Additively manufactured booster splitter with integral heating passageways

Patent metadata

Field	Value
Publication number	US-11053848-B2
Application number	US-201815878759-A
Country	US
Kind code	B2
Filing date	Jan 24, 2018
Priority date	Jan 24, 2018
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A booster splitter for a gas turbine engine and a method of additively manufacturing the booster splitter are provided. The booster splitter includes an annular outer wall defining an internal fluid passageway in fluid communication with a fluid supply and terminating in discharge ports that eject a flow of fluid into the compressor section of the gas turbine engine. The internal fluid passageway may also be in fluid communication with heating plenums of a first plurality of airfoils for heating those airfoils.

First claim

What is claimed is:

1. A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
an annular inner wall defining a radially outer boundary of a compressor flow path defined through a compressor section of the gas turbine engine;
an annular outer wall spaced apart from the annular inner wall along the radial direction, the annular outer wall being curved to meet with the annular inner wall at a forward end, the forward end defining an inlet to the compressor flow path;
an annular bulkhead spanning between the annular inner wall and the annular outer wall substantially along the radial direction, the bulkhead defining an inlet port;
a fluid passageway defined within the annular outer wall, the fluid passageway extending from the inlet port, into the bulkhead, radially outward to the outer wall, and through the annular outer wall towards the inlet defined by the forward end, the annular outer wall proximate to an exterior surface of the gas turbine engine; and
a fluid supply in fluid communication with the fluid passageway for providing a flow of fluid through the fluid passageway.

2. The gas turbine engine of claim 1 , wherein the outer wall defines heat exchange fins within the fluid passageway.

3. The gas turbine engine of claim 1 , further comprising:
an inlet conduit providing fluid communication between the fluid supply and the inlet port.

4. The gas turbine engine of claim 1 , wherein the outer wall defines:
an annular discharge plenum extending circumferentially proximate the forward end of the outer wall, the outer wall further defining a plurality of discharge ports spaced circumferentially proximate the forward end and being in fluid communication with the discharge plenum.

5. The gas turbine engine of claim 4 , wherein the discharge ports are positioned within the inlet for discharging the flow of fluid into the compressor flow path.

6. The gas turbine engine of claim 1 , wherein the gas turbine engine comprises a first plurality of airfoils spaced circumferentially within the compressor flow path, each of the first plurality of airfoils defining a heating plenum and bleed air ports.

7. The gas turbine engine of claim 1 , wherein the fluid supply is the compressor section of the gas turbine engine.

8. The gas turbine engine of claim 7 , wherein an inlet conduit provides fluid communication between a high pressure compressor and one or more inlet ports defined by the outer wall.

9. The gas turbine engine of claim 1 , wherein the fluid passageway defines a serpentine pattern within the outer wall.

10. The gas turbine engine of claim 1 , wherein the outer wall defines multiple fluid passageways spaced apart along a circumferential direction of the outer wall, each of the multiple fluid passageways being in fluid communication with the fluid supply.

11. The gas turbine engine of claim 1 , wherein the gas turbine engine comprises an annular nacelle spaced apart from the outer wall along the radial direction to define a bypass passageway therebetween, and wherein the inner wall and the outer wall split a primary flow of air into a flow of bypass air and a flow of core air.

12. The gas turbine engine of claim 1 , wherein the outer wall, the inner wall, or both are integrally formed as a single monolithic component.

13. The gas turbine engine of claim 1 , wherein the inner wall and the outer wall comprise a plurality of layers formed by:
depositing a layer of additive material on a bed of an additive manufacturing machine; and
selectively directing energy from an energy source onto the layer of additive material to fuse a portion of the additive material.

14. The gas turbine engine of claim 1 , wherein the passageway is surrounded and confined by the outer wall.

15. The gas turbine engine of claim 1 , wherein the annular bulkhead defines a plurality of inlet ports, the inlet ports spaced circumferentially about the bulkhead, each of the inlet ports fluidly coupled to the compressor section through a separate inlet conduit.

16. A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a splitter positioned at a forward end of a core engine and defining a core inlet, the spotter configured for splitting a primary flow of air between the core inlet and bypass airflow passageway, the bypass airflow passageway defined between the core engine and art annular nacelle, the splitter comprising:
an annular inner wall defining a radially outer bounder of a compressor flow path defined through a compressor section of the core engine;
an annular outer wall spaced apart from the annular inner wall along the direction, the annular outer wall being curved to meet with the annular inner wall at a forward end, the forward end defining the core inlet;
an annular bulkhead spanning between the annular inner and the annular outer wall substantially along the radial direction, the bulkhead defining an inlet port;
a fluid passageway defined within the annular outer wall, wherein the fluid passageway extends from the inlet port, into the bulkhead, radially outward to the outer wall, and through the annular outer wall towards the core inlet defined by the forward end, the annular outer wall proximate to an exterior surface of the gas turbine engine; and
a fluid supply in fluid communication with the fluid passageway for providing a flow of fluid to the fluid passageway.

17. The gas turbine engine of claim 16 , wherein the outer wall defines heat exchange fins within fluid passageway.

18. The gas turbine engine of claim 14 , further comprising: an inlet conduit providing fluid communication between the fluid supply and the inlet port.

19. The gas turbine engine of claim 16 , wherein the gas turbine engine comprises a first plurality of airfoils spaced circumferentially within the compressor section, each of the first plurality of airfoils defining a heating plenum and bleed air ports.

20. A method of manufacturing the gas turbine engine according to claim 1 , the method comprising:
depositing a layer of additive material on a bed of an additive manufacturing machine; and
selectively directing energy from an energy source onto the layer of additive material to fuse a portion of the additive material and form at least one of: the annular inner wall or the annular outer wall.

Assignees

• Gen Electric

Inventors

• Kray Nicholas Joseph
• Dorbala Sreekanth Kumar
• Jain Nitesh
• Sharma Prashant

Classifications

• F05D2230/31

  Layer deposition · CPC title

• F02C3/04 Primary

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F05D2230/22

  by sintering · CPC title

• F05D2230/234

  Laser welding · CPC title

• F01D25/02

  De-icing means for engines having icing phenomena · CPC title