• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    According to the invention, a multi-stage turbine includes a first turbine stage (34) having a first impeller (38B) having a plurality of first grooves (52B) spaced circumferentially around the first impeller (38B) and a plurality of first blade segments (54) each coupled to at least one of the plurality of first grooves (52B). The multi-stage turbine further includes a second turbine stage (34) including a second impeller (38A) having a plurality of second grooves (52A) spaced circumferentially around the second impeller (38A) and a plurality of second blade segments (54 ) each coupled to at least one of the plurality of second grooves (52A). The multi-stage turbine further includes a one-piece annular interstage seal (60) extending axially between the first and second impellers (38B, 38A), the one-piece annular interstage seal (60) having a first radial support (62B) connected to the first first impeller (38B) and having a second radial support (62A) coupled to the second impeller (38A).
    公开号:CH703590B1
    申请号:CH01274/11
    申请日:2011-07-29
    公开日:2016-07-29
    发明作者:Scott Cummins Josef；David Wilson Ian
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background to the invention
    The present invention relates to a multi-stage turbine with a one-piece, annular intermediate stage seal.
    Generally, gas turbines burn a mixture of compressed air and fuel to produce hot combustion gases. The combustion gases may flow through one or more turbine stages to produce power for a load and / or a compressor. Between the stages, a pressure drop occurs, which can allow a flow of a fluid, such as combustion gases through unintentional paths. Seals may be interposed between the stages to reduce fluid leakage between the stages. Unfortunately, the seals may be exposed to stresses, such as thermal stresses, which may bias the seals in the axial and / or radial directions, thereby reducing the effectiveness of the seals. For example, bowing a seal may increase the possibility of a rubbing condition between stationary and rotating components.
    The object of the present invention is therefore to provide a multi-stage turbine with an improved interstage seal, which has an improved radial and axial stability.
    Brief description of the invention
    According to the invention, a multi-stage turbine includes a first turbine stage comprising a first impeller having a plurality of first grooves circumferentially spaced around the first impeller and a plurality of first rotor segments each having at least one of the first grooves are coupled. The multi-stage turbine further includes a second turbine stage having a second impeller having a plurality of second grooves circumferentially spaced around the second impeller and a plurality of second rotor segments each coupled to at least one of the second grooves.
    The multi-stage turbine further includes a one-piece annular interstage seal extending axially between the first and second impellers, the one-piece annular interstage seal having a first radial support coupled to the first impeller and a second radial support which is coupled to the second impeller, and the one-piece annular interstage seal extends along the circumference over at least two of the plurality of first grooves or at least two of the plurality of second grooves.
    [0006] According to one embodiment, the first radial mount includes a plurality of first radial retention protrusions circumferentially offset from one another, each first radial retention protrusion configured to be coupled to one of the plurality of first grooves in the first impeller to facilitate movement of the first radial retention protrusion one-piece inter-turbine seal in a radial direction to block.
    Brief description of the drawings
    These and other features, aspects and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings in which like reference characters designate like parts throughout the drawings and in which:<Tb> FIG. 1 <SEP> is a schematic block diagram of one embodiment of a gas turbine that may use turbine seals;<Tb> FIG. FIG. 2 shows a cross-sectional side view of the gas turbine according to FIG. 1, cut along the longitudinal axis; FIG.<Tb> FIG. 3 <SEP> is a sectional side view of the gas turbine according to FIG. 2, illustrating an embodiment of an intermediate stage seal between turbine stages;<Tb> FIG. FIG. 4 is a partial cross-sectional side view of the gas turbine of FIG. 2 with blades removed from adjacent stages; FIG.<Tb> FIG. FIG. 5 is a partial cross-sectional side view of the gas turbine of FIG. 2 with the interstage seal removed from adjacent stages; FIG.<Tb> FIG. Fig. 6 is a partial cross-sectional view of one embodiment of radial retaining projections inserted into grooves of a rotor of a turbine engine taken along line 6-6 of Fig. 3;<Tb> FIG. 7 is a cross-sectional side view of a portion of the gas turbine of FIG. 2 illustrating another embodiment of an interstage seal between turbine stages;<Tb> FIG. Fig. 8 is a fragmentary perspective view of one embodiment of the interstage seal as inserted into grooves of the impeller; and<Tb> FIG. FIG. 9 is a fragmentary perspective view of an embodiment of an axial retaining projection engaging the impeller. FIG.
