WO2016118138A1

WO2016118138A1 - Seal system for ring segments radially outward of a turbine assembly within a turbine engine

Info

Publication number: WO2016118138A1
Application number: PCT/US2015/012372
Authority: WO
Inventors: Runzhong CHEN
Original assignee: Siemens Aktiengesellschaft; Siemens Energy, Inc.
Priority date: 2015-01-22
Filing date: 2015-01-22
Publication date: 2016-07-28

Abstract

A gas turbine engine (10) with a seal system (12) for a turbine ring segment assembly is disclosed. The seal system (12) may include a seal plate retention device (16) that retains a seal plate (18) between adjacent ring segments positioned radially outward of a circumferential row (24) of turbine blades (26). The seal plate retention device (16) may retain the seal plate (18) in position without welds. In particular, the seal plate retention device (16) may retain the seal plate (18) at least partially within a first seal plate receiver (28) in a first ring segment (20) and a second seal plate receiver (30) in a second ring segment (22). In at least one embodiment, the seal plate retention device (16) may include one or more arms (32) extending from the seal plate (18) to provide a robust seal with reduced likelihood of becoming dislodged and flowing downstream where the seal plate (18) would likely damage downstream components.

Description

SEAL SYSTEM FOR RING SEGMENTS RADIALLY OUTWARD OF A TURBINE ASSEMBLY WITHIN A TURBINE ENGINE

FIELD OF THE INVENTION

This invention is directed generally to turbine engines, and more particularly to seal systems for turbine ring segment assemblies for turbine engines.

BACKGROUND

A plurality of ring segments are typically assembled to form a ring radially outward of the tips of turbine blade forming a portion of a stage within a turbine assembly in a gas turbine engine. The ring segments are typically sealed together with seals to limit hot gas from escaping the hot gas pathway. The seals have been formed from plates that are welded in place. During use, these plates can work free and become dislocated. The dislocated plates are often swept into the hot gas path and flow downstream causing significant damage to downstream turbine

components. Thus, a need exists for a more robust seal system.

SUMMARY OF THE INVENTION

A gas turbine engine with a seal system for a turbine ring segment assembly is disclosed. The seal system may include a seal plate retention device that retains a seal plate between adjacent ring segments positioned radially outward of a circumferential row of turbine blades. The seal plate retention device may retain the seal plate in position without welds. In particular, the seal plate retention device may retain the seal plate at least partially within a first seal plate receiver in a first ring segment and a second seal plate receiver in a second ring segment. In at least one embodiment, the seal plate retention device may include one or more arms extending from the seal plate to provide a robust seal with reduced likelihood of becoming dislodged and flowing downstream where the seal plate would likely damage downstream components.

In at least one embodiment, the gas turbine engine may include a turbine assembly formed from a rotor assembly having one or more turbine blades formed from a generally elongated airfoil having a leading edge, a trailing edge, a pressure side, a suction side, a tip at a first end and a platform coupled to a second end of the generally elongated airfoil opposite to the first end. First and second ring segments may be positioned radially outward from the tip of the turbine blade. The first and second ring segments may be aligned in a circumferentially extending row and form at least a portion of a ring around a travel path of the turbine blade. The first and second ring segments may each include an inner surface forming a portion of a hot gas path within the turbine assembly. One or more seal plates may have one or more seal plate retention devices. In at least one embodiment, the seal plate may extend from an upstream edge of the first ring segment to a downstream end of the first ring segment. One or more first seal plate receivers may be positioned in a first side surface of the first ring segment. The first seal plate receiver may receive at least a portion of the seal plate. One or more second seal plate receivers may be positioned in a second side surface of the second ring segment. The first side surface of the first ring segment and the second side surface of the second ring segment may face each other. The second seal plate receiver may receive at least a portion of the seal plate. The seal plate retention device may be configured to prevent the seal plate from being released from being partially positioned within the first seal plate receiver and the one second seal plate receiver. The seal plate retention device may enable the seal plate to be retained within the first seal plate receiver and the second seal plate receiver without a weld.

