective engine speed reduction ratio.

2 . The turbofan engine as recited in claim 1 , wherein the first gear system and the second gear system each includes a sun gear, a plurality of planet gears and a ring gear circumscribing the plurality of planet gears.

3 . The turbofan engine as recited in claim 2 , wherein a low shaft driven by the first turbine drives the sun gear of the first gear system and an intermediate shaft driven by the second turbine drives the sun gear of the second gear system and the plurality of planet gears rotate about a corresponding plurality of fixed axes and the first gear system ring gear is coupled to the fan and the second gear system ring gear is coupled to the second compressor.

4 . The turbofan engine as recited in claim 3 , wherein the first compressor is coupled to the first gear system ring gear.

5 . The turbofan engine as recited in claim 1 , wherein the first gear system is coupled to a portion of the second gear system.

6 . The turbofan engine as recited in claim 5 , wherein the gear controller is coupled to the second compressor and controls rotation of the second gear system through the second compressor.

7 . The turbofan engine as recited in claim 5 , wherein the gear controller is coupled to a carrier of the second gear system for controlling rotation of the carrier relative to a static structure.

8 . The turbofan engine as recited in claim 1 , wherein the gear controller varies the effective speed reduction of both the first gear system and the second gear system.

9 . The turbofan engine as recited in claim 7 , wherein increasing a speed of rotation of the carrier relative to the static structure reduces the effective speed reduction to increase a speed of both the second compressor and the fan.

10 . The turbofan engine as recited in claim 7 , wherein decreasing a speed of rotation of the carrier relative to the static structure increases the effective speed reduction to decrease a speed of both the second compressor and the fan.

11 . The turbofan engine as recited in claim 1 , wherein the first gear system and the second gear system includes a gear reduction in a static condition greater than about 2.3.

12 . A method of controlling a turbofan engine comprising:
coupling a fan rotatable about an axis to a first turbine through a first gear system such that the fan rotates at a speed slower than the first turbine; coupling a second compressor section to a second turbine through a second gear system such that the second compressor section rotates at a speed slower than the second turbine; and controlling rotation of at least one of the first gear system and the second gear system relative to a fixed structure with a gear controller to vary an effective speed reduction ratio.

13 . The method as recited in claim 12 , coupling the first gear system to the second gear system to vary the effective speed reduction of both the first gear system and the second gear system.

14 . The method as recited in claim 13 , including coupling the gear controller to the second compressor section and varying the effective speed reduction ratio of both the first gear system and the second gear system through the second compressor section.

15 . The method as recited in claim 14 , including coupling the gear controller to a portion of the second gear system for varying the effective speed reduction ration of both the first gear system and the second gear system.

16 . The method as recited in claim 12 , including reducing the effective speed reduction ratio by increasing a speed of rotation relative to a static structure of the second gear system and the first gear system.

17 . The method as recited in claim 12 , including increasing the effective speed reduction ratio by decreasing a speed of rotation relative to a static structure of the second gear system and the first gear system.

Assignees

• United Technologies Corp

Inventors

• Otto John R
• Coffin James B
• Husband Jason

Classifications

• F02C3/107

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

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F02C7/36

  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 title

• F02K3/06 Primary

  with front fan · CPC title