Orientation feature for swirler tube

Patent metadata

Field	Value
Publication number	US-10030582-B2
Application number	US-201514617109-A
Country	US
Kind code	B2
Filing date	Feb 9, 2015
Priority date	Feb 9, 2015
Publication date	Jul 24, 2018
Grant date	Jul 24, 2018

Abstract

A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

First claim

What is claimed is:

1. A cooling structure for a gas turbine engine comprising:
a gas turbine engine structure defining a cooling cavity, wherein the gas turbine engine structure includes an opening to define a portion of a cooling flow path;
a cooling component configured to direct cooling flow into the cooling cavity;
a bracket supporting the cooling component and having an attachment interface to fix the bracket to the gas turbine engine structure, and wherein the bracket comprises a forward bracket positioned on one side of the gas turbine engine structure and an aft bracket positioned on an opposite side of the gas turbine engine structure, and wherein the cooling component is associated with the aft bracket, and wherein the forward bracket includes a mounting flange portion with a center boss portion extending outwardly from the mounting flange portion;
an inlet tube associated with the center boss portion of the forward bracket to direct cooling flow through the opening and into the cooling component;
the forward and aft brackets each including a first orientation feature; and
a second orientation feature associated with the gas turbine engine structure, the first and second orientation features cooperating with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure.

2. The structure of claim 1 , wherein one of the first and second orientation features comprises a male feature and the other of the first and second orientation features comprises a female feature that receives the male feature.

3. The structure of claim 2 , wherein the male feature comprises a tab and the female feature comprises a slot.

4. The structure of claim 2 , wherein the male feature comprises a pin and the female feature comprises an opening.

5. The structure of claim 1 , wherein the first orientation feature comprises at least one tab and the second orientation feature comprises a rib, and wherein the rib interferes with the tab to prevent mounting the bracket in an incorrect orientation relative to the gas turbine engine structure.

6. The structure of claim 1 , wherein the cooling component comprises a swirler tube that redirects cooling flow from a first direction defined by the inlet tube to a second direction that is transverse to the first direction.

7. The structure of claim 6 , including at least first and second fasteners positioned on opposite sides of the swirler tube to secure the gas turbine engine structure, forward bracket and aft bracket together.

8. The structure of claim 1 , wherein the attachment interface includes at least one fastener that secures both the forward and aft brackets to the gas turbine engine structure.

9. The structure of claim 1 , wherein the gas turbine engine structure comprises a mid-turbine frame structure having a plate portion with a forward face and an aft face, and wherein the mounting flange portion of the forward bracket comprises a first mounting flange portion attached to the forward face and wherein the aft bracket has a second mounting flange portion attached to the aft face, and wherein when the cooling component is properly installed the first and second mounting flange portions are flush with the respective forward and aft faces, and when the cooling component is not properly installed the first and second orientation features interfere with each other such that the first and second mounting flange portions are prevented from sitting flush with the respective forward and aft faces.

10. The structure of claim 1 , wherein the cooling component comprises a swirler tube that initiates a swirling flow pattern about a central axis of the engine.

11. A gas turbine engine comprising:
a mid-turbine frame located axially between a first turbine and a second turbine, the mid-turbine frame including an opening to define a portion of a cooling flow path into a rotor cavity;
a cooling component comprising a cooling tube configured to direct cooling flow into the rotor cavity;
a bracket assembly supporting the cooling component and having an attachment interface to fix the bracket assembly to the mid-turbine frame, wherein the bracket comprises a forward bracket positioned on one side of the mid-turbine frame and an aft bracket positioned on an opposite side of the mid-turbine frame, and wherein the cooling tube is associated with the aft bracket, and wherein the forward bracket includes a mounting flange portion with a center boss portion extending outwardly from the mounting flange portion;
an inlet tube associated with the center boss portion of the forward bracket to direct cooling flow through the opening and into the cooling tube;
a first orientation feature associated with the bracket assembly; and
a second orientation feature associated with the mid-turbine frame, the first and second orientation features cooperating with each other to ensure that the cooling component is only installed in one orientation relative to the mid-turbine frame.

12. The gas turbine engine of claim 11 , wherein the opening in the mid-turbine frame defines a center axis, and wherein the cooling tube comprises a swirler tube that initiates a swirling flow pattern about an engine center axis.

13. The gas turbine engine of claim 12 , wherein the forward bracket is positioned at the opening on one side of the mid-turbine frame and the aft bracket is positioned at the opening on an opposite side of the mid-turbine frame, and wherein the swirler tube is associated with the aft bracket.

14. The gas turbine engine of claim 13 , wherein the first orientation feature is formed on both the forward and aft brackets, and wherein the second orientation feature is formed on each side of the mid-turbine frame such that each of the forward and aft brackets can only be mounted on the mid-turbine frame in one mounting orientation.

15. The gas turbine engine of claim 11 , wherein the mid-turbine frame has a plate portion with a forward face and an aft face, and wherein the mounting flange portion of the forward bracket comprises a first mounting flange portion attached to the forward face and the aft bracket has a second mounting flange portion attached to the aft face, and wherein when the cooling component is properly installed the first and second mounting flange portions are flush with the respective forward and aft faces, and when the cooling component is not properly installed the first and second orientation features interfere with each other such that the first and second mounting flange portions are prevented from sitting flush with the respective forward and aft faces.

16. The gas turbine engine of claim 11 , including at least first and second fasteners positioned on opposite sides of the cooling tube to secure the mid-turbine frame, forward bracket and aft bracket together.

17. A gas turbine engine comprising:
a mid-turbine frame located axially between a first turbine and a second turbine, the mid-turbine frame including an opening to define a portion of a cooling flow path into a rotor cavity;
a cooling component comprising a cooling tube configured to direct cooling flow into the rotor cavity, wherein the opening in the mid-turbine frame defines a center axis, and wherein the cooling tube comprises a swirler tube that initiates a swirling flow pattern about an engine center axis;
a bracket assembly supporting the cooling component and having an attachment interface to fix the bracket assembly to the mid-turbine frame, wherein the bracket assembly comprises a forward bracket positioned at the opening on one

Assignees

• United Technologies Corp

Inventors

• Zacchera Kevin
• Hough Matthew Andrew
• Lemoine Jonathan
• Treat Christopher
• Mateo Alberto A

Classifications

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F05D2260/14

  Preswirling · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F01D5/081 Primary

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F05D2230/64

  using positioning or alignment devices for aligning or centring, e.g. pins · CPC title