Tube fed tangential on-board injector for gas turbine engine

Patent metadata

Field	Value
Publication number	US-9777634-B2
Application number	US-201414479566-A
Country	US
Kind code	B2
Filing date	Sep 8, 2014
Priority date	Sep 12, 2013
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

A tangential on-board injector assembly for a gas turbine engine includes an annular housing including a plenum. A plurality of discrete tubes is fluidly connected to the plenum and is configured to provide a cooling fluid to the annular housing.

First claim

What is claimed is:

1. A tangential on-board injector assembly for a gas turbine engine comprising:
an annular housing including a plenum, and a flange extending radially outward from the annular housing, and the annular housing includes a circumferential array of tangential on-board injector vanes arranged downstream from the plenum;
a diffuser case secured to the flange; and
a plurality of discrete tubes fluidly connected to the plenum and configured to provide a cooling fluid to the annular housing, wherein the tubes each have an end arranged radially interiorly of the diffuser case.

2. The assembly according to claim 1 , comprising a circumferential array of turbine vanes secured to the flange.

3. The assembly according to claim 2 , comprising pins removably securing an inner diameter platform of the turbine vanes to the flange.

4. The assembly according to claim 1 , wherein the annular housing includes a circumferential array of apertures, and the tubes each include a neck received in and sealed relative to the respective aperture.

5. A gas turbine engine comprising:
a combustor section arranged fluidly between a compressor section and a turbine section;
a cooling fluid source configured to provide a cooling fluid;
a tangential on-board injector having an annular housing including a plenum;
a diffuser case secured to the annular housing and arranged about a combustor housing in the combustor section; and
a plurality of discrete tubes fluidly connect the cooling fluid source and configured to provide a tangential on-board injector flow to the plenum, wherein the tubes each have an end arranged radially interiorly of the diffuser case.

6. The gas turbine engine according to claim 5 , wherein the turbine section includes a rotor supporting turbine blades, the tangential on-board injector configured to supply the cooling fluid to the rotor.

7. The gas turbine engine according to claim 5 , wherein the compressor section provides a bleed air that corresponds to the cooling fluid.

8. The gas turbine engine according to claim 7 , wherein the cooling fluid source includes a heat exchanger.

9. The gas turbine engine according to claim 5 , wherein the diffuser case is configured to receive a diffuser flow, the diffuser flow discrete from the tangential on-board injector flow.

10. The gas turbine engine according to claim 5 , comprising a flange extending radially outward from the annular housing, and a circumferential array of turbine vanes secured to the flange.

11. The gas turbine engine according to claim 10 , comprising pins removably securing an inner diameter platform of the turbine vanes to the flange.

12. The gas turbine engine according to claim 5 , wherein the annular housing includes a circumferential array of apertures, and the tubes each include a neck received in and sealed relative to the respective aperture, and the annular housing includes a circumferential array of tangential on-board injector vanes arranged downstream from the plenum.

13. The gas turbine engine according to claim 5 , comprising a bearing supporting the rotor for rotation relative to an engine static structure, the bearing arranged in a bearing compartment that is configured to receive a buffer flow, the buffer flow discrete from the tangential on-board injector flow.

14. The gas turbine engine according to claim 5 , wherein the diffuser case is configured to receive a diffuser flow, and a bearing supporting the rotor for rotation relative to an engine static structure, the bearing arranged in a bearing compartment that is configured to receive a buffer flow, the diffuser flow and the buffer flow discrete from the tangential on-board injector flow.

15. A method of supply fluid to a turbine rotor, comprising the steps of:
supplying a cooling fluid to a tangential on-board injector through multiple discrete apertures at a location radially interiorly of a diffuser case that surrounds a combustor.

16. The method according to claim 15 , wherein multiple discrete tubes fluidly connect a cooling fluid source to the tangential on-board injector.

17. The method according to claim 15 , comprising the step of supplying a diffuser flow and a buffer flow respectively to the diffuser case and a bearing compartment, the diffuser flow and the buffer flow separate from the cooling fluid supply to the tangential on-board injector.

Assignees

• United Technologies Corp

Inventors

• Drake Christopher
• Lyons Christopher B

Classifications

• F01D5/082

  on the side of the rotor disc · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F02C7/22

  Fuel supply systems · CPC title