Heatshield assembly with double lap joint for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10100670-B2
Application number	US-201414893801-A
Country	US
Kind code	B2
Filing date	Jun 12, 2014
Priority date	Jun 14, 2013
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A heat shield assembly for a gas turbine engine includes a first heat shield segment defined about an axis and a second heat shield segment defined about the axis. A double circumferential lap joint is defined between the first heat shield segment and the second heat shield segment.

First claim

What is claimed is:

1. A heat shield assembly for a gas turbine engine, the assembly comprising:
a first heat shield segment defined about an axis;
a second heat shield segment defined about said axis;
a double circumferential lap joint between said first heat shield segment and said second heat shield segment;
wherein said double circumferential lap joint is defined by an outer cover and an alignment tab mounted to said first heat shield segment;
wherein said outer cover and said alignment tab extend beyond an edge of said first heat shield segment; and
wherein said alignment tab includes a curved end which curves away from said outer cover.

2. The assembly as recited in claim 1 , wherein said outer cover and said alignment tab form an interference fit with said second heat shield segment.

3. The assembly as recited in claim 1 , wherein said outer cover includes a radiused end.

4. The assembly as recited in claim 1 , wherein said alignment tab is a plate.

5. The assembly as recited in claim 1 , wherein said outer cover is generally L-shaped in cross-section.

6. The assembly as recited in claim 5 , wherein said outer cover includes an axial end radially displaced from said first heat shield segment.

7. The assembly as recited in claim 6 , wherein said axial end includes a curved end that curves away from said first heat shield segment.

8. The assembly as recited in claim 1 , wherein said outer cover is generally serpentine shaped.

9. A case assembly for a gas turbine engine, the assembly comprising:
an outer air seal flange interface defined about an engine axis;
a first heat shield segment defined about said axis radially outboard of said outer air seal flange interface;
a second heat shield segment defined about said axis radially outboard of said outer air seal flange interface;
a double circumferential lap joint between said first heat shield segment and said second heat shield segment;
a fastener mounted to said outer air seal flange interface and said first heat shield segment;
wherein said double circumferential lap joint is defined by an outer cover and an alignment tab mounted to said first heat shield segment;
wherein said outer cover and said alignment tab extend beyond an edge of said first heat shield segment; and
wherein said alignment tab includes a curved end which curves away from said outer cover.

10. The assembly as recited in claim 9 , further comprising a flange which extends from said outer air seal flange interface, wherein said flange is sandwiched between said first heat shield segment, said second heat shield segment and said outer cover.

11. The assembly as recited in claim 10 , wherein said first heat shield segment, said second heat shield segment and said outer cover define an interference fit with said flange to generate a pinching preload.

12. The assembly as recited in claim 9 , further comprising
a heat shield retainer assembly that is mounted to a second outer air seal flange interface; and
said first heat shield segment, said second heat shield segment and said heat shield retainer assembly surround said outer air seal flange interface and said second outer air seal flange interface.

13. The assembly as recited in claim 9 , further comprising
a heat shield retainer assembly that is mounted to a second outer air seal flange interface; and
said first heat shield segment, said second heat shield segment and said heat shield retainer assembly bridge said outer air seal flange interface and said second outer air seal flange interface.

14. A method of mounting a heat shield assembly within a bleed air cavity of a gas turbine engine, the method comprising:
surrounding an outer air seal flange interface with a first heat shield segment and a second heat shield segment;
interfacing the first heat shield segment and the second heat shield segment at a double circumferential lap joint to provide a sliding seal;
wherein said double circumferential lap joint is defined by an outer cover and an alignment tab mounted to said first heat shield segment;
wherein said outer cover and said alignment tab extend beyond an edge of said first heat shield segment; and
wherein said alignment tab includes a curved end which curves away from said outer cover.

15. The method as recited in claim 14 , further comprising:
defining a circumferential thermal expansion gap between the first heat shield segment and the second heat shield segment; and
bridging the circumferential thermal expansion gap with the double circumferential lap joint.

Assignees

• United Technologies Corp

Inventors

• Leslie Nicholas R
• Tatman Neil L

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D25/08

  Cooling (of machines or engines in general F01P); Heating; Heat-insulation (of blade-carrying members, of blades F01D5/00) · CPC title

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F01D25/145 Primary

  Thermally insulated casings · CPC title