Clutched compressor section for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10473028-B2
Application number	US-201715651497-A
Country	US
Kind code	B2
Filing date	Jul 17, 2017
Priority date	Jul 17, 2017
Publication date	Nov 12, 2019
Grant date	Nov 12, 2019

Abstract

A clutched compressor section of a gas turbine engine coupled to a rotor shaft. The clutched compressor section includes at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft.

First claim

What is claimed is:

1. A clutched compressor section of a gas turbine engine coupled to a rotor shaft, comprising:
at least one decoupleable rotor stage, the decoupleable rotor stage switchable between a coupled condition and a decoupled condition with a clutch mechanism, the coupled condition coupling the decoupleable rotor stage with the rotor shaft, the decoupled condition decoupling the decoupleable rotor stage from the rotor shaft;
a plurality of compressor rotor stages axially spaced from each other and operatively coupled to each other, the at least one decoupleable rotor stage being one of the plurality of compressor rotor stages; and
a group of stages of the plurality of compressor rotor stages coupled to each other and to the rotor shaft, the at least one decoupleable rotor stage coupled to the group of stages in the coupled condition and decoupled from the group of stages in the decoupled condition, the decoupled condition allowing the decoupleable rotor stage to freely rotate independently of the group of stages, the clutch mechanism comprising:
a first engagement member extending from a disk of one of the stages of the group of stages; and
a second engagement member extending from a disk of the decoupleable stage, the relative position of the first engagement member and the second engagement member determining if the decoupleable stage and the group of stages are in the coupled condition or the decoupled condition.

2. The clutched compressor section of claim 1 , wherein the decoupleable stage is located downstream of the group of stages.

3. The clutched compressor section of claim 1 , wherein the decoupleable stage is coupled to a shaft that is coaxially oriented with the rotor shaft.

4. The clutched compressor section of claim 1 , wherein the first engagement member and the second engagement member are disposed in an interference fit condition in the coupled condition, wherein a threshold centrifugal force overcomes the interference fit condition to dispose the first engagement member and the second engagement member in the decoupled condition.

5. The clutched compressor section of claim 1 , wherein the relative position of the first engagement member and the second engagement member is controlled with an electromagnetic field applied proximate the clutch mechanism.

6. The clutched compressor section of claim 5 , wherein the electromagnetic field is generated from a stator pack located proximate the clutch mechanism.

7. The clutched compressor section of claim 1 , wherein the first engagement member and the second engagement member are aero-viscously coupled to each other.

8. The clutched compressor section of claim 1 , wherein the decoupled condition is provided when the rotational speed of the rotor shaft exceeds a predetermined speed to reduce fluid compression and compressor temperature.

9. The clutched compressor section of claim 1 , wherein the plurality of rotor stages are part of a high pressure compressor.

10. A gas turbine engine comprising:
a compressor section;
a combustor section;
a turbine section;
a rotor shaft coupling the compressor section and the turbine section;
at least one rotor stage of the compressor section that is decoupleable from the rotor shaft with a clutch mechanism configured to switch between a coupled condition and a decoupled condition;
a plurality of compressor rotor stages axially spaced from each other and operatively coupled to each other, the at least one decoupleable rotor stage being one of the plurality of compressor rotor stages; and
a group of stages of the plurality of compressor rotor stages coupled to each other and to the rotor shaft, the at least one decoupleable rotor stage coupled to the group of stages in the coupled condition and decoupled from the group of stages in the decoupled condition, the decoupled condition allowing the decoupleable rotor stage to freely rotate independently of the group of stages, the clutch mechanism comprising:
a first engagement member extending from a disk of one of the rotor stages; and
a second engagement member extending from a disk of the decoupleable stage, the relative position of the first engagement member and the second engagement member determining if the decoupleable stage and the remainder of the stages are in the coupled condition or the decoupled condition.

11. The gas turbine engine of claim 10 , wherein the decoupleable stage is located downstream of the remainder of stages.

12. The gas turbine engine of claim 10 , wherein each of the remainder of the stages are coupled to each other and to a rotor shaft that directly drives the remainder of the stages.

13. The gas turbine engine of claim 12 , wherein the decoupleable stage is coupled to a shaft that is coaxially oriented with the rotor shaft.

14. The gas turbine engine of claim 10 , wherein the first engagement member and the second engagement member are disposed in an interference fit condition in the coupled condition, wherein a threshold centrifugal force overcomes the interference fit condition to dispose the first engagement member and the second engagement member in the decoupled condition.

15. The gas turbine engine of claim 14 , wherein the relative position of the first engagement member and the second engagement member is controlled with an electromagnetic field applied proximate the clutch mechanism.

Assignees

• United Technologies Corp

Inventors

• Ditomasso John C
• Dibenedetto Enzo

Classifications

• F05D2270/112

  by limiting temperatures · CPC title

• F05D2260/404

  through magnetic drive coupling · CPC title

• F05D2260/4023

  through a friction clutch · CPC title

• F05D2240/20

  Rotors · CPC title

• F05D2220/323

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