Heat shield for a fuel manifold

• US 7,926,286 B2
• Filed: 09/26/2006
• Issued: 04/19/2011
• Est. Priority Date: 09/26/2006
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Rudrapatna, Nagaraja, Oskooei, Saeid, Morenko, Oleg, Patel, Bhawan B.
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US11/535,185
• Publication Number:
  US 20080072599A1
• Time in Patent Office: 1,666 Days
• Field of Search: 607/39, 607/96, 608/00, 607/72
• US Class Current: 60/772
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02C 7/222 Fuel flow conduits, e.g. manifolds
• CPC Class Codes: Y10T 29/4932 Turbomachine making
• CPC Class Codes: Y10T 29/49391 Tube making or reforming
• CPC Class Codes: Y10T 29/49796 Coacting pieces
• CPC Class Codes: Y10T 29/49805 Shaping by direct application of fluent pressure
• CPC Class Codes: Y10T 29/49947 by applying separate fastener

Abstract

A fuel injection system for a gas turbine engine having a manifold ring, a plurality of spray tip assemblies and a heat shield including at least two heat shield segments cooperating to at least substantially surround a cross-section of the manifold ring around a circumference of the manifold ring, and detachably retained around the manifold ring through a plurality of removable fasteners.

Claims

1. A fuel injection system for a gas turbine engine, the system comprising:

a manifold ring having at least one circumferential fuel channel defined therein and at least one inlet in fluid communication with the fuel channel;

a plurality of spray tip assemblies in fluid communication with the fuel channel;

a heat shield including at least two arcuate heat shield segments cooperating to at least substantially surround a cross-section of the manifold ring around a circumference of the manifold ring, each heat shield segment defining only a portion of the cross-section and a portion of the circumference; and

a plurality of individual fasteners extending through the manifold ring which are detachably connected to the heat shield segments and detachably retaining the heat shield segments around the manifold ring, the fasteners coupling cooperating arcuate heat shield segments to each other about the cross section of the manifold ring.

2. The system as defined in claim 1, wherein the fasteners join cooperating heat shield segments without contacting the manifold ring.

3. The system as defined in claim 1, wherein the manifold ring includes a series of bores defined therethrough, each of the bores receiving a respective one of the fasteners therein.

4. The system as defined in claim 3, wherein each bore has a diameter larger than a diameter of the respective fastener received therein, and the manifold ring includes spacers cooperating with each bore to prevent the fastener from contacting the manifold ring inside the bore.

5. The system as defined in claim 4, wherein the manifold ring has a shoulder defined therein around each end of each bore, and a respective one of the spacers is snugly received in each shoulder and tightly surrounds the respective fastener.

6. The system as defined in claim 4, wherein the spacers also prevent the heat shield segments from contacting the manifold ring.

7. The system as defined in claim 1, wherein the heat shield closely surrounds each of the spray tip assembly such as to be at least almost in contact therewith.

8. The system as defined in claim 1, wherein the heat shield segments cooperate to completely surround the cross-section of some circumferential portions of the manifold ring.

9. The system as defined in claim 1, wherein the heat shield segments includes at least first and second series of heat shield segments, each of the heat shield segments extending around a portion of the circumference of the manifold ring, and corresponding segments from each of the series cooperating to at least substantially surround the cross-section of the manifold ring.

10. The system as defined in claim 9, wherein the first series includes inner heat shield segments cooperating to cover a circumferential portion of an inner circumferential surface of the manifold ring, and the second series includes outer heat shield segments cooperating to cover a circumferential portion of an outer circumferential surface of the manifold ring.

11. The system as defined in claim 10, wherein the manifold ring includes a series of radially extending bores defined therethrough, each of the bores receiving a respective one of the fasteners therein, each fastener interconnecting at least one of the inner segments and at least one of the outer segments.

12. A heat shield for an annular fuel manifold of a gas turbine engine, the heat shield comprising a plurality of heat shield segments cooperating to define a hollow ring having a substantially closed cross-section, the cross-section being defined around an entire circumference of the annular fuel manifold by at least two different ones of the heat shield segments cooperating with one another, with each of said shield segments defining only a portion of the cross-section and a portion of the circumference, and each of the heat shield segments extending around only a portion of the circumference of the ring;

a plurality of individual fasteners extending through the annular fuel manifold, the fasteners coupling cooperating arcuate heat shield segments to each other about the cross section of the annular fuel manifold.

13. The heat shield as defined in claim 12, wherein the heat shield segments overlap at selected points of the circumference of the ring such that the cross-section at the selected points is closed.

14. The heat shield as defined in claim 12, wherein the plurality of heat shield segments include inner segments and outer segments, each of the inner segment cooperating with a corresponding one of the outer segments to define the cross-section, the inner segments cooperating to define an inner circumferential surface of the ring, and the outer segments cooperating to define an outer circumferential surface of the ring.

15. The heat shield as defined in claim 12, wherein the heat shield segments are made of one of stainless steel and an alloy of nickel, chromium and iron.

16. A method of attaching a heat shield to a gas turbine fuel manifold ring, the method comprising:

placing at least first and second complementary arcuate heat shield portions around the gas turbine fuel manifold ring such that the heat shield portions cooperate to at least substantially surround a cross-section of the manifold ring about an entire circumference of the manifold ring;

each of said shield portions defining only a portion of the cross-section and a portion of the circumference;

providing a plurality of individual fasteners extending through the manifold ring and coupling the complementary heat shield portions to each other about the cross section of the manifold ring; and

retaining each of the heat shield portions over the manifold ring with at least one of the fasteners.

17. The method as defined in claim 16, wherein placing the at least first and second heat shield portions includes placing the first and second heat shield portions around the manifold ring such that the first and second heat shield portions cooperate to surround the major part of the cross-section about a portion of the circumference, and placing at least third and fourth heat shield portions around the manifold ring such that the at least third and fourth heat shield portions cooperate to cover the at least major part of the cross-section about a remainder of the circumference.

18. The method as defined in claim 16, wherein retaining each of the heat shield portions includes passing the removable fastener through a bore defined in the manifold ring and interconnecting at least two of the heat shield portions covering different surfaces of the manifold ring with the fastener.

19. The method as defined in claim 18, further including preventing the fastener from contacting the manifold ring inside the bore.