Compressor rotor heat shield

Patent metadata

Field	Value
Publication number	US-9441639-B2
Application number	US-201313892414-A
Country	US
Kind code	B2
Filing date	May 13, 2013
Priority date	May 13, 2013
Publication date	Sep 13, 2016
Grant date	Sep 13, 2016

Abstract

A heat shield for a rotor in a turbine engine is provided. The heat shield includes a main body having a first pair of recesses. The first pair of recesses is adapted to fit around a portion of one or more rotor blades or between two axially adjacent rotor wheels. The first pair of recesses limits axial and radial movement of the heat shield by interaction with the rotor blades or by interaction with the two axially adjacent rotor wheels. The first pair of recesses engage axially adjacent rotor blades or the axially adjacent rotor wheels. The heat shield protects the rotor from hot gas.

First claim

The invention claimed is:

1. A heat shield for a rotor in a turbine engine, the heat shield comprising:
a main body having a first pair of recesses, the first pair of recesses adapted to fit around a portion of one or more rotor blades, the first pair of recesses limiting axial and radial movement of the heat shield by interaction with the rotor blades, the first pair of recesses engaging axially adjacent rotor blades; and
wherein the heat shield protects the rotor from hot gas, and the heat shield is retained on the rotor by engagement or connection to a rotor blade and without connection of the heat shield to a rotor wheel.

2. The heat shield of claim 1 , the heat shield further comprising:
a pin adapted to fit in a hole of the main body; the pin adapted to be driven into a rotor blade recess;
wherein the pin limits relative rotation between the rotor blade recess and the heat shield.

3. The heat shield of claim 1 , further comprising:
one or more seal wires disposed on the first pair of recesses, the seal wires configured to limit gas flow between the rotor blades and the heat shield.

4. The heat shield of claim 1 , wherein the heat shield is comprised of a plurality of heat shield segments circumferentially disposed around the rotor of a compressor.

5. The heat shield of claim 1 , further comprising a concave section formed in a radially inward facing surface of the main body, the concave section configured to reduce weight of the heat shield.

6. The heat shield of claim 1 , further comprising a shiplap section located at each end of the heat shield, the shiplap section configured to overlap an adjacent heat shield, and
wherein the shiplap section is configured to reduce leakage between the end of the heat shield.

7. The heat shield of claim 1 , the heat shield further comprising at least one of a heat shield tab or a heat shield notch configured to engage a rotor blade notch or a rotor blade tab, respectively;
wherein tab/notch interaction limits relative circumferential motion between the heat shield and the one or more rotor blades.

8. A compressor for a gas turbine, the compressor comprising a rotor having a plurality of rotor wheels and each rotor wheel having a plurality of rotor blades, the compressor comprising:
a heat shield having a main body, the main body having a first pair of recesses, the first pair of recesses adapted to fit around a portion of one or more rotor blades, the first pair of recesses limiting axial and radial movement of the heat shield by interaction with the rotor blades, the first pair of recesses engaging axially adjacent rotor blades; and
wherein the heat shield protects the rotor from hot gas, and the heat shield is retained on the rotor by engagement with, or connection to, the rotor blade and without connection of the heat shield to the rotor wheel.

9. The compressor of claim 8 , further comprising at least one of:
one or more seal wires disposed on the first pair of recesses, the seal wires configured to limit gas flow between the rotor blades and the heat shield, or
a shiplap section located at each end of the heat shield, the shiplap section configured to overlap an adjacent heat shield, and wherein the shiplap section is configured to reduce leakage between the end of the heat shield.

10. The compressor of claim 8 , the heat shield further comprising:
a pin adapted to fit in a hole of the main body; the pin adapted to be driven into a rotor blade recess; and
wherein the pin limits relative rotation between the rotor blade recess and the heat shield.

11. The compressor of claim 8 , wherein the heat shield is comprised of a plurality of heat shield segments circumferentially disposed around the rotor.

12. The compressor of claim 8 , further comprising a concave section formed in a radially inward facing surface of the main body, the concave section configured to reduce weight of the heat shield.

13. The compressor of claim 8 , the heat shield further comprising at least one of a heat shield tab or a heat shield notch configured to engage a rotor blade notch or a rotor blade tab, respectively;
wherein tab/notch interaction limits relative circumferential motion between the heat shield and the one or more rotor blades.

Assignees

• Gen Electric

Inventors

• Hafner Matthew Troy

Classifications

• F04D29/322

  Blade mountings · CPC title

• F04D29/5853 Primary

  heat insulation or conduction · CPC title