The seal plate retention device may include one or more first arms extending laterally from a first side of the seal plate. The first seal plate receiver may include one or more retention device receivers receiving the first arm. The seal plate retention device may include one or more second arms extending laterally from a second side of the seal plate. The first arm may be positioned at an upstream edge of the seal plate. The retention device receiver in the first seal plate receiver may be positioned at an upstream edge of the first ring segment. The first seal plate receiver may include an opening in the upstream edge of the first ring segment. The retention device receiver in the first seal plate receiver may include an opening in the upstream edge of the first ring segment.

The second seal plate receiver may include one or more retention device receivers receiving the second arm. The second arm may be positioned at an upstream edge of the seal plate. The retention device receiver in the second seal plate receiver may be positioned at an upstream edge of the second ring segment. The second seal plate receiver may include an opening in the upstream edge of the second ring segment. The retention device receiver in the second seal plate receiver may include an opening in the upstream edge of the second ring segment.

The seal system has been described with respect to first and second ring segments. However, the seal system is not limited to only being used between two rings segments; rather, the seal system may be used with a turbine ring segment assembly formed from a plurality of ring segments forming a ring radially outward of the turbine blades. The plurality of ring segments may number more than two ring segments. In at least one embodiment, the first and second ring segments may be a plurality of first and second ring segments forming a ring around a travel path of the turbine blade such that each of the first and second ring segments are joined together via seal plates having at least one seal plate retention device. Each first ring segment may include one or more first seal plate receivers receiving at least a portion of the seal plate, and each second ring segment may include one or more second seal plate receivers receiving at least a portion of the seal plate. This pattern may be repeated as many times as necessary, depending on the number of ring segments, to form a ring.

An advantage of the seal system is that the seal plate retention device reduces the likelihood of damage to downstream turbine components by providing a robust seal with reduced likelihood of becoming.

Another advantage of the seal system is that the seal plate retention device enables the seal plate to be retained within the first seal plate receiver and the second seal plate receiver without a weld. Thus, the seal system is not susceptible to failure due to failure of a weld.

These and other embodiments are described in more detail below.

BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying drawings, which are incorporated in and form a part of the specification, illustrate embodiments of the presently disclosed invention and, together with the description, disclose the principles of the invention. Figure 1 is a cross-sectional, perspective view of a gas turbine engine with the seal system positioned between adjacent ring segments radially outward of turbine blades of the turbine assembly.

Figure 2 is a detail, cross-sectional view of with the seal system positioned between adjacent ring segments radially outward of turbine blades of the turbine assembly taken at detail 2-2 in Figure 1 .

Figure 3 is a perspective view looking radially inward on two adjacent ring segments coupled together with the seal system.

Figure 4 is a seal plate of the seal system.

Figure 5 is a perspective view of the second ring segment.

Figure 6 is a detail view of the retention device receiver positioned within the second seal plate receiver in the second ring segment.

DETAILED DESCRIPTION OF THE INVENTION

As shown in Figures 1-6, a gas turbine engine 10 with a seal system 12 for a turbine ring segment assembly 14 is disclosed. The seal system 12 may include a seal plate retention device 16 that retains a seal plate 18 between adjacent ring segments 20, 22 positioned radially outward of a circumferential row 24 of turbine blades 26. The seal plate retention device 16 may retain the seal plate 18 in position without welds. In particular, the seal plate retention device 16 may retain the seal plate 18 at least partially within a first seal plate receiver 28 in a first ring segment 20 and a second seal plate receiver 30 in a second ring segment 22. In at least one embodiment, the seal plate retention device 16 may include one or more arms 32 extending from the seal plate 18 to provide a robust seal with reduced likelihood of becoming dislodged and flowing downstream where the seal plate 18 would likely damage downstream components.

