Granted Patent B2

US 10,815,807 · App. 15/995,082 · Granted Oct 27, 2020

Inventors: Brad Wilson VanTassel (Easley, SC); Steven Paul Byam (Fountain Inn, SC); Joseph Anthony Weber (Simpsonville, SC); Evan Andrew Sewall (Greer, SC); Travis J Packer (Simpsonville, SC)

Assignee: General Electric Company

F01D9/065F01D9/041F01D11/08F01D25/14F05D2240/11F05D2260/20

Abstract

Claims (95)

1. A turbine of a gas turbine engine, the turbine comprising a stationary shroud ring that includes inner shroud segments circumferentially stacked about a hot gas path, wherein the inner shroud segments includes a first inner shroud segment that comprises:

a cooling configuration that includes cooling channels configured to receive and direct a coolant through an interior of the first inner shroud segment, each of the cooling channels extending lengthwise between a first end and a second end, wherein the second end comprises an outlet formed through an exterior surface of the first inner shroud segment;

a circumferential edge;

a slot formed in the circumferential edge; and

a sealing member positioned within the slot, wherein the slot includes an outboard ceiling positioned radially outward from the sealing member;

wherein the outlet of at least one of the cooling channels is positioned within the outboard ceiling of the slot.

2. The turbine according to claim 1 , wherein a cooling channel group comprises a plurality of the cooling channels;

wherein the outlets of each the cooling channels within the cooling channel group are positioned within the slot;

wherein the first inner shroud segment comprises:

opposed first and second circumferential edges, the circumferential edge comprising one of the first and second circumferential edges;

opposed leading and trailing edges extending between the first and second circumferential edges; and

opposed inner and outboard faces extending between the leading and trailing edges and the first and second circumferential edges, the inner face being directed in an inboard direction toward the hot gas path and an outboard face being directed in an outboard direction.

3. The turbine according to claim 2 , wherein the turbine comprises a center axis relative to which an axial direction, radial direction, and circumferential direction are defined; and

wherein the first inner shroud segment is oriented such that:

the leading and trailing edges are offset in the axial direction, with the offset therebetween defining a width of the first inner shroud segment;

the first and second circumferential edges are offset in the circumferential direction, with the offset therebetween defining a length of the first inner shroud segment; and

the inner and outboard faces are offset in the radial direction, with the offset therebetween defining a height of the first inner shroud segment.

4. The turbine according to claim 3 , wherein the slot on the circumferential edge extends lengthwise between the leading and trailing edges of the first inner shroud segment;

wherein the sealing member extends lengthwise within the slot from a first position at the leading edge to a second position at the trailing edge of the first inner shroud segment;

wherein each of the cooling channels within the cooling channel group extends across at least 75% of the length of the first inner shroud segment; and

wherein the first end of each of the cooling channels within the cooling channel group comprises an inlet formed through the outboard face of the first inner shroud segment.

5. The turbine according to claim 3 , wherein the slot on the circumferential edge extends lengthwise between the leading and trailing edges of the first inner shroud segment;

wherein the sealing member extends lengthwise within the slot from a first position at the leading edge to a second position at the trailing edge of the first inner shroud segment;

wherein each of the cooling channels within the cooling channel group extends across at least 50% of the length of the first inner shroud segment;

wherein the slot is defined between the outboard ceiling, which defines a boundary in the outboard direction, and a floor, which defines a boundary in the inboard direction; and

wherein the outlets of each the cooling channels within the cooling channel group are formed through the outboard ceiling of the slot.

6. The turbine according to claim 5 , wherein the outboard ceiling the slot comprises a beveled portion adjacent to the circumferential edge; and

wherein the outlets of each the cooling channels within the cooling channel group are formed through the beveled portion of the outboard ceiling of the slot.

7. The turbine according to claim 5 , wherein the cooling channel group comprises at least six of the cooling channels;

wherein the outlets of each of the cooling channels within the cooling channel group are aimed so that an initial trajectory of coolant being released therefrom comprises a directional component in the inboard direction; and

wherein the outlets of the cooling channels within the cooling channel group are spaced between the leading and trailing edges of the inner shroud segment.

8. The turbine according to claim 5 , wherein the outlets of each of the cooling channels within the cooling channel group are aimed at the sealing member positioned within the slot; and

wherein the outlets of each of the cooling channels within the cooling channel group comprise a radial position that is outboard relative to the sealing member.

9. The turbine according to claim 8 , wherein the sealing member comprises opposed inner and outboard faces, the outboard face being directed in the outboard direction;

wherein the outlets of each of the cooling channels within the cooling channel group are aimed at the outboard face of the sealing member;

wherein each of the outlets of the cooling channels within the cooling channel group comprises an impingement outlet configuration;

wherein, defined relative to a reference cooling channel having a reference outlet, the impingement outlet configuration comprises a configuration in which the reference outlet has a cross-sectional flow area that is less than 60% of a cross-sectional flow area of the reference cooling channel.

10. An inner shroud segment for use in a stationary shroud ring encircling a hot gas path of a gas turbine engine, the inner shroud segment comprising:

a cooling configuration that includes cooling channels configured to receive and direct a coolant through an interior of the inner shroud segment, each of the cooling channels extending lengthwise between a first end and a second end that comprises an outlet formed through an exterior surface of the inner shroud segment;

opposed first and second circumferential edges; and

first and second slots formed in the first and second circumferential edges, respectively, for receiving a sealing member, the first slot and the second slot each comprising an outboard ceiling;

wherein:

the outlet of at least one of the cooling channels is positioned within the outboard ceiling of the first slot; and

the outlet of at least one of the cooling channels is positioned within the second the outboard ceiling of the slot.

