Split line flow path seals

Patent metadata

Field	Value
Publication number	US-9759079-B2
Application number	US-201514723909-A
Country	US
Kind code	B2
Filing date	May 28, 2015
Priority date	May 28, 2015
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.

First claim

What is claimed is:

1. A gas turbine engine assembly, the assembly comprising
a first component comprising ceramic matrix materials, the first component including a panel arranged to separate a high pressure zone from a low pressure zone and formed to include a first chamfer surface that extends from a high pressure surface of the first component facing the high pressure zone to a first side surface of the first component,
a second component comprising ceramic matrix materials, the second component including a panel arranged to separate the high pressure zone from the low pressure zone and formed to include a second chamfer surface that extends from a high pressure surface of the second component facing the high pressure zone to a second side surface of the first component,
a seal assembly arranged in a channel formed by the first chamfer and the second chamfer when the first side surface of the first component is arranged in confronting relation to the second side surface of the second component, the seal assembly including a rod configured to block gasses from passing through the interface of the first side surface included in the first component with the second side surface included in the second component and a rod locator configured to engage the rod to hold the rod in place relative to the first component and the second component,
wherein the seal assembly includes a bias member configured to push the rod into contact with the first chamfered surface of the first component and the second chamfered surface of the second component, and
wherein the rod locator and the bias member are included in a singular component.

2. The assembly of claim 1 , wherein the rod of the seal assembly is formed to include a notch into which the rod locator extends.

3. The assembly of claim 2 , wherein the notch extends only partway around the rod included in the seal assembly.

4. The assembly of claim 2 , wherein the notch extends all the way around the rod included in the seal assembly.

5. The assembly of claim 4 , wherein the rod locator is formed to include a cutout that receives a necked-down portion of the rod included in the seal assembly at the notch so that the rod is able to rotate relative to the first component and the second component when used in a gas turbine engine.

6. The assembly of claim 1 , wherein the first chamfered surface has a curved shape as it extends from the high pressure surface of the first component to the first side surface of the first component and the second chamfered surface has a curved shape as it extends from the high pressure surface of the second component to the second side surface of the second component.

7. The assembly of claim 1 , wherein the rod has a generally cylindrical shape.

8. The assembly of claim 1 , wherein the singular component comprises a sheet of metallic material having a substantially constant thickness.

9. The assembly of claim 1 , wherein the rod locator is a singular component that comprises a sheet of material having a substantially constant thickness.

10. The assembly of claim 9 , wherein the first component is formed to include a locator slot that receives a portion of the rod locator and the second component is formed to include a locator slot that receives a portion of the rod locator.

11. A gas turbine engine assembly, the assembly comprising
a first component including a panel arranged to separate a high pressure zone from a low pressure zone when used in a gas turbine engine,
a second component including a panel arranged to separate the high pressure zone from the low pressure zone when used in a gas turbine engine,
a rod arranged in a channel formed between the first component and the second component that opens toward the high pressure zone when used in a gas turbine engine,
further comprising a bias member that engages the rod, and
further comprising a rod locator that engages the rod to hold the rod in place relative to the first component and the second component, and the rod locator and the bias member are included in a singular component.

12. The assembly of claim 11 , further comprising a rod locator that engages the rod to hold the rod in place relative to the first component and the second component, and the rod is formed to include a notch into which the rod locator extends.

13. The assembly of claim 12 , wherein the rod locator is formed to include a cutout that receives a necked-down portion of the rod included in the seal assembly at the notch.

14. The assembly of claim 11 , wherein the singular component comprises a sheet of metallic material having a substantially constant thickness.

15. The assembly of claim 11 , further comprising a rod locator that engages the rod to hold the rod in place relative to the first component and the second component, and the first component is formed to include a locator slot that receives a portion of the rod locator and the second component is formed to include a locator slot that receives a portion of the rod locator.

16. The assembly of claim 11 , wherein the first component comprises ceramic matrix composite materials and the second component comprises ceramic matrix composite materials.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc
• Rolls-Royce High Temperature Composites Inc
• Rolls Royce Plc
• Rolls Royce Nam Tech Inc
• Rolls-Royce High Temperature Composites Inc

Inventors

• Sippel Aaron D
• Freeman Ted J
• Thomas David J
• Lamusga Joseph P
• Shoemaker Brian J
• Hillier Steven

Classifications

• F01D25/265

  Vertically split casings; Clamping arrangements therefor · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title

• F01D5/225

  by shrouding · CPC title

• F01D11/008

  by spacer elements between the blades, e.g. independent interblade platforms · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title