In at least one embodiment, the gas turbine engine 10 may include a turbine assembly 34 formed from a rotor assembly 36 having one or more turbine blades 26 formed from a generally elongated airfoil 38, as shown in Figure 2, having a leading edge 40, a trailing edge 42, a pressure side 44, a suction side 46, a tip 48 at a first end 49 and a platform 51 coupled to a second end 53 of the generally elongated airfoil 38 opposite to the first end 50. The turbine blades 26 may have any appropriate configuration and is not limited to a particular design already in existence. The turbine ring segment assembly 14, as shown in Figure 1 , may be formed from first and second ring segments 20, 22, as shown in Figure 3, positioned radially outward from the tip 48 of the turbine blade 26. The first and second ring segments 20, 22 may be aligned in a circumferentially extending row 24, as shown in Figure 2, and form at least a portion of a ring around a travel path 50 of the turbine blade 26. The first and second ring segments 20, 22 may each include an inner surface 52 forming a portion of a hot gas path 54 within the turbine assembly 34. The first and second ring segments 20, 22 may have any appropriate configuration and may be coupled to a turbine vane carrier or other support structure in an appropriate manner.

The seal system 12 may include one or more seal plates 18 having one or more seal plate retention devices 16, as shown in Figure 4. The seal plate 18 may be formed from a generally elongated body 56 with a length that is substantially longer than a width of the body 56. In at least one embodiment, the length of the generally elongated body 56 may be greater than a width of the body 56, and the width of the body may be greater than a thickness of the body 56. In at least one embodiment, the seal plate 18 may extend from an upstream edge 74 of the first ring segment 20 to downstream end 94 of the first ring segment 20. The seal plate 18 may also extend from an upstream edge 88 of the second ring segment 22 to a downstream end 94 of the second ring segment 22. In other embodiments, the seal plate 18 may have a shorter length than a distance from the upstream edge 74 of the first ring segment 20 to downstream end 94 of the first ring segment 20 or the upstream edge 72 of the second ring segment 22 to the downstream end 94 of the second ring segment 22.

One or more first seal plate receivers 28 may be positioned in a first side surface 58 of the first ring segment 20, as shown in Figure 3. The first seal plate receiver 28 may be configured to receive at least a portion of the seal plate 18. In at least one embodiment, the first seal plate receiver 28 may include an opening 60 in the first side surface 58 of the first ring segment 20. The opening 60 may be sized to receive the seal plate 18. In at least one embodiment, the opening 60 may be sized in a radially extending direction to be greater than a thickness of the seal plate 18, thereby enabling the seal plate 18 to be received within the opening 60 and the first seal plate receiver 28.

One or more second seal plate receivers 30 may be positioned in a second side surface 62 of the second ring segment 22, as shown in Figures 3, 5 and 6. The first side surface 58 of the first ring segment 20 and the second side surface 62 of the second ring segment 22 may face each other. The first side surface 58 of the first ring segment 20 and the second side surface 62 of the second ring segment 22 may be parallel or may be positioned nonparallel and nonorthogonal to each other. The second seal plate receiver 30 may be configured to receive at least a portion of the seal plate 18. In at least one embodiment, the second seal plate receiver 30 may include an opening 64 in the second side surface 60 of the second ring segment 22. The opening 64 may be sized to receive the seal plate 18. In at least one embodiment, the opening 64 may be sized in a radially extending direction to be greater than a thickness of the seal plate 18, thereby enabling the seal plate 18 to be received within the opening 64 and the first seal plate receiver 28.

