Adaptive case for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11092030-B2
Application number	US-201916388199-A
Country	US
Kind code	B2
Filing date	Apr 18, 2019
Priority date	Apr 18, 2019
Publication date	Aug 17, 2021
Grant date	Aug 17, 2021

Abstract

A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a plurality of blades circumferentially spaced from each other;
a plurality of rings spaced radially outward from the plurality of blades; and
at least one actuator in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one ring of the plurality of rings, wherein the at least one ring is moveable relative to another ring of the plurality of rings.

2. The gas turbine engine of claim 1 , further comprising a housing extending along a central longitudinal axis having an opening facing radially inward with the plurality of rings located within the housing and adjacent the opening.

3. The gas turbine engine of claim 2 , wherein the axial gap is located between an axial end of the housing and one of the plurality of rings.

4. The gas turbine engine of claim 2 , wherein the axial gap is located between adjacent rings of the plurality of rings with a downstream facing surface of a first ring of the adjacent rings defining a first axial end of the of axial gap and a second ring of the adjacent rings defining a second axial end of the axial gap.

5. The gas turbine engine of claim 1 , wherein the plurality of rings engage at least one cam to move at least one of the plurality of rings in an axial direction relative to another one of the plurality of rings.

6. The gas turbine engine of claim 5 , wherein the cam includes a plurality of grooves that engage a corresponding tab on each of the plurality of rings.

7. The gas turbine engine of claim 6 , wherein each of the plurality of grooves include a first portion axially spaced from a second portion by an offset portion, wherein the first portion extends in a circumferential direction having a first constant axial position and the second portion extends in a circumferential direction having a second constant axial position spaced axially from the first constant axial position.

8. The gas turbine engine of claim 7 , wherein the offset portion for each of the plurality of grooves is circumferentially spaced from the offset portion in an adjacent one of the plurality of grooves and the offset portion in a circumferential and axial direction from the first constant axial position to the second constant axial position.

9. The gas turbine engine of claim 5 , wherein the at least one cam includes a plurality of cams spaced around an axis of rotation of the gas turbine engine and each of the plurality if cams is cylindrical having a constant radius to an outermost surface.

10. A casing structure for a gas turbine engine comprising:
a housing extending along a central longitudinal axis having an opening facing radially inward;
a plurality of rings locating within housing adjacent the opening; and
at least one actuator in mechanical communication with the plurality of rings to create an axial gap located adjacent at least one ring of the plurality of rings, wherein the at least one ring is moveable relative to another ring of the plurality of rings.

11. The casing structure of claim 10 , wherein the axial gap is located between an axial end of the housing and one of the plurality of rings.

12. The casing structure of claim 10 , wherein the axial gap is located between adjacent rings of the plurality of rings with a downstream facing surface of a first ring of the adjacent rings defining a first axial end of the of axial gap and a second ring of the adjacent rings defining a second axial end of the axial gap.

13. The casing structure of claim 10 , wherein the plurality of rings engage at least one cam to move at least one of the plurality of rings an in axial direction relative to another one of the plurality of rings.

14. The casing structure of claim 13 , wherein the at least one cam includes a plurality of circumferentially extending grooves that engage a corresponding tab on each of the plurality of rings.

15. The casing structure of claim 14 , wherein each of the plurality of grooves include a first portion axially spaced from a second portion by an offset portion, wherein the first portion extends in a circumferential direction having a first constant axial position and the second portion extends in a circumferential direction having a second constant axial position spaced axially from the first constant axial position.

16. The casing structure of claim 15 , wherein the offset portion for each of the plurality of grooves is circumferentially spaced from an offset in an adjacent one of the plurality of grooves and the offset portion extends in a circumferential and axial direction from the first constant axial position to the second constant axial position.

17. The casing structure of claim 13 , wherein the at least one cam includes a plurality of cams spaced around an axis of rotation of the gas turbine engine and each of the plurality of cams is cylindrical having a constant radius to an outermost surface.

18. A method of controlling an axial gap in a casing structure in a gas turbine engine comprising the steps of:
engaging at least one ring with a mechanical connection attached to an actuator;
moving the at least one ring of a plurality of rings in a first axial direction based on a first operating condition of the gas turbine engine to create an axial gap in the casing structure; and
moving the at least one ring of the plurality of rings in a second axial direction based on a second operating condition of the gas turbine engine;
wherein the at least one ring is moveable relative to another ring of the plurality of rings.

19. The method of claim 18 , wherein the first operating condition includes cruise engine speed and the first axial direction is downstream.

20. The method of claim 19 , wherein the second operating condition is includes transonic blade speed adjacent the casing structure and the second axial direction is upstream.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Joly Michael M
• Kuczek Andrzej Ernest
• Chaudhry Zaffir A
• Medic Gorazd
• Prasad Dilip

Classifications

• F05D2260/56

  using cams or eccentrics · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F01D9/047

  Nozzle boxes · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title