Gas turbine engine inlet assembly and method of making same

Patent metadata

Field	Value
Publication number	US-9784134-B2
Application number	US-201314036994-A
Country	US
Kind code	B2
Filing date	Sep 25, 2013
Priority date	Sep 25, 2013
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

A method of fabricating an inlet assembly for a gas turbine engine, the method including defining an intake duct of the inlet assembly between first and second space apart inlet case portions, locating at least one strut across the intake duct, each strut having a proximal end made integral to the first inlet case portion and an opposed distal end engaged in a respective strut-receiving aperture defined through the second inlet case portion, while maintaining the distal end of each strut in the respective strut-receiving aperture, adjusting the relative position of the first inlet case portion and the second inlet case portion until a predetermined throat dimension of the intake duct is obtained, and locking the adjusted relative position by attaching the second inlet case portion to each strut. An inlet assembly and gas turbine engine with inlet assembly as also disclosed.

First claim

The invention claimed is:

1. A method of fabricating an inlet assembly for a gas turbine engine, the method comprising:
defining an intake duct of the inlet assembly between first and second spaced apart inlet case portions;
locating at least one strut across the intake duct, each strut having a proximal end made integral to the first inlet case portion and an opposed distal end engaged in a respective strut-receiving aperture defined through the second inlet case portion;
while maintaining the distal end of each strut in the respective strut-receiving aperture, adjusting a penetration distance of the distal end in the respective strut-receiving aperture to adjust an axial distance between the first inlet case portion and the second inlet case portion until the axial distance corresponds to a predetermined throat dimension; and
locking the adjusted axial distance by attaching the second inlet case portion to each strut.

2. The method as defined in claim 1 , wherein attaching the second inlet case portion to each strut includes welding the distal end of each strut to the second inlet case portion.

3. The method as defined in claim 1 , further comprising making the proximal end of each strut integral to the first inlet case portion through welding.

4. The method as defined in claim 3 , further comprising butt welding the proximal end of each strut to a respective pedestal extending from a skin of the first inlet case portion.

5. The method as defined in claim 1 , further comprising welding at least another part of the gas turbine engine to one of the first inlet case portion and the second inlet case portion.

6. The method as defined in claim 1 , wherein one of the first and second inlet case portions is a structural component, the method further comprising: welding at least one bending moment control tube to the structural component.

7. An inlet assembly for a gas turbine engine, the inlet assembly comprising:
at least first and second spaced apart inlet case portions defining an intake duct therebetween; and
at least one strut extending across the intake duct and having a proximal end made integral to the first inlet case portion and a distal end engaged in a respective strut-receiving aperture defined through the second inlet case portion, a relative position of the first and second inlet case portions being fixed through a connection between each of the at least one strut and the second inlet case portion, a length of a portion of each of the at least one strut defined along a direction extending between the distal and proximal ends, wherein the length extends between the inlet case portions, and the length of the portion of each of the at least one strut controlling a throat dimension of the intake duct, wherein the length of the portion of each of the at least one strut and the throat dimension are defined along an axial direction of the inlet assembly.

8. The inlet assembly as defined in claim 7 , wherein the connection between each of the at least one strut and the second inlet case portion includes a filet-weld between the second inlet case portion and the distal end of the strut.

9. The inlet assembly as defined in claim 7 , wherein the proximal end of each of the at least one strut is butt-welded to the first inlet case portion.

10. The inlet assembly as defined in claim 7 , wherein the at least one strut includes a plurality of circumferentially spaced apart struts.

11. The inlet assembly as defined in claim 7 , wherein the at least one strut includes a single central strut having a hollow configuration configured to receive a shaft of the engine therethrough.

12. The inlet assembly as defined in claim 11 , wherein the first case portion has a torque tube of the gas turbine engine made integral thereto and extending in axial alignment with the strut away from the intake duct, the torque tube having a hollow configuration configured to receive the shaft of the engine therethrough.

13. The inlet assembly as defined in claim 12 , further comprising bending moment control tubes having an end welded to the first case portion.

14. The inlet assembly as defined in claim 7 , wherein the intake duct defines a radial inlet and the throat dimension is defined as an axial distance between the first and second inlet case portions.

15. The inlet assembly as defined in claim 7 , wherein at least one of the first and second inlet case portions has an outer skin made integral to an inner skin thereof such as to defined a double skin.

16. The inlet assembly as defined in claim 7 , wherein the intake duct defines an inlet slanted with respect to a radial direction of the gas turbine engine, and the second case portion defines an inlet fairing.

17. A gas turbine engine comprising:
an inlet assembly including at least first and second spaced apart inlet case portions defining an intake duct therebetween; and
at least one strut extending across the intake duct and having a proximal end made integral to the first inlet case portion and a distal end engaged in a respective strut-receiving aperture defined through the second inlet case portion, a relative position of the first and second inlet case portions being fixed through a connection between each of the at least one strut and the second inlet case portion, a length of a portion of each of the at least one strut defined along a direction extending between the distal and proximal ends, wherein the length extends between the inlet case portions, and the length of the portion of each of the at least one strut controlling a throat dimension of the intake duct, wherein the length of the portion of each of the at least one strut and the throat dimension are defined along an axial direction of the gas turbine engine.

18. The gas turbine engine as defined in claim 17 , wherein the connection between each of the at least one strut and the second inlet case portion includes a filet-weld between the second inlet case portion and the distal end of the strut.

19. The gas turbine engine as defined in claim 17 , wherein each of the inlet case portions is welded to at least one other component of the gas turbine engine.

20. An inlet assembly for a gas turbine engine, the inlet assembly comprising:
at least first and second spaced apart inlet case portions defining an intake duct therebetween; and
at least one strut extending across the intake duct and having a proximal end made integral to the first inlet case portion and a distal end engaged in a respective strut-receiving aperture defined through the second inlet case portion, a relative position of the first and second inlet case portions being fixed through a connection between each of the at least one strut and the second inlet case portion, a length of a portion of each of the at least one strut extending between the inlet case portions controlling a throat dimension of the intake duct;
wherein the first case portion has a torque tube of the gas turbine engine made integral thereto and extending in axial alignment with the strut away from the intake duct, the torque tube having a hollow configuration configured to receive the shaft of the engine therethrough.

21. The inlet assembly as defined in claim 20 , further comprising bending moment control tubes having an end welded to the first case portion.

Assignees

• Pratt & Whitney Canada

Inventors

• Eleftheriou Andreas

Classifications

• F02C7/042

  having variable geometry · CPC title

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F05D2230/237

  Brazing · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title