Rotatable and adjustable hose for gas turbine

Patent metadata

Field	Value
Publication number	US-10711697-B2
Application number	US-201715459544-A
Country	US
Kind code	B2
Filing date	Mar 15, 2017
Priority date	Mar 15, 2017
Publication date	Jul 14, 2020
Grant date	Jul 14, 2020

Abstract

A gas turbine engine system includes a fuel delivery circuit configured to convey fuel, a combustion chamber configured to combust the fuel, and a flexible hose that fluidly connects the fuel delivery circuit to the combustion chamber. The flexible hose includes a combustion chamber connector portion attached to the combustion chamber, a fuel delivery circuit connector portion attached to the fuel delivery circuit, and a central flexible portion connecting the first connector portion to the second connector portion. The central flexible portion is made of a flexible material. In addition, the fuel delivery circuit connector portion includes a pivotal assembly with an adjustable end that is pivotal relative to a central longitudinal axis of the central flexible portion of the flexible hose when the central flexible portion is in a straight condition.

First claim

What is claimed is:

1. A gas turbine engine system comprising:
a fuel delivery circuit configured to convey fuel;
a combustion chamber configured to combust the fuel; and
a flexible hose that fluidly connects the fuel delivery circuit to the combustion chamber, the flexible hose comprising:
a combustion chamber connector portion attached to the combustion chamber;
a fuel delivery circuit connector portion attached to the fuel delivery circuit; and
a central flexible portion connecting the combustion chamber connector portion to the fuel delivery circuit connector portion, the central flexible portion defining a central longitudinal axis when the central flexible portion is in a straight condition,

wherein the central flexible portion is made of a flexible material;
wherein the fuel delivery circuit connector portion comprises a pivotal assembly with a fixed portion, an adjustable portion, and a securing ring on an exterior of the adjustable portion, the securing ring being configured to engage the fixed portion to secure the adjustable portion in place within the pivotal assembly;
wherein the adjustable portion is pivotal relative to the central longitudinal axis while the adjustable portion is secured in place by the securing ring;
wherein the adjustable portion forms part of a flow path for the fuel, and
wherein the central flexible portion has a first minimum bending radius that is greater than a second minimum bending radius of the pivotal assembly.

2. The gas turbine engine system of claim 1 , wherein the adjustable portion of the pivotal assembly is also rotatable around the central longitudinal axis.

3. The gas turbine engine system of claim 1 , wherein the adjustable portion is configured to be received within the fixed portion, the adjustable portion being free to pivot around a pivot point within the fixed portion, and wherein the adjustable portion and the fixed portion are configured so that when the adjustable portion is received within the fixed portion and secured by the securing ring, the flow path for the fuel is continuous through the adjustable portion and the fixed portion.

4. The gas turbine engine system of claim 3 , wherein the pivotal assembly further comprises a seal positioned between the adjustable portion and the fixed portion, the seal being configured to prevent a leakage of fluid between the adjustable portion and the fixed portion regardless of an orientation of the adjustable portion relative to the fixed portion.

5. The gas turbine engine system of claim 4 , wherein the adjustable portion is mechanically locked to the fixed portion.

6. The gas turbine engine system of claim 1 , wherein the combustion chamber comprises a plurality of cans and the flexible hose is one of a plurality of flexible hoses that connect the cans to the fuel delivery circuit, each of the plurality of flexible hoses comprising respective combustion chamber connection portions, fuel delivery circuit connector portions and central flexible portions, wherein each of the central flexible portions is made of the flexible material, and the respective fuel delivery circuit connector portions each comprise a respective pivotal assembly, each pivotal assembly comprising a respective adjustable portion that is pivotal relative to a respective central longitudinal axis of the central flexible portion of the respective flexible hose when the central flexible portion is in the straight condition.

7. The gas turbine engine system of claim 1 , wherein the fuel delivery circuit connector portion comprises another pivotal assembly with an adjustable end that is pivotal relative to the central longitudinal axis.

8. The gas turbine engine system of claim 1 , further comprising a compressor and a turbine section.

9. A gas turbine engine system comprising:
a fuel delivery circuit configured to convey fuel;
a combustion chamber configured to combust the fuel; and
a flexible hose that fluidly connects the fuel delivery circuit to the combustion chamber, the flexible hose defining a central longitudinal axis when the flexible hose is in a straight condition, the flexible hose comprising:
a bendable portion made of a flexible material that allows the bendable portion to bend; and
a pivotal portion disposed at a first end of the bendable portion, the pivotal portion including a ball and socket connection that allows the first end of the flexible hose to pivot relative to the central longitudinal axis;

wherein the ball and socket connection is configured to be held together by a securing ring on an exterior of the ball and socket connection; and
wherein the securing ring is configured to allow the first end of the bendable portion to be pivotal relative to the central longitudinal axis while the ball and socket connection is secured together by the securing ring.

10. The gas turbine engine system of claim 9 , wherein an adjustable member with a rounded end defines a ball of the ball and socket connection, and a fixed member having a receiving portion that receives the rounded end of the adjustable member defines a socket of the ball and socket connection.

11. The gas turbine engine system of claim 10 , wherein the adjustable member and the fixed member are mechanically locked to each other.

12. The gas turbine engine system of claim 10 , wherein the fixed member is rigidly attached to the bendable portion.

13. The gas turbine engine system of claim 9 , wherein the first end of the flexible hose has a greater range of movement relative to the central longitudinal axis of the flexible hose than the bendable portion.

14. The gas turbine engine system of claim 9 , further comprising a second ball and socket connection being located on a second end of the bendable portion.

15. The gas turbine engine system of claim 9 , further comprising a compressor and a turbine section.

16. A gas turbine engine system comprising:
a fuel delivery circuit configured to convey fuel;
a combustion chamber configured to combust the fuel; and
a flexible hose that fluidly connects the fuel delivery circuit to the combustion chamber, the flexible hose comprising a) a central bendable region with a first minimum bending radius and b) a second bendable region with a second minimum bending radius,
wherein the first minimum bending radius is greater than the second minimum bending radius.

17. The gas turbine engine system of claim 16 , wherein the central bendable region is made of a flexible material that allows the central bendable region to bend.

18. The gas turbine engine system of claim 17 , wherein the second bendable region comprises a ball and socket connection that allows the second bendable region to bend.

19. The gas turbine engine system of claim 16 , wherein the second bendable region comprises an adjustable member mechanically lockable to a fixed member in a pivotal relationship; and wherein the adjustable member defines a first lumen, and the fixed member defines a second lumen, such that the first lumen and the second lumen collectively define a continuous flow path for the fuel when the adjustable member is mechanically locked to the fixed member.

20. The gas turbine engine system of claim 16 , further comprising a compressor and a turbine section.

21. The gas turbine engine of claim 1 , wherein the securing ring is configured to come into engagement with the fixed portion by sliding along an exterior of the adjustable portion.

22. The gas turbine engine of claim 21 , wherein the securing ri

Assignees

• Gen Electric

Inventors

• Soto Jesus Wilfrido
• Garza Luis
• Patino Juan

Classifications

• F16L27/06

  with special sealing means between the engaging surfaces · CPC title

• F02C7/222 Primary

  Fuel flow conduits, e.g. manifolds · CPC title

• F16L37/52

  Universal joints, i.e. with a mechanical connection allowing angular movement or adjustment of the axes of the parts in any direction · CPC title

• F02C7/22 Primary

  Fuel supply systems · CPC title