Orientation feature for swirler tube

Patent metadata

Field	Value
Publication number	US-10871108-B2
Application number	US-201816011737-A
Country	US
Kind code	B2
Filing date	Jun 19, 2018
Priority date	Feb 9, 2015
Publication date	Dec 22, 2020
Grant date	Dec 22, 2020

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

The invention claimed is:

1. A method of installing a cooling structure in a gas turbine engine comprising:
providing a mid-turbine frame that defines a cooling cavity and has an opening to define a portion of a cooling flowpath, and providing a cooling component that is configured to direct cooling flow into the cooling cavity, and wherein the mid-turbine frame has a plate portion with a forward face and an aft face;
providing a bracket that supports the cooling component and has an attachment interface to fix the bracket to the mid-turbine frame, wherein the bracket comprises a forward bracket and an aft bracket, the forward bracket positioned on one side of the mid-turbine frame and having a first mounting flange portion with a center boss portion extending outwardly from the mounting flange portion, and the aft bracket positioned on an opposite side of the mid-turbine frame and having a second mounting flange portion;
associating the cooling component with the aft bracket;
associating an inlet tube with the center boss portion of the forward bracket to direct cooling flow through the opening and into the cooling component;
forming a first orientation feature on the bracket;
forming a second orientation feature on the mid-turbine frame; and
associating the first and second orientation features with each other to ensure that the cooling component is only installed in one orientation relative to the mid-turbine frame by
attaching the first mounting flange portion to the forward face, and
attaching the second mounting flange portion to the aft face;
to provide a properly installed cooling component when the first and second mounting flange portions are flush with the respective forward and aft faces.

2. The method 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, and
wherein associating the first and second orientation features with each other comprises inserting the male feature into the female feature to achieve the one orientation.

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

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

5. The method of claim 1 , wherein the first orientation feature comprises at least one tab and the second orientation feature comprises a rib.

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

7. The method of claim 1 , wherein the forward and aft brackets each include the first orientation feature.

8. The method 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.

9. The method of claim 1 , wherein the attachment interface includes at least one fastener that secures both the forward and aft brackets to the mid-turbine frame.

10. The method of claim 9 , wherein the opening in the mid-turbine frame comprises a flow opening in the plate portion of the mid-turbine frame, and wherein the at least one fastener comprises at least a first fastener and a second fastener, and including aligning a center opening of the forward bracket with the flow opening in the plate portion of the mid-turbine frame, aligning a center opening of the aft bracket with the flow opening, and securing the forward and aft brackets to the mid-turbine frame by inserting the first fastener through aligned fastener openings in the forward bracket, aft bracket, and mid-turbine frame on one side of the flow opening, and inserting the second fastener through aligned fastening openings in the forward bracket, aft bracket, and mid-turbine frame on an opposite side of the flow opening.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

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

Classifications

• 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

• F05D2260/36

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

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · 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

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title