# US 10,371,005 B2 · Multi-ply heat shield assembly with integral band clamp for a gas turbine engine

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- Number: US 10,371,005 B2
- Document ID: US10371005B2
- Status: Granted
- Kind: B2
- Application number: 15/215,132
- Filed: 2016-07-20
- Published: 2018-01-25
- Granted: 2019-08-06
- Earliest claimed: 2016-07-20
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Jeffrey D Ponchak; Mark J Rogers; James R Plante
- Web page: https://patentgrep.com/patent/US10371005B2

## CPC

- F01D 25/145: {Thermally insulated casings}
- F01D 25/24: 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})
- F01D 25/265: {Vertically split casings; Clamping arrangements therefor}
- F05D 2220/32: in gas turbines
- F05D 2230/60: Assembly methods
- F05D 2260/231: Preventing heat transfer
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A heat shield assembly for a gas turbine engine includes a first heat shield ply assembly defined about an axis; a second heat shield ply assembly defined about the axis, the second heat shield ply assembly receivable at least partially over the first heat shield assembly and a band clamp mounted to the second heat shield assembly to circumferentially retain the first heat shield ply assembly and the second heat shield ply assembly.

## Claims

### Claim 1

A gas turbine engine comprising:
a first case segment with a first flange;
a second case segment with a second flange and a third flange, a first interface defined by the second flange and the first flange;
a first multiple of bolts that extend through the first interface;
a third case segment with a fourth flange, a second interface defined by the fourth flange and the third flange;
a second multiple of bolts that extend through the second interface;
a heat shield assembly that extends at least partially around the first multiple of bolts and the second multiple of bolts, wherein the heat shield assembly comprises:
a first heat shield ply assembly defined about an axis;
a second heat shield ply assembly defined about the axis, the second heat shield ply assembly receivable at least partially over the first heat shield assembly; and
a band clamp mounted to the second heat shield assembly to circumferentially retain the first heat shield ply assembly and the second heat shield ply assembly.

### Claim 2 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the heat shield assembly seals in an axial and a radial direction.

### Claim 3 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the heat shield assembly spans the second case segment.

### Claim 4 (depends on 1)

The gas turbine engine as recited in claim 1, wherein the first multiple of bolts includes first bolt heads that are directed in first direction and the second multiple of bolt heads extend in a second direction opposite the first direction, the heat shield surrounds the first bolt heads and the second bolt heads.