    Detailed description of the invention
    Hereinafter, one or more specific embodiments of the present invention will be described.
    When elements of various embodiments of the present invention are introduced, the articles "a," "an," "the," and "the" mean that one or more of the elements are present. The expressions "comprising", "containing" and "having" are to be understood in the sense of inclusive and mean that there may be other elements besides the listed elements.
    The present disclosure is directed to gas turbine engines incorporating interstage gaskets wherein each interstage gasket includes features to reduce stresses along the axial end surface of the gasket to minimize radial deflection of the gasket and to thermally stabilize the gasket. In addition, these features increase the surface area of the turbine impellers exposed to the cooling air, thereby increasing the strength of the impeller. For example, during operation, the interstage seal may be fully supported by adjacent turbine runners via radial retainers of the seal coupled to the runners. The impellers have grooves for the radial supports of the seal and abutment to block movement of the seals in the radial and axial directions. The radial supports may include dovetails or axial retention protrusions. Further, the interstage seal may form a single piece extending circumferentially over the grooves at a high radius of the turbine runners. The high radius of the interstage seal can increase the interstage volume for cooling as well as the surface areas of the turbine wheels for cooling. Further, the interstage seal may be releasable to allow access to underlying components. For example, the interstage seal may slide axially into and out of an installed position via one or more impellers.
    Fig. 1 shows a block diagram of an exemplary system 10 that includes a gas turbine 12 that can use interstage seals with radial brackets on adjacent wheels. In some embodiments, the system 10 may include an aircraft or aircraft, a watercraft, a locomotive, a power generation system, or combinations of these. The illustrated gas turbine engine 12 includes an air inlet section 16, a compressor 18, a combustor section 20, a turbine 22, and an outlet section 24. The turbine 22 is coupled to the compressor 18 via a shaft 26.
    As indicated by the arrows, air may enter the gas turbine 12 through the inlet section 16 and flow into the compressor 18, which compresses the air prior to its entry into the combustor section 20. The illustrated combustor section 20 includes a combustor shell 28 that is concentrically or annularly disposed about the shaft 26 between the compressor 18 and the turbine 22. The compressed air from the compressor 18 enters the combustion chambers 30, and the compressed air may mix and combust with fuel in the combustion chambers 30 to drive the turbine 22.
    From the combustion chamber portion 20, the hot combustion gases flow through the turbine 22, whereby the compressor 18 is driven via the shaft 26. For example, the combustion gases may exert drive forces on turbine blades within the turbine 22 to rotate the shaft 26. As discussed below, the turbine 22 may include multiple interstage seals with radial brackets on adjacent wheels. After the hot combustion gases have passed through the turbine 22, they can exit the gas turbine 12 through the outlet section 24.
    Fig. 2 shows a cross-sectional side view of one embodiment of the gas turbine 12 of Fig. 1, taken along the longitudinal axis 32. As shown, the gas turbine 22 includes three separate stages 34. Each stage 34 includes a set of blades 36, the are coupled to an impeller 38 which may be rotatably secured to the shaft 26 (Fig. 1). The blades 36 extend radially outwardly from the idler wheels 38 and are partially disposed in the path of the hot combustion gases. Seals 60 extend between adjacent idler wheels 38 and are supported thereby. As discussed below, the seals 60 include radial brackets that are connected to adjacent wheels 38 to provide radial retention while also allowing for improved cooling and removal. Although the gas turbine engine 22 is illustrated as a three-stage turbine, the seals 60 described herein may be employed in any suitable turbine type with any number of stages and shafts. For example, the gaskets 60 may be included in a gas turbine having a multi-stage turbine, in a dual-turbine system including a low-pressure turbine and a high-pressure turbine, or in a steam turbine. Further, the seals 60 described herein may also be used in a rotary compressor, such as the compressor 18 illustrated in FIG. 1.
