Turbine shroud assemblies for gas turbine engines

Patent metadata

Field	Value
Publication number	US-10907487-B2
Application number	US-201816161250-A
Country	US
Kind code	B2
Filing date	Oct 16, 2018
Priority date	Oct 16, 2018
Publication date	Feb 2, 2021
Grant date	Feb 2, 2021

Abstract

A turbine shroud assembly includes a shroud support and a shroud segment. The shroud support structure includes a forward support rail and an aft support rail. The forward support rail includes forward first engagement structures and the aft support rail includes aft first engagement structures. The shroud segment includes a forward segment rail and an aft segment rail. The forward segment rail includes forward second engagement structures positioned on a forward segment rail periphery and the aft segment rail includes second engagement structures positioned on an aft segment rail periphery. The forward first engagement structures radially and circumferentially engage with the forward second engagement structures and the aft first engagement structures radially and circumferentially engage with the aft second engagement structures to radially and circumferentially interlock the shroud segment to the shroud support structure.

First claim

What is claimed is:

1. A turbine shroud assembly, comprising:
a shroud support with a forward support rail and an aft support rail extending radially and about a circumferential orientation, wherein the forward support rail includes a first inner periphery defining a first inner periphery surface that faces radially inward and the aft support rail includes a second inner periphery defining a second inner periphery surface that faces radially inward, wherein the forward support rail includes a forward first dovetail structure formed in the first inner periphery surface, wherein the aft support rail includes an aft first dovetail structure formed in the second inner periphery; and
a shroud segment with a forward segment rail and an aft segment rail extending radially and about the circumferential orientation, wherein the forward segment rail has a first outer periphery defining a forward segment rail periphery surface that faces radially outward, wherein the rear segment rail has a second outer periphery defining an aft segment rail periphery surface that faces radially outward, wherein the forward segment rail includes a forward second dovetail structure formed in the forward segment rail periphery surface and the aft segment rail includes an aft second dovetail structure formed in the aft segment rail periphery surface, and
wherein the forward first dovetail structure is configured to radially and circumferentially engage with the forward second dovetail structure, wherein the forward second dovetail structure extends axially only partially through the forward support rail, and the aft first dovetail structure is configured to radially and circumferentially engage with the aft second dovetail structure, wherein the aft second dovetail structure extends only partially through the aft support rail, to radially and circumferentially interlock the shroud segment to the shroud support.

2. The turbine shroud assembly of claim 1 , wherein the forward support rail includes a radially extending segment, wherein the forward first dovetail structure mates with the forward second dovetail structure and the aft first dovetail structure mates with the aft second dovetail structure such that the radially extending segment of the forward support rail completely overlaps the forward segment rail along the axial orientation.

3. The turbine shroud assembly of claim 1 , wherein one of the forward first dovetail structure or the forward second dovetail structure is a partially enclosed notch that includes a bottom wall disposed away from the respective first inner periphery or first outer perimeter and a mouth at the first inner periphery or at the first outer perimeter respectively, wherein a notch circumferential width of the notch is greater at the bottom wall than at the mouth, and the other of the forward first dovetail structure or the forward second dovetail structure is a projection with a root, wherein the projection diverges from the root such that a projection circumferential width of the projection increases along a radial height of the projection to the first inner periphery or to the second inner periphery respectively.

4. The turbine shroud assembly of claim 3 , wherein both the aft first dovetail structure and the aft second dovetail structure includes a partially enclosed notch with a mouth opening through the first inner periphery and at the second inner periphery, respectively and includes a projection interlocking with the partially enclosed notch and extending through the first inner periphery and at the second inner periphery, respectively.

5. The turbine shroud assembly of claim 1 , wherein the forward first dovetail structure and the aft first dovetail structure are each formed by an array of projections, and wherein the forward second dovetail structure and the second dovetail structure are each formed by an array of partially enclosed notches opening through the first outer periphery and the second outer periphery, respectively.

6. The turbine shroud assembly of claim 5 , wherein the array of projections is an array of dovetail projections each with a root, wherein the projections diverge from the root such that a projection circumferential width of the projections increases along a radial height of the projections to the first inner periphery or to the second inner periphery respectively and the array of partially enclosed notches are dovetail notches configured to receive the array of dovetail projections.

7. The turbine shroud assembly of claim 1 , wherein the shroud segment includes a base from which the forward segment rail and the aft segment rail radially extend and the shroud support includes a body from which the forward support rail and the aft support rail radially extend, and wherein the turbine shroud assembly further comprises a cavity at least partially formed by the body of the shroud support, the forward support rail, the aft support rail, the forward segment rail, the aft segment rail, and the base of the shroud segment, and comprising a baffle disposed in the cavity and defining an upstream plenum and a downstream plenum, the baffle coupled to the aft support rail and to the body, the baffle including a plurality of orifices that fluidly couple the upstream plenum with downstream plenum.

8. The turbine shroud assembly of claim 1 , wherein the forward support rail includes a stop flange extending radially inward further than the second inner periphery of the aft support rail, the stop flange extending axially to axially position the shroud segment relative to the shroud support.

9. The turbine shroud assembly of claim 1 , comprising a baffle extending between the forward segment rail and the aft segment rail, and a seal engaging the baffle and the shroud support.

10. The turbine shroud assembly of claim 1 , wherein the shroud support includes a base from which the forward and aft support rails extend, and comprising a baffle extending between and engaging the aft segment rail and the base.

11. A shroud segment for a turbine shroud assembly of a gas turbine engine having a shroud support with a forward support rail including a forward engagement projection that extends radially inward and an aft support rail including an aft engagement projection, the shroud segment comprising:
a base;
a forward segment rail extending radially from the base and along a circumferential orientation parallel to the forward support rail, wherein the forward segment rail extends to a first outermost periphery surface, and includes a forward engagement notch defined through the first outermost periphery surface, the forward engagement notch having a forward mouth that opens through the first outermost periphery surface; and
an aft segment rail extending radially from the base and along the circumferential orientation parallel to the aft support rail, wherein the aft segment rail extends to a second outermost periphery surface, and includes an aft engagement notch defined through the second outermost periphery surface, the aft engagement notch having an aft mouth that opens through the second outermost periphery surface,
wherein the forward engagement notch is configured to radially and circumferentially engage the forward engagement projection, with the forward engagement projection extending into the forward engagement notch and extending through the forward mouth, wherein the forward segment rail, for an axial length of the forward engagement notch, extends axially only partially through the forward support rail, and the aft engagement notch is configured to radially and circumferentially engage the aft engagement projection, with the aft engagement projection extending into the aft notch and extending through the

Assignees

• Honeywell Int Inc

Inventors

• Zurmehly Luke
• Smoke Jason
• Kime Kent L
• Petersen Blake

Classifications

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D25/246 Primary

  Fastening of diaphragms or stator-rings · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D9/04 Primary

  forming ring or sector · CPC title