Full hoop blade track with internal cooling channel

Patent metadata

Field	Value
Publication number	US-11092014-B1
Application number	US-202016841052-A
Country	US
Kind code	B1
Filing date	Apr 6, 2020
Priority date	Apr 6, 2020
Publication date	Aug 17, 2021
Grant date	Aug 17, 2021

Abstract

A blade track system includes a blade track configured to be positioned around a plurality of blades of a gas turbine engine. The blade track includes: a full-hoop body, an inlet port, and an exit port. The full-hoop body includes an outer surface and an inner surface. The inner surface defines an internal cooling channel extending within the full-hoop body. The inlet port and the exit port are each integrated with the full-hoop body and in fluid communication with the internal cooling channel.

First claim

What is claimed is:

1. A blade track system comprising:
a blade track configured to be positioned around a plurality of blades of a gas turbine engine, the blade track comprising:
a full-hoop body comprising an outer surface and an inner surface, the inner surface defining an internal cooling channel extending within the full-hoop body;
an inlet port integrated with the full-hoop body and in fluid communication with the internal cooling channel, the inlet port configured to supply a coolant from external the hoop body to within the internal cooling channel; and
an exit port integrated with the full-hoop body and in fluid communication with the internal cooling channel, the exit port configured to discharge the coolant to outside the full-hoop body.

2. The blade track system of claim 1 , wherein the inlet port radially extends from the inner surface to a radially outward surface portion of the outer surface of the full-hoop body.

3. The blade track system of claim 1 , wherein the exit port radially extends from the inner surface to a radially outward surface portion of the outer surface of the full-hoop body.

4. The blade track system of claim 1 , wherein the exit port axially extends from the inner surface to a side surface portion of the outer surface of the full hoop body.

5. The blade track system of claim 1 , wherein the blade track further comprises a plurality of inlet ports comprising the inlet port.

6. The blade track system of claim 5 , wherein the plurality of inlet ports are circumferentially positioned equidistant from each other about the full-hoop body.

7. The blade track system of claim 5 , wherein the blade track further comprises a plurality of exit ports comprising the exit port.

8. The blade track system of claim 7 , wherein the plurality of exit ports are circumferentially positioned equidistant from each other about the full-hoop body.

9. The blade track system of claim 7 , wherein the plurality of inlet ports and the plurality of exit ports are alternatingly positioned about the full-hoop body.

10. The blade track system of 7 , wherein the plurality of inlet ports comprises exactly three inlet ports and the plurality of exit ports comprises exactly three exit ports.

11. The blade track system of claim 1 , wherein the internal cooling channel circumferentially extends entirely through the full-hoop body.

12. The blade track system of claim 1 , wherein the inner surface comprises at least one thickening portion circumferentially extending in the internal cooling channel.

13. The blade track system of claim 1 , further comprising an inlet tube coupled to a radially outward surface portion of an outer surface of the blade track, the inlet tube comprising an inner lumen in fluid communication with the inlet port.

14. The blade track system of claim 13 , wherein the inlet tube radially extends from the radially outward surface portion to an engine casing surrounding the blade track, the blade track and the engine casing defining a circumferential cavity therebetween.

15. The blade track system of claim 14 , further comprising: a forward seal plate providing a forward boundary of the circumferential cavity, and at least one side port axially extending through the forward seal plate, the at least one side port configured to permit a leakage fluid to flow from external to within the circumferential cavity.

16. A system comprising:
a blade track system comprising a blade track comprising:
a full-hoop body surrounding a plurality of blades of a gas turbine engine; and
an internal cooling channel extending within the full-hoop body, and

a cooling system configured to supply a coolant over a coolant flow path to the internal cooling channel in the full-hoop body, the coolant flow path isolated from a main fluid flow path of the gas turbine engine extending through the plurality of blades.

17. The system of claim 16 , wherein the coolant comprises a modulated coolant, and wherein the cooling system further comprises a valve section configured to output the modulated coolant toward the internal cooling channel.

18. The system of claim 17 , wherein the valve section is configured to receive a low pressure air from a compressor section of the gas turbine engine.

19. The system of claim 16 , wherein the blade track system defines a leakage flow path extending in a circumferential cavity between the blade track and a casing, the coolant flow path further isolated from the leakage flow path.

20. A blade track cooling method comprising:
flowing a main fluid over a main fluid flow path through a plurality of turbine blades surrounded by a blade track; and
flowing a coolant over a coolant flow path through an internal cooling channel of the blade track, the coolant flow path isolated from the main fluid flow path.

Assignees

• Rolls Royce Corp

Inventors

• Moga Corina
• Lambert Tony
• Starr Shaling

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title

• F05D2240/55

  Seals · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F01D11/24

  by selectively cooling-heating stator or rotor components · CPC title