    As described above with reference to FIG. 1, air enters through the air inlet section 16 and is compressed by the compressor 18. The compressed air from the compressor 18 is then directed into the combustor section 20 wherein the compressed air is mixed with fuel. The mixture of compressed air and fuel is generally combusted within the combustor section 20 to produce high temperature, high pressure combustion gases used to generate torque within the turbine 22. In particular, the combustion gases impart driving forces to the blades 36 to rotate the wheels 38. In some embodiments, a pressure drop may occur at each stage of the turbine that may facilitate gas flow through unintended paths. For example, the hot combustion gases may flow into the interstage space between turbine runners 38, which may introduce thermal stresses on the turbine components. In some embodiments, the interstage space may be cooled by exhaust air tapped from the compressor or provided by another source. However, an influx of hot combustion gases to the interstage space can reduce the cooling effects. Accordingly, the seals between adjacent impellers 38 may be disposed at a high radius to seal and trap the interstage space against the hot combustion gases.
    Fig. 3 shows a cross-sectional side view of a pair of adjacent rotor stages 34, as illustrated in Fig. 2. For illustrative purposes, only a portion of the stages 34 are shown. However, the steps 34 generally include annular impellers 38 with blades 36 extending radially outwardly from an impeller support portion 50 of the impellers 38 (in the direction indicated by the arrow 48). The impeller support portion 50 is disposed along the circumference of the impellers 38 and includes grooves 52 (eg, dovetail grooves) for receiving lower segments 54 of the blade 36. In some embodiments, about 50 to 150 blades 36 may be circumferentially encircled about the impellers 38 (as shown in FIG Arrow 56) and an associated pivot (which extends substantially in the direction indicated by the arrow 58) and spaced therefrom.
    An interstage seal 60 extends between the two adjacent impellers 38A and 38B and is mechanically supported by the impellers 38. The interstage seal 60 is annularly disposed as an integral part between the impellers 38 (in the circumferential direction 56) and is attached to the impellers 38 via radial brackets 62. Each impeller 38 forms an annular structure with the interstage seal 60 extending as an annular structure between the impellers 38. During operation, the impellers 38 and the interstage seal 60 rotate about a common axis. In some embodiments, the interstage seal 60 may be connected to the impellers 38 at or near the same radial location (extending in the direction 48) as the circumferentially spaced grooves 52 within the impellers 38 that hold the blades 36. The interstage seal 60 may include a circular structure of 360 ° attached to adjacent wheels 38 to form a wall that thermally isolates an interstage space or impeller cavity 64 that forms an air cooling chamber.
    The interstage space 64 receives exhaust air that is tapped from the compressor 18 to cool the interstage space 64 and adjacent turbine components, such as the wheels 38. In order to promote cooling, the space 64 is made as large as possible, and hence the interstage seal 60 is fixed to the outermost portion of the running wheels 38 or the impeller support portions 50 when the wall is formed by the interstage seal 60. In particular, portions for securing the interstage seal 60 to the (in the direction 48) radially outer portions of the wheels 38 are arranged. The positioning of the interstage seal 60 toward the radially outer portion (in the direction 48) of the wheels 38 or the wheel support sections 50 increases or maximizes the interstage space 64 to allow cooling in the interstage space 64. In particular, the wall formed by the interstage seal 60 has an inner radius 66. The grooves 52A and 52B have upper, outer radii 68 and 70, respectively, and lower inner radii 72 and 74, respectively. The inner radius 66 of the interstage seal wall may be greater than or equal to both the lower, inner radius 74 and the upper, outer radius 70 of the groove 52B. In addition, the inner wall radius 66 may be greater than or equal to at least one of the lower, inner radius 72 and the upper, outer radius 68 of the groove 52A. The increased size of the interstage space 64 and associated cooling capacity due to the high inner radius 66 of the interstage seal 60 may allow for the use of lower strength materials for the wheels 38. Cooling can also be supported because there is no radial partition in the interstage space. In particular, the volume 64 in the radial direction 48 is a continuous space. Furthermore, the cooling air due to the larger surface area along the wheels 38 can achieve greater convection cooling.