11. The inner shroud segment according to claim 10 , wherein a first cooling channel group comprises a plurality of the cooling channels, and a second cooling channel group comprises a plurality of the cooling channels;

wherein:

the outlets of each of the cooling channels within the first cooling channel group comprise a position within the first slot; and

the outlets of each of the cooling channels within the second cooling channel group comprise a position within the second slot.

12. The inner shroud segment according to claim 11 , wherein the inner shroud segment comprises:

opposed leading and trailing edges extending between the first and second circumferential edges; and

opposed inner and outboard faces extending between the leading and trailing edges and the first and second circumferential edges;

wherein:

an offset between the first and second circumferential edges defines a length of the inner shroud segment;

an offset between the leading and trailing edges defines a width of the inner shroud segment; and

an offset between the inner and outboard faces defines a height of the inner shroud segment;

wherein each of the cooling channels of the first and second cooling channel groups extends across at least 50% of the length of the inner shroud segment.

13. The inner shroud segment according to claim 12 , wherein the first slot on the first circumferential edge extends lengthwise between the leading and trailing edges of the inner shroud segment;

wherein the second slot on the second circumferential edge extends lengthwise between the leading and trailing edges of the inner shroud segment; and

wherein:

the outlets within the first slot are spaced between the leading and trailing edges of the inner shroud segment; and

the outlets within the second slot are spaced between the leading and trailing edges of the inner shroud segment.

14. The inner shroud segment according to claim 13 , wherein each of the first and second slots is defined between the outboard ceiling and, opposed to the outboard ceiling, a floor, wherein the ceiling and floor are approximately parallel to the outboard and inner faces, respectively;

wherein:

the outlets of the cooling channels within the first cooling channel group are each formed through the outboard ceiling of the first slot; and

the outlets of the cooling channels within the second cooling channel group are each formed through the ceiling of the second slot.

15. The inner shroud segment according to claim 14 , wherein each of the outlets of the cooling channels within the first and second cooling channel groups comprises an impingement outlet configuration;

wherein the cooling channels of the first and second cooling channel groups are:

approximately parallel to each other; and

arranged according to an alternating counterflow arrangement in which adjacent ones of the cooling channels have oppositely oriented flow directions.

16. A turbine of a gas turbine engine, the turbine comprising a seal formed at an interface defined between adjacent first and second inner shroud segments that, together, form a portion of a stationary shroud ring encircling a hot gas path, wherein the interface is formed between abutting first and second circumferential edges of the first and second inner shroud segments, respectively, the seal comprising:

first and second slots disposed on the first and second circumferential edges, respectively, the first and second slots cooperatively forming a seal chamber spanning across the interface, wherein the first slot and the second slot each comprise an outboard ceiling;

a sealing member positioned within the seal chamber, the sealing member correspondingly shaped with the seal chamber such that operable engagement therewithin maintains the sealing member positioned across the interface; and

cooling channels formed within each of the first and second inner shroud units, each of the cooling channels extending lengthwise between a first end and second end that comprises an outlet;

wherein:

a first cooling channel group comprises a plurality of the cooling channels formed within the first inner shroud segment; and

a second cooling channel group comprises a plurality of the cooling channels formed within the second inner shroud segment;

wherein:

the outlets of the cooling channels within the first cooling channel group each comprises a position within the outboard ceiling of the first slot; and

the outlets of the cooling channels within the second cooling channel group each comprises a position within the outboard ceiling of the second slot.

17. The turbine according to claim 16 , wherein the first and second inner shroud segment each comprises:

opposed leading and trailing edges extending between the first and second circumferential edges; and

opposed inboard and outboard faces extending between the leading and trailing edges and the first and second circumferential edges;

wherein the turbine comprises a shaft through which a center axis is defined, where an axial direction, radial direction, and circumferential direction are defined relative to the center axis; and

wherein each of the first and second inner shroud segment are oriented such that:

the leading and trailing edges are offset in the axial direction, with the offset therebetween defining a width;

the first and second circumferential edges are offset in the circumferential direction, with the offset therebetween defining a length; and

the inboard and outboard faces are offset in the radial direction, with the offset therebetween defining a height;

wherein the inboard face faces in an inboard direction toward the hot gas path and the outboard face faces in an outboard direction; and

wherein each of the cooling channels of the first and second cooling channel groups extends across at least 50% of the length of the respective one of the first and second inner shroud segments.

18. The turbine according to claim 17 , wherein each of the first and second slots is defined between a respective outboard ceiling, which defines a boundary in the outboard direction, and a respective floor, which defines a boundary in the inboard direction; and

wherein the outlets of each the cooling channels within the first and second cooling channel groups are formed through the respective outboard ceiling of the respective one of the first and second slots.

19. The turbine according to claim 18 , wherein the outlets of each of the cooling channels within the first and second cooling channel groups are aimed so that an initial trajectory of coolant released therefrom comprises a directional component in the inboard direction.

20. The turbine according to claim 18 , wherein the sealing member comprises opposed inner and outboard faces, where the outboard face faces the outboard direction;

wherein the outlets of each of the cooling channels within the first and second cooling channel groups are aimed at the outboard face of the sealing member; and

wherein each of the outlets of the cooling channels within the first and second cooling channel groups comprises an impingement outlet configuration.

Assignments (2)

Continuity (1)

Cited By (16)

US 12,188,365 US 12,215,593 US 12,228,044 US 12,241,376 US 12,258,880 US 12,286,885 US 12,286,906 US 12,305,525 US 12,352,176 US 12,410,725 US 12,416,241 US 12,421,862 US 12,421,870 US 12,503,962 US 12,577,881 US 12,709,992