The seal plate retention device 16 may be configured to prevent the seal plate 18 from being released from being partially positioned within the first seal plate receiver 28 and the second seal plate receiver 30. The seal plate retention device 16 may enable the seal plate 18 to be retained within the first seal plate receiver 28 and the second seal plate receiver 30 without a weld. In at least one embodiment, as shown in Figure 4, the seal plate retention device 16 may include one or more first arms 66 extending laterally from a first side 68 of the seal plate 18. The first seal plate receiver 28 may include one or more retention device receivers 70 receiving the first arm 66. The first arm 66 may be positioned at an upstream edge 72 of the seal plate 18. To receive the first arm 66, the retention device receiver 70 in the first seal plate receiver 28 may be positioned at an upstream edge 74 of the first ring segment 20. The first seal plate receiver 28 may include an opening 76 in the upstream edge 74 of the first ring segment 20. The retention device receiver 70 in the first seal plate receiver 28 may include an opening 78 in the upstream edge 74 of the first ring segment 20. The first arm 66 may extend generally orthogonal to the seal plate 18. In another embodiment, the first arm 66 may extend nonorthogonally and nonparallel to the seal plate 18. A downstream edge 102 of the first arm 66 may be orthogonal to the seal plate 18. Alternatively, the downstream edge 102 of the first arm 66 may be nonorthogonal to the seal plate 18, such that the downstream edge 102 of the first arm 66 may extend at an angle relative to the seal plate 18.

The seal plate retention device 16 may include one or more second arms 80 extending laterally from a second side 82 of the seal plate 18. The second seal plate receiver 30 may include one or more retention device receivers 84 receiving the second arm 80. The second arm 80 may be positioned at an upstream edge 72 of the seal plate 18. The retention device receiver 84 in the second seal plate receiver 30 may be positioned at an upstream edge 88 of the second ring segment 22. The second seal plate receiver 30 may include an opening 90 in the upstream edge 72 of the second ring segment 22. The retention device receiver 84 in the second seal plate receiver 30 may include an opening 92 in the upstream edge 72 of the second ring segment 22. The second arm 80 may extend generally orthogonal to the seal plate 18. In another embodiment, the second arm 80 may extend nonorthogonally and nonparallel to the seal plate 18. A downstream edge 104 of the second arm 80 may be orthogonal to the seal plate 18. Alternatively, the downstream edge 104 of the second arm 80 may be nonorthogonal to the seal plate 18, such that the downstream edge 104 of the second arm 80 may extend at an angle relative to the seal plate 18.

The seal system 12 has been described with respect to first and second ring segments 22. However, the seal system 12 is not limited to only being used between two rings segments 20, 22; rather, the seal system 12 may be used with a turbine ring segment assembly 14 formed from a plurality of ring segments 20, 22 forming a ring radially outward of the turbine blades 26. The plurality of ring segments 20, 22 may number more than two ring segments. In at least one embodiment, the first and second ring segments 20, 22 may be a plurality of first and second ring segments 20, 22 forming a ring around a travel path 50 of the turbine blade 26 such that each of the first and second ring segments 20, 22 are joined together via seal plates 18 having at least one seal plate retention device 16. Each first ring segment 20 may include one or more first seal plate receivers 28 receiving at least a portion of the seal plate 18, and each second ring segment 22 may include one or more second seal plate receivers 30 receiving at least a portion of the seal plate 18. This pattern may be repeated as many times as necessary, depending on the number of ring segments, to form a ring.

As shown in Figure 2, the seal plate 16 of the ring segments 20, 22 may be prevented from moving axially by a vane hook 96. The vane hook 96 may be held in position via an iso ring 98. The vane hook 96 prevents the first and second arms 66, 80 from becoming dislodged from residing within the retention device receiver 70 of the first seal plate receiver 28 and the retention device receiver 84 of the second seal plate receiver 30. The vane hook 96 does this by preventing the first and second arms 66, 80 and the seal plate 16 from moving axially upstream. Thus, the first and second arms 66, 80 remain positioned within the retention device receiver 70 of the first seal plate receiver 28 and the retention device receiver 84 of the second seal plate receiver 30, preventing damage from occurring to downstream turbine components.

The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.