    The interstage seal 60 may cooperate with stationary vanes (not shown) to control the flow of hot fluids, such as hot combustion gases or steam, with a path 76 (generally indicated by an arrow) through the wheels 38 Blades 36 passes, to conduct. In particular, the vane structure may include a sealing surface that cooperates with sealing teeth 78 disposed on the outer surface 80 of the interstage seal 60. In some embodiments, labyrinth seals may be formed between the seal face material and the seal teeth 78. However, in other embodiments, any type of seal may be formed. The seal teeth 78 may be positioned radially outward (in direction 48) of the interstage seal 60. The location of the interstage seal 60 toward the radially outer region (direction 48) of the impellers 38 or the impeller support sections 50 may allow the interstage seal 60 to have a large sealing radius and minimize the radial height of the vane structure. The minimized radial height may reduce the axially facing surface area of the vane structure as well as the axial gas bending loads that may cause a displacement of the position of the vane structure.
    As mentioned above, the interstage seal 60 includes radial brackets 62 to secure the structure 60 to the wheels 38. The radial brackets 62 provide both radial and axial support for the intermediate stage seal 60. A first radial bracket 62B includes radial retaining projections 82. In some embodiments, both the first radial bracket 62B and a second radial bracket 62A of the interstage seal 60 include radial retention projections 82 (see Fig. 7). The radial holding protrusions 82 of the first radial holder 62B are disposed in the grooves 52B to block movement of the radial holding protrusions 82 and thus the interstage seal 60 in the radial direction 48. The radial retention protrusions 82 of the first radial support 62B may include dovetail protrusions 82. The dovetail projections 82 may then be disposed in the dovetail grooves 52B to block movement of the dovetail projections 82 in the radial direction 48. The lower segments 54 of the blades 36 are also disposed in the grooves 52B so as to block movement of the radial retaining projections 82 in the axial direction 58 in this manner.
    The second radial support 62A includes axial protrusions 84. The axial protrusions of the second radial support 62A may contact radial abutments of the impeller 38A, thereby providing axial and radial retention for the interstage seal 60. The radial abutments may include an edge 86 of the impeller 38A, axial protrusions 87 with rope sealing grooves 88 of the impeller support portion 50 and axial protrusions 95 of the blades 36 (see Fig. 4). The axial retainer projections 84 of the second radial retainer 62A may include a cover plate portion 90, seal-interactive portions 92, and edge-interacting portions 94. The cover plate portion 90 cooperates with both the impeller support portion 50 and the lower segments 54 of the blades 36. The eye seal groove interaction sections 92 may be coupled to the eye seal grooves 88 of the axial projections 87 to form a channel 96 for a rope seal 98. The blades 36 may also include axial projections 95 with rope sealing grooves 99 (see Fig. 4). The shroud grooves 99 of the blades 36 and the shallow grooves 88 of the impeller support portion 50 may extend circumferentially 360 ° in the direction 56 around the impeller 38A and, together with the rope seal 38, minimize leakage from the stationary components of the machine. In some embodiments, the blades 36 and the axial protrusions 87 of the impeller support portion 50 may further include retention slots. The retention slots of the blades 36 and the retention slots of the wheel support section 50 may extend circumferentially 360 ° in the direction 56 around the impeller 38A and, together with a blade retention wire, provide axial retention for the blade 36. The edge interaction portions 94 may interact with the rim 86 of the impeller 38A to block movement of the axial retention projection 84 of the second radial support 62A in the radial direction 48. In some embodiments, the edge interaction portions 94 may form crimped connections with the rim 86 of the impeller 38A.
