Clearance control for gas turbine engine section

Patent metadata

Field	Value
Publication number	US-9255489-B2
Application number	US-201213366424-A
Country	US
Kind code	B2
Filing date	Feb 6, 2012
Priority date	Feb 6, 2012
Publication date	Feb 9, 2016
Grant date	Feb 9, 2016

Abstract

A section of a gas turbine engine includes a case structure having a first coefficient of thermal expansion. A continuous, ring-shaped liner has a second coefficient of thermal expansion that is substantially different than the first coefficient of thermal expansion. A flexible leaf member operatively connects the liner to the case structure. The leaf member is configured to accommodate diametrical change in the liner throughout various fan section operating temperatures.

First claim

What is claimed is:

1. A section of a gas turbine engine comprising:
a case structure having a first coefficient of thermal expansion;
a continuous ring-shaped liner having a second coefficient of thermal expansion that is substantially different than the first coefficient of thermal expansion; and
a flexible leaf member having first and second portions mechanically affixed and secured respectively to the liner and to the case structure such that the first and second portions are respectively immovable with respect to the liner and to the case structure, the leaf member configured to accommodate diametrical change in the liner throughout various section operating temperatures, wherein the first and second portions are spaced from one another in a circumferential direction that corresponds to a blade rub direction.

2. The section according to claim 1 , a blade arranged within the case structure and having a third coefficient of thermal expansion that is substantially similar to the second coefficient of thermal expansion, the continuous ring-shaped liner surrounding the blade, a desired radial tip clearance between the liner and the blade, and the flexible leaf member maintaining the desired radial tip clearance throughout various section operating temperatures.

3. The section according to claim 2 , wherein the case structure includes a composite case, and the blade is a metallic fan blade.

4. The section according to claim 3 , wherein the case structure includes a honeycomb structure operatively connected radially inward of and to the composite case.

5. The section according to claim 4 , wherein the case structure includes a composite septum interconnected to the honeycomb by an adhesive.

6. The section according to claim 5 , comprising a rub strip supported on and radially inward of the liner between the liner and the blade.

7. The section according to claim 3 , wherein the blade and the liner are constructed from the same series aluminum alloy.

8. The section according to claim 1 , wherein the first and second portions are provided on opposing ends of the leaf member.

9. The section according to claim 1 , wherein the first portion is provided on an end of the leaf member, and the second portion is provided on a central part of the leaf member.

10. The section according to claim 9 , wherein the first portion includes a leg and a foot, the end provided by the foot.

11. The section according to claim 10 , wherein the leg is angled in the circumferential direction.

12. The section according to claim 1 , wherein the leaf member includes overlapping straps arranged generally in an X-shaped pattern, the straps providing the first and second portions.

13. The section according to claim 1 , wherein leaf member is provided an annular structure with undulations about its circumference, the undulations provided peaks and valleys corresponding to the first and second portions.

14. The section according to claim 1 , wherein the leaf member includes discrete leafs separated from one another and oriented in the circumferential direction.

Assignees

• Ditomasso John C
• Robertson Thomas J
• Reinhardt Gregory E
• United Technologies Corp

Inventors

• Ditomasso John C
• Robertson Thomas J
• Reinhardt Gregory E

Classifications

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F05D2250/184

  sinusoidal · CPC title

• F01D11/18 Primary

  using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title

• F01D11/16

  by self-adjusting means (F01D11/12 takes precedence) · CPC title

• F05D2300/501

  Elasticity · CPC title