Turbine blade track assembly

Patent metadata

Field	Value
Publication number	US-9759082-B2
Application number	US-201314145202-A
Country	US
Kind code	B2
Filing date	Dec 31, 2013
Priority date	Mar 12, 2013
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

A gas turbine engine is disclosed with a turbine section having at least one turbine rotor with a plurality of turbine blades, a plurality of blade tracks positioned circumferentially around the turbine blades, at least one dovetail shaped connecting member extending radially outward from each blade track, and a hanger connected to a structural member of the gas turbine engine and configured to releasably couple with the at least one dovetail shaped connecting member of a corresponding blade track.

First claim

What is claimed is:

1. An apparatus comprising:
a blade track including a segment portion comprising ceramic matrix composite materials and having a first radially-facing surface and a second radially-facing surface opposite the first radially-facing surface, wherein the first radially-facing surface is arcuate;
a first attachment portion comprising ceramic matrix composite materials and extending radially outward from the second surface and circumferentially between a first circumferentially-facing surface and a second circumferentially-facing surface opposite the first circumferentially-facing surface, wherein a coupling region of the first attachment portion has a dovetail shaped cross section, and
a second attachment portion comprising ceramic matrix composite materials and extending radially outward from the second surface and circumferentially between a third circumferentially-facing surface and a fourth circumferentially-facing surface opposite the third circumferentially-facing surface, wherein a coupling region of the second attachment portion has a dovetail shaped cross section,
wherein the second attachment portion is spaced apart axially from the first attachment portion, and
wherein the ceramic matrix composite materials of the second attachment portion include a first reinforcement wrap, a second reinforcement wrap, a third reinforcement wrap, a fourth reinforcement wrap, a first preform insert, and a second preform insert, the first reinforcement wrap and the second reinforcement wrap are positioned adjacent one another, first end portions of the first reinforcement wrap and the second reinforcement wrap are spaced apart from one another, the first preform insert is positioned between the spaced apart first end portions of the first reinforcement wrap and the second reinforcement wrap, the third reinforcement wrap and the fourth reinforcement wrap are positioned adjacent one another, first end portions of the third reinforcement wrap and the fourth reinforcement wrap are spaced apart from one another, and the second preform insert is positioned between the spaced apart first end portions of the third reinforcement wrap and the fourth reinforcement wrap.

2. The apparatus of claim 1 , further comprising:
a pair of spaced apart radially-extending third surfaces extending from the first radially-facing surface to the second radially-facing surface of the segment portion, wherein a distance from one of the radially-extending third surfaces to the first attachment portion along the axial direction is substantially the same as a distance from the other of the radially-extending third surfaces to the first attachment portion along the axial direction.

3. The apparatus of claim 1 , further comprising:
a hanger having a coupling portion structured to receive the coupling region of a corresponding attachment portion of the blade track.

4. The apparatus of claim 3 , wherein the hanger and the blade track have different coefficients of thermal expansion.

5. The apparatus of claim 3 , wherein a plurality of blade track segments are arranged circumferentially about a common axis to define an exhaust gas flow path for a turbine.

6. The gas turbine engine of claim 1 , wherein the first end portion of the second reinforcement wrap is positioned adjacent the first end portion of the fourth reinforcement wrap and the first end portions of the first reinforcement wrap and the third reinforcement wrap diverge away from one another.

7. The gas turbine engine of claim 6 , wherein the ceramic matrix composite materials of the segment portion include a fifth reinforcement wrap and a third preform insert, second ends of the first and second reinforcement wraps extend away from second ends of the third and fourth reinforcement wraps, the third preform insert is positioned between a portion of the second and fourth reinforcement wraps, and the fifth reinforcement wrap is positioned adjacent the second and fourth reinforcement wraps and the third preform insert.

8. A turbine blade track assembly comprising:
a blade track segment portion having a first surface, a second surface opposite the first surface, and a pair of spaced apart third surfaces extending from the first surface to the second surface, wherein the first surface is an arcuate surface adapted to form a portion of an outer wall of an exhaust gas flow path;
a first blade track attachment portion extending radially from the second surface and circumferentially toward the third surfaces and a second blade track attachment portion extending radially from the second surface and circumferentially toward the third surfaces, the first attachment portion being axially spaced apart from the second attachment portion, wherein a coupling region of the first blade track attachment portion has a dovetail shaped cross section and a coupling region of the second blade track attachment portion has an open channel with a substantially C-shaped cross section; and
a blade track hanger configured to connect to a fixed structure positioned in a gas turbine engine, the hanger having a coupling portion structured to receive the dovetail shaped coupling region of the first blade track attachment portion,
wherein the first blade track attachment portion includes ceramic matrix composite materials including a first reinforcement wrap, a second reinforcement wrap, and a first preform insert, the first reinforcement wrap and the second reinforcement wrap are positioned adjacent one another, first end portions of the first reinforcement wrap and the second reinforcement wrap are spaced apart from one another, and the first preform insert is positioned between the spaced apart first end portions of the first reinforcement wrap and the second reinforcement wrap.

9. The turbine blade track assembly of claim 8 , wherein a width of the first blade track attachment portion along the axial direction is greater than half a length of the segment portion from one of the third surfaces to the other of the third surfaces.

10. The turbine blade track assembly of claim 8 , wherein a coefficient of thermal expansion of the blade track is different from a coefficient of thermal expansion of the hanger.

11. The turbine blade track assembly of claim 8 , wherein the hanger is formed of a metallic material.

12. The turbine blade track assembly of claim 8 , wherein the blade track segment and the attachment portions are formed from a ceramic matrix composite material.

13. The gas turbine engine of claim 8 , wherein the ceramic matrix composite materials included in the first blade track attachment portion further include a third reinforcement wrap, a fourth reinforcement wrap, and a second preform insert, the third reinforcement wrap and the fourth reinforcement wrap are positioned adjacent one another, first end portions of the third reinforcement wrap and the fourth reinforcement wrap are spaced apart from one another, and the second preform insert is positioned between the spaced apart first end portions of the third reinforcement wrap and the fourth reinforcement wrap.

14. The gas turbine engine of claim 13 , wherein the first end portion of the second reinforcement wrap is positioned adjacent the first end portion of the fourth reinforcement wrap and the first end portions of the first reinforcement wrap and the third reinforcement wrap diverge away from one another.

15. The gas turbine engine of claim 14 , wherein the blade track segment portion includes ceramic matrix composite materials including a fifth reinforcement wrap and a third preform insert, second ends of the first and second reinforcement wraps extend away

Assignees

• Rolls Royce Corp

Inventors

• Thomas David J
• Uskert Richard C

Classifications

• F01D11/18

  using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion · CPC title

• F01D11/12

  using a rubstrip, e.g. erodible. deformable or resiliently-biased part · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title