    FIG. 4 illustrates a cross-sectional side view of the pair of adjacent turbine stages 34. During servicing or other disassembly processes, the blades 36 may extend out of the grooves 52A in an axial direction 108 or removed from the grooves 52B in an axial direction 110. During installation, the interstage seal 60 may slide axially over the impeller 38B to a position between the impellers 38A and 38B while the blades 36 are removed. The interstage seal 60 can slide over the impeller 38B in the axial direction 108, while the radial retention protrusions 82 of the first radial support 62B slide in the same direction 108 through the grooves 52B. During this movement, both retaining projections 82 and 84 of the first and second radial supports 62B and 62A, respectively, can be aligned with and slide through the grooves 52B. The intermediate stage seal 60 slides in the axial direction until the axial retention projection 84 of the second radial support 62A contacts the radial abutments 86 and 87 of the impeller 38A or impeller support portion 50 as described above to form the interstage seal. The radial abutments 86 and 87 block further movement of the intermediate stage seal 60 in the axial direction 108. The blades 36 may be reinserted into the grooves 52A and 52B where the lower segments 54 of the blades 36 inserted into the grooves 52B move the radial retention projections 82 of the first radial support 62B in the axial direction 110. Further, upon reintroduction of the blades 36, the axial retention protrusion 84 of the second axial support 62A contacts the radial abutment 95 of the impeller 38A to form the interstage seal.
    FIG. 5 illustrates the release of the interstage seal 60 from the pair of adjacent turbine runners 38. With the blades 36 removed from the slots 52A and 52B, the interstage seal 60 may slide in the axial direction 110 around the radial retention protrusions 82 of the first radial runners Remove bracket 62B from grooves 52B. During this removal, both retaining projections 82 and 84 of the first and second radial supports 62B and 62A, respectively, can be aligned with and slide through the grooves 52B. In embodiments having radial retention protrusions 82 of the first radial support 62B at one end of the interstage seal 60, as illustrated in FIG. 5, only the blades 36 in the grooves 52B need to be removed to remove the interstage seal 60 in the axial direction 110. The removal of the interstage seal 60 provides access to components normally under the interstage seal 60 without disassembling other components of the turbine 22.
    6 shows a partial cross-sectional view of one embodiment of the interstage seal 60 having a plurality of radial retention protrusions 82 of the first radial support 62B inserted into grooves 52B of the impeller 38B taken along line 6-6 of FIG. The impeller support portion 50 of the impeller 38B includes a plurality of protrusions 118 extending radially outward from the impeller 38B. The protrusions 118 are circumferentially spaced around the impeller 38B so as to form circumferentially spaced grooves 52B. The grooves 52B may be dovetail grooves 52B. The grooves 52B formed by the spaced projections 118 may include a wavy, curved or generally non-linear surface defined by a plurality of peaks and valleys. For example, the surface may include tabs or tabs 120. The radial holding protrusions 82 of the first radial holder 62B of the interstage seal 60 are circumferentially offset from each other and inserted into the grooves 52B. The radial retention protrusions 82 of the first radial support 62B may be dovetail protrusions 82. Similar to the grooves 52B, the dovetail projections 82 may include a corrugated, curved or generally non-linear surface 121 defined by a plurality of peaks and valleys. For example, dovetail projections 82 may include tabs 122 interposed between tabs 120 of dovetail slots 52B. The protrusions 82 of the first radial support 62B may extend completely or only partially into the grooves 52B in the radial direction 124 leaving a gap between the protrusions 82 and the impeller 38B. This clearance allows further cooling of the impeller 38B and the impeller support portion 50. The interaction between the tabs 120 and 122 may prevent the radial retention protrusions 82 of the first radial support 62B from being displaced in the radial direction 126. In other words, lugs 120 and 122 do not permit radial movement of interstage seal 60 on impeller 38B. In addition, the grooves 52B block the movement of the protrusions 82 of the first radial support 62B in the circumferential direction 128. As partially illustrated, the interstage seal 60 forms a single annular member that extends circumferentially across multiple grooves 52B and extends 360 ° over all Grooves 52B can extend across. For example, the interstage seal 60 may extend for 2 to 50, 2 to 25, 2 to 10, or 2 to 5 slots.