Claims

CLAIMS We claim:

1 . A gas turbine engine (10), characterized in that:

a turbine assembly (34) formed from a rotor assembly (36) having at least one turbine blade (26) formed from a generally elongated airfoil (38) having a leading edge (40), a trailing edge (42), a pressure side (44), a suction side (46), a tip (48) at a first end (49) and a platform (51 ) coupled to a second end (53) of the generally elongated airfoil (38) opposite to the first end (49);

first and second ring segments (20, 22) positioned radially outward from the tip (48) of the at least one turbine blade (26), wherein the first and second ring segments (20, 22) are aligned in a circumferentially extending row (24) and form at least a portion of a ring around a travel path (50) of the at least one turbine blade (26) and wherein the first and second ring segments (20, 22) each include an inner surface (52) forming a portion of a hot gas path (54) within the turbine assembly (34); at least one seal plate (18) having at least one seal plate retention device

(16);

at least one first seal plate receiver (28) positioned in a first side surface (58) of the first ring segment (20), wherein the at least one first seal plate receiver (28) receives at least a portion of the at least one seal plate (18);

at least one second seal plate receiver (30) positioned in a second side surface (62) of the second ring segment (22), wherein the first side surface (58) of the first ring segment (20) and the second side surface (62) of the second ring segment (22) face each other and wherein the at least one second seal plate receiver (30) receives at least a portion of the at least one seal plate (18); and

wherein the at least one seal plate retention device (16) is configured to prevent the at least one seal plate (18) from being released from being partially positioned within the at least one first seal plate receiver (28) and the at least one second seal plate receiver (30).

2. The gas turbine engine (10) of claim 1 , characterized in that the at least one seal plate retention device (16) includes at least one first arm (66) extending laterally from a first side (68) of the at least one seal plate (18), and wherein the at least one first seal plate receiver (28) includes at least one retention device receiver (70) receiving the at least one first arm (66).

3. The gas turbine engine (10) of claim 2, characterized in that the at least one seal plate retention device (16) includes at least one second arm (80) extending laterally from a second side of the at least one seal plate (18), and wherein the at least one second seal plate receiver (30) includes at least one retention device receiver (70) receiving the at least one second arm (80).

4. The gas turbine engine (10) of claim 3, characterized in that the at least one second arm (80) is positioned at an upstream edge (86) of the at least one seal plate (18), and wherein the at least one retention device receiver (70) in the at least one second seal plate receiver (30) is positioned at an upstream edge of the second ring segment (22).

5. The gas turbine engine (10) of claim 3, characterized in that the at least one second seal plate receiver (30) includes an opening (90) in the upstream edge of the second ring segment (22), and the at least one retention device receiver (70) in the at least one second seal plate receiver (30) includes an opening (92) in the upstream edge of the second ring segment (22).

6. The gas turbine engine (10) of claim 2, characterized in that the at least one first arm (66) is positioned at an upstream edge (72) of the at least one seal plate (18), and wherein the at least one retention device receiver (70) in the at least one first seal plate receiver (28) is positioned at an upstream edge (74) of the first ring segment (20).

7. The gas turbine engine (10) of claim 6, characterized in that the at least one first seal plate receiver (28) includes an opening (76) in the upstream edge (74) of the first ring segment (20), and the at least one retention device receiver (70) in the at least one first seal plate receiver (28) includes an opening (78) in the upstream edge (74) of the first ring segment (20).

8. The gas turbine engine (10) of claim 1 , characterized in that the at least one seal plate (18) extends from an upstream edge (74) of the first ring segment (20) to a downstream end (94) of the first ring segment (20).

9. The gas turbine engine (10) of claim 1 , characterized in that the first and second ring segments (20, 22) further comprise a plurality of first and second ring segments (20, 22) forming a ring around a travel path (50) of the at least one turbine blade (26) such that each of the first and second ring segments (20, 22) are joined together via seal plates (18) having at least one seal plate retention device (16) and wherein each first ring segment (20) includes the at least one first seal plate receiver (28) receiving at least a portion of the at least one seal plate (18) and each second ring segment (22) includes the at least one second seal plate receiver (30) receiving at least a portion of the at least one seal plate (18).