Unitary body turbine shrouds including internal cooling passages

Patent metadata

Field	Value
Publication number	US-10822986-B2
Application number	US-201916263548-A
Country	US
Kind code	B2
Filing date	Jan 31, 2019
Priority date	Jan 31, 2019
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

Turbine shrouds including internal cooling passages are disclosed. The shrouds may include a unitary body including a support portion, an intermediate portion formed integral with and extending from the support portion, and a seal portion formed integral with the intermediate portion, opposite the support portion. The unitary body may also include two opposing slash faces extending between the support portion and the seal portion, a HGP seal slot formed on each of the two opposing slash faces, and at least one plenum and cooling passage extending through the support portion, intermediate portion, and/or the seal portion. The unitary body may also include an exhaust channel and slash face exhaust holes formed in each of the two opposing slash faces. The exhaust channel may be in fluid communication with the cooling passage(s), and the slash face exhaust holes may be in fluid communication with the exhaust channel.

First claim

What is claimed is:

1. A turbine shroud for a turbine system, the turbine shroud comprising:
a unitary body including:
a support portion coupled directly to a turbine casing of the turbine system;
an intermediate portion integral with and extending away from the support portion;
a seal portion integral with the intermediate portion, opposite the support portion, the seal portion including a forward end, an aft end positioned opposite the forward end, and a hot gas path (HGP) surface extending between the forward end and aft end;
two opposing slash faces extending adjacent to and between the support portion and the HGP surface of the seal portion, the two opposing slash faces positioned opposite one another;
a hot gas path (HGP) seal slot formed on each of the two opposing slash faces;
at least one inlet opening formed in the support portion;
at least one plenum in fluid communication with the at least one inlet opening, the at least one plenum extending through the support portion and the intermediate portion;
a first cooling passage extending through the seal portion, between the forward end and the aft end of the seal portion, the first cooling passage positioned between the at least one plenum and the HGP surface of the seal portion, and the first cooling passage in fluid communication with the at least one plenum;
an exhaust channel formed in each of the two opposing slash faces, between the support portion and the HGP seal slot, the exhaust channel in fluid communication with the first cooling passage; and
a plurality of slash face exhaust holes formed in each of the two opposing slash faces, between the HGP surface of the seal portion and the HGP seal slot, the plurality of slash face exhaust holes in fluid communication with the exhaust channel.

2. The turbine shroud of claim 1 , wherein the unitary body further includes:
a plurality of connection conduits formed in the seal portion, adjacent each of the two opposing slash faces, each of the plurality of connection conduits extending between and fluidly coupling the exhaust channel and the plurality of slash face exhaust holes formed in each of the two opposing slash faces.

3. The turbine shroud of claim 1 , wherein the first cooling passage of the unitary body further includes:
a forward part positioned adjacent the forward end of the seal portion,
an aft part positioned adjacent the aft end of the seal portion, and
a central part positioned between the forward part and the aft part.

4. The turbine shroud of claim 3 , wherein the unitary body further includes:
a first conduit extending between and fluidly coupling the forward part of the cooling passage and the exhaust channel formed in one of the two opposing slash faces; and
a second conduit extending between and fluidly coupling the forward part of the cooling passage and the exhaust channel formed in the other of the two opposing slash faces, opposite the first conduit.

5. The turbine shroud of claim 3 , wherein the unitary body further includes at least one of:
a second cooling passage extending within the unitary body adjacent the forward end of the seal portion, the second cooling passage in direct fluid communication with the forward part of the first cooling passage, or
a third cooling passage extending within the unitary body adjacent the aft end of the seal portion, the third cooling passage in direct fluid communication with the aft part of the first cooling passage.

6. The turbine shroud of claim 5 , wherein the unitary body further includes:
a first conduit extending between and fluidly coupling the second cooling passage and the exhaust channel formed in one of the two opposing slash faces; and
a second conduit extending between and fluidly coupling the second cooling passage and the exhaust channel formed in the other of the two opposing slash faces, opposite the first conduit.

7. The turbine shroud of claim 5 , wherein the unitary body further includes:
a first rib formed in the seal portion, the first rib positioned between and separating the at least one plenum and the first cooling passage; and
at least one of:
a second rib formed adjacent the forward end of the seal portion, the second rib positioned between and separating the forward part of the first cooling passage and the second cooling passage, or
a third rib formed adjacent the aft end of the seal portion, the third rib positioned between and separating the aft part of the first cooling passage and the third cooling passage.

8. The turbine shroud of claim 7 , wherein the unitary body further includes:
a first plurality of impingement openings formed through the first rib to fluidly couple the first cooling passage to the at least one plenum; and
at least one of:
a second plurality of impingement openings formed through the second rib, the second plurality of impingement openings fluidly coupling the forward part of the first cooling passage and the second cooling passage, or
a third plurality of impingement openings formed through the third rib, the third plurality of impingement openings fluidly coupling the aft part of the first cooling passage and the third cooling passage.

9. The turbine shroud of claim 5 , wherein the unitary body further includes:
a plurality of forward exhaust holes formed through the forward end of the seal portion, each of the plurality of forward exhaust holes in fluid communication with the second cooling passage.

10. The turbine shroud of claim 5 , wherein the unitary body further includes:
a plurality of aft exhaust holes formed through the aft end of the seal portion, each of the plurality of aft exhaust holes in fluid communication with the third cooling passage.

11. The turbine shroud of claim 1 , wherein the at least one plenum further extends through at least a portion of the seal portion.

12. A turbine system comprising:
a turbine casing;
a rotor extending axially through the turbine casing;
a plurality of turbine blades positioned circumferentially about and extending radially from the rotor; and
a plurality of turbine shrouds directly coupled to the turbine casing and positioned radially between the turbine casing and the plurality of turbine blades, each of the plurality of turbine shrouds including:
a unitary body including:
a support portion coupled directly to the turbine casing;
an intermediate portion integral with and extending radially from the support portion;
a seal portion integral with the intermediate portion, radially opposite the support portion, the seal portion including a forward end, an aft end positioned opposite the forward end, and a hot gas path (HGP) surface extending between the forward end and aft end;
two opposing slash faces extending adjacent to and radially between the support portion and the HGP surface of the seal portion, the two opposing slash faces positioned opposite one another;
a hot gas path (HGP) seal slot formed on each of the two opposing slash faces;
at least one inlet opening formed in the support portion;
at least one plenum in fluid communication with the at least one inlet opening, the at least one plenum extending radially through the support portion and the intermediate portion;
a first cooling passage extending through the seal portion, between the forward end and the aft end of the seal portion, the first cooling passage positioned radially between the at least one plenum and the HGP surface of the seal portion, and the first cooling passage in fluid communication with the at least one plenum;
an exhaust channel formed in each of the two opposing slash faces, radially between the support portion and the HGP seal slot, the exhaust channel i

Assignees

• Gen Electric

Inventors

• Snider Zachary John
• Weber David Wayne

Classifications

• F01D25/12

  Cooling · CPC title

• F01D11/08 Primary

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

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title