    As mentioned above, both the first and second radial retainers 62B and 62A of the interstage seal 60 may each include a plurality of radial retention protrusions 82. Fig. 7 illustrates an embodiment with the interstage seal 60 including first radial retention protrusions 82B of the first radial support 62B and second radial retention protrusions 82A of the second radial support 62A disposed in the grooves 52B and 52A of the wheels 38B and 38A, respectively. Insertion of the first and second protrusions 82B and 82A of the first and second radial brackets 62B and 62A, respectively, into the grooves 52B and 52A blocks movement of the interstage seal 60 in the radial direction indicated by the arrows 138 and 144. The lower segments 54 of the blades 36 are disposed in the grooves 52A and 52B to block the movement of the radial retaining projections 82A and 82B in axial directions 140 and 142, respectively. The radial retention protrusions 82A and 82B of the second and first radial supports 62A and 62B, respectively, may include dovetail protrusions 82, and the grooves 52A and 52B may include dovetail grooves 52 as described in connection with FIG. The dovetail projections 82A may be oriented in a radially outward direction 138 that is opposite to the radially inwardly facing orientation direction 144 of the dovetail projections 82B. In embodiments where the two radial retention protrusions 82A and 82B include dovetail protrusions 82, the interstage seal 60 extends circumferentially over at least two of the grooves 52A and at least two of the grooves 52B, as illustrated in FIG. 6, and the interstage seal 60 may extend circumferentially over all the grooves 52A and 52B to form the wall between the impellers 38A and 38B.
    Fig. 8 is a fragmentary perspective view of one embodiment of the interstage seal 60 inserted in grooves 52B of the impeller 38B. The one-piece interstage seal 60, as illustrated in FIG. 8, includes seal teeth 78, the first radial support 62B with radial retention protrusions 82, and the second radial support 62A with axial retention protrusions 84. The seal teeth 78 may extend circumferentially through 360 ° Direction 154 and interact with vane structures, as described above. The axial retention protrusions 84 of the second radial support 62A include the cover plate portion 90 and the edge interaction portions 94. The cover plate portion 90 may extend continuously circumferentially 360 degrees in the direction 154 and interact with the lower segments 54 of the blades 36 or impeller support portion 50 , The edge interaction sections 94 may be spaced apart by gaps 156. These gaps 156 are aligned with the protrusions 118 of the impeller 38B and gaps between the radial retention protrusions 82 of the first radial support 62B occupied by the protrusions 118. The gaps 156 may be shaped similar to the upper portions 158 of the protrusions 118 of the impeller 38B, thereby facilitating the alignment of the retention protrusions 82 and 84 with the grooves 52B, thus allowing the edge interaction portion 94 of the axial retention protrusions 84 of the second radial support 62A. to slide axially through the grooves 52B. The radial retention protrusions 82 of the first radial support 62B may include dovetail protrusions 82 as described in connection with FIG. The protrusions 82 may be disposed in the grooves 52B, thereby allowing the seal to extend circumferentially beyond at least two of the grooves 52B. The grooves 52B may include dovetail grooves 52B.
