Interlocking rotor assembly with thermal shield

Patent metadata

Field	Value
Publication number	US-10309251-B2
Application number	US-201414770832-A
Country	US
Kind code	B2
Filing date	Mar 10, 2014
Priority date	Mar 15, 2013
Publication date	Jun 4, 2019
Grant date	Jun 4, 2019

Abstract

A rotor assembly includes a first rotor, a second rotor mounted on the first rotor and co-rotatable there with, and a thermal shield interlocked with the second rotor for co-rotation there with.

First claim

What is claimed is:

1. A rotor assembly comprising:
a first rotor;
a second rotor mounted on the first rotor and co-rotatable there with; and
a thermal shield interlocked with the second rotor for co-rotation there with, wherein the first rotor has a first outer diameter and the second rotor has a second outer diameter that is smaller than the first outer diameter, and the second rotor includes at least one radially-extending tab and the thermal shield includes at least one radially-extending tab circumferentially interlocked with the at least one radially-extending tab of the second rotor.

2. The rotor assembly as recited in claim 1 , wherein the at least one radially-extending tab of the second rotor includes a step.

3. The rotor assembly as recited in claim 1 , wherein the second rotor includes a plurality of radially-extending circumferentially-spaced tabs and the thermal shield includes a plurality of radially-extending circumferentially-spaced tabs circumferentially interlocked with the plurality of radially-extending circumferentially-spaced tabs of the second rotor.

4. The rotor assembly as recited in claim 3 , wherein the first rotor includes a plurality of radially-extending circumferentially-spaced tabs and the plurality of radially-extending circumferentially-spaced tabs of the second rotor are circumferentially interlocked with the plurality of radially-extending circumferentially-spaced tabs of the first rotor.

5. The rotor assembly as recited in claim 4 , wherein the plurality of radially-extending circumferentially-spaced tabs of the thermal shield are circumferentially aligned with the plurality of radially-extending circumferentially-spaced tabs of the first rotor.

6. The rotor assembly as recited in claim 4 , wherein the plurality of radially-extending circumferentially-spaced tabs of the thermal shield are axially trapped between the second rotor and the plurality of radially-extending circumferentially-spaced tabs of the first rotor.

7. The rotor assembly as recited in claim 1 , wherein the second rotor includes an axially-facing pocket, and a portion of the thermal shield is seated in the axially-facing pocket.

8. The rotor assembly as recited in claim 1 , wherein the thermal shield is a continuous ring.

9. A gas turbine engine comprising:
a first rotor;
a second rotor mounted on the first rotor and co-rotatable there with; and
a thermal shield interlocked with the second rotor for co-rotation there with, wherein the first rotor has a first outer diameter and the second rotor has a second outer diameter that is smaller than the first outer diameter, and the second rotor includes at least one radially-extending tab and the thermal shield includes at least one radially-extending tab circumferentially interlocked with the at least one radially-extending tab of the second rotor.

10. A method of assembling a rotor assembly, the method comprising:
interlocking a thermal shield with a second rotor for co-rotation there with, the second rotor being mounted on a first rotor and co-rotatable there with, wherein the first rotor has a first outer diameter and the second rotor has a second outer diameter that is smaller than the first outer diameter, and the second rotor includes at least one radially-extending tab and the thermal shield includes at least one radially-extending tab circumferentially interlocked with the at least one radially-extending tab of the second rotor.

11. The method as recited in claim 10 , wherein the interlocking includes mounting the thermal shield on the second rotor and rotating the thermal shield to circumferentially misalign the at least one radially-extending tab on the thermal shield with the at least one radially-extending tab on the second rotor.

12. The method as recited in claim 11 , wherein the at least one radially-extending tab on the thermal shield is axially offset with respect to the at least one radially-extending tab on the second rotor.

13. The method as recited in claim 12 , wherein the interlocking includes moving the second rotor relative to the thermal shield to axially align, and circumferentially interlock, the at least one radially-extending tab on the thermal shield with the at least one radially-extending tab on the second rotor.

Assignees

• United Technologies Corp

Inventors

• Sandoval Jonathan Perry
• Partyka Julian

Classifications

• F01D5/025 Primary

  Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00) · CPC title

• F01D25/08 Primary

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

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F01D5/066

  Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps · CPC title

• F01D5/3015

  with side plates · CPC title