    Fig. 9 is a fragmentary perspective view of one embodiment of the interstage seal 60 abutting the impeller 38A and the impeller support portion 50. Figs. The interstage seal 60, as illustrated in FIG. 9, includes seal teeth 78 and the second radial mount 62A with axial retention protrusions 84. The axial retention protrusions 84 of the second radial mount 62A include the cover plate section 90, the ring seal groove interaction section 92, and the edge interaction sections 94 Cover plate portion 90 and the seichtichtungswirkwirkungsabschnitte 92 operate in the manner described above. The edge interaction sections 94 are coupled to a bottom surface 168 of the rim 86 of the impeller 38A. The gaps 156 between the edge interaction portions 94 provide access for cooling air 170 from the interstage space 64. The cooling air 170 facilitates cooling of the upper portion of the impeller 38A, the impeller support portion 50, and the lower segments 54 of the blades 36. As mentioned above, this cooling allows that a lower strength material can be used for the wheels 38.
    The radial brackets 62 of the interstage seal 60 described in the preceding embodiments provide both axial and radial retention by being connected to the wheels 38, thus permitting the use of a lighter structure 60 These radial brackets 62 exposed at a high radius of the wheels 38, a larger surface area of the wheels 38 of the cooling air of the interstage space 64, whereby the use of a lower strength material for the wheels 38 is made possible. This high radial position of the interstage seal 60 also allows a reduction in the size of the nozzle, i. the radial dimension of the vanes. Further, the construction of the radial brackets 62 allows for the removal of the interstage seal 60 in the axial direction through the slots 52 for the blades 36 without having to unstack or disassemble the rotor.
    The invention relates to a multi-stage turbine 22 which includes a first turbine stage 34 which includes a first impeller 38B having a plurality of first grooves 52B circumferentially spaced around the first impeller 38B and a plurality of first blade segments are each coupled to at least one of the plurality of first grooves 52B. The multi-stage turbine 22 further includes a second turbine stage 34 including a second impeller 38A having a plurality of second grooves 52A circumferentially spaced around the second impeller 38A and a plurality of second blade segments each having at least one of the plurality of second blades Grooves 52A are coupled. The multi-stage turbine 22 further includes a one-piece annular interstage seal 60 extending axially between the first and second impellers 38B, 38A, the one-piece interstage seal 60 having a first radial support 62B coupled to the first impeller 38B and a first radial support 62B second radial support 62A coupled to the second impeller 38A and the one-piece interstage seal 60 extend circumferentially over at least two of the plurality of first grooves 52B or at least two of the plurality of second grooves 52A.
    LIST OF REFERENCE NUMBERS
    [0030]<Tb> 10 <September> System<Tb> 12 <September> Gas Turbine<Tb> 16 <September> air intake portion<Tb> 18 <September> compressor<Tb of> 20 <September> combustor section<Tb> 22 <September> Turbine<Tb> 24 <September> outlet<Tb> 26 <September> wave<Tb> 28 <September> combustion chamber housing<Tb> 30 <September> combustion chamber<Tb> 32 <September> longitudinal axis<Tb> 34 <September> Level<Tb> 36 <September> blade<Tb> 38 <September> Wheels<Tb> 48 <September> direction<Tb> 50 <September> wheel support section<Tb> 52 <September> grooves<tb> 54 <SEP> Lower Segments<Tb> 56 <September> direction<Tb> 58 <September> direction<Tb> 60 <September> interstage seal<tb> 62 <SEP> Radial mounts<Tb> 64 <September> intermediate space<tb> 66 <SEP> Inner radius<tb> 68 <SEP> Upper radius<tb> 70 <SEP> Upper radius<tb> 72 <SEP> Lower radius<tb> 74 <SEP> Lower radius<Tb> 76 <September> flow path<Tb> 78 <September> seal teeth<Tb> 80 <September> outer surface<tb> 82 <SEP> Radial Retaining Tabs<tb> 84 <SEP> Axial Retaining Tabs<Tb> 86 <September> Rand<Tb> 88 <September> Seildichtungsnut<Tb> 90 <September> top plate portion<Tb> 92 <September> Seildichtungsnutwechselwirkungsabschnitt<Tb> 94 <September> Rand interaction section<tb> 95 <SEP> Axial lead<Tb> 96 <September> Channel<Tb> 98 <September> rope seal<Tb> 99 <September> Seildichtungsnut<Tb> 108 <September> axial<Tb> 110 <September> axial<Tb> 118 <September> projections<Tb> 120 <September> Nose<Tb> 122 <September> Nose<Tb> 124 <September> direction<Tb> 126 <September> radial direction<Tb> 128 <September> direction<Tb> 138 <September> radial direction<T b> 140 <September> axial direction<Tb> 142 <September> axial<Tb> 144 <September> direction<Tb> 154 <September> direction<Tb> 156 <September> gap<Tb> 168 <September> bottom
    权利要求:
    Claims (10)
    [1]
    1. Multi-stage turbine (22), comprising:a first turbine stage (34) having a first impeller (38B) having a plurality of first grooves (52B) circumferentially spaced around the first impeller (38B) and a plurality of first blade segments each connected to at least one of first grooves (52B) are coupled;a second turbine stage (34) having a second impeller (38A) having a plurality of second grooves (52A) circumferentially spaced around the second impeller (38A) and a plurality of second blade segments each being connected to at least one of second grooves (52A) are coupled;a one-piece annular interstage seal (60) extending axially between the first and second impellers (38B, 38A), the one-piece annular interstage seal (60) having a first radial support (62B) connected to the first impeller (38B ) and a second radial support (62A) coupled to the second impeller (38A) and the one-piece annular interstage seal (60) circumferentially over at least two of the plurality of first grooves (52B) or at least two the plurality of second grooves (52A) extends.
    [2]
    The multi-stage turbine (22) of claim 1, wherein the one-piece interstage seal (60) is a one-piece annular seal (60) extending circumferentially throughout the plurality of first grooves (52B) and all the plurality of second grooves (52A).
    [3]
    The multi-stage turbine (22) of claim 1, wherein the first radial support (62B) has a plurality of first radial retention protrusions (82, 82B) and each first radial retention protrusion (82, 82B) is disposed in one of the plurality of first grooves (52B) to positively block movement of the one-piece annular interstage seal (60) in a radial direction.
    [4]
    The multi-stage turbine (22) of claim 3, wherein each first radial retention protrusion (82, 82B) has a first dovetail projection (82, 82B) and each of the plurality of first grooves (52B) has a dovetail groove (52B).
    [5]
    The multi-stage turbine (22) of claim 3, wherein each first vane segment is disposed in one of the plurality of first grooves (52B) to block movement of one of the first radial retention projections (82, 82B) in an axial direction.
    [6]
    The multi-stage turbine (22) of claim 5, wherein the one-piece, annular, intermediate-stage seal (60) is configured to be insertable along the axial direction via the first impeller (38) between the first and second impellers (38) the first plurality of blade segments are removed from the plurality of first grooves (52B), each first radial retaining projection (82) being configured to extend along one of the plurality of first grooves (52) in the axial direction upon insertion of the one-piece interstage seal (60) Pass through axial direction.
    [7]
    The multi-stage turbine (22) of claim 3, wherein the second radial support (62A) has a plurality of second radial retention protrusions (82, 82A) and each second radial retention protrusion (82, 82A) is disposed in one of the plurality of second grooves (52A) to positively block movement of the one-piece annular interstage seal (60) in the radial direction.
    [8]
    The multi-stage turbine (22) of claim 3, wherein the second radial support (62A) includes at least one axial retention protrusion (84) configured to contact a radial abutment of the second impeller (38A) Movement of the one-piece, annular intermediate stage seal (60) in the radial direction to block by positive engagement.
    [9]
    The multi-stage turbine (22) of claim 1, wherein the plurality of first grooves (52B) extend from a first inner radius (74) to a first outer radius (70), the plurality of second grooves (52) extend from a second inner radius Extending radius (72) to a second outer radius (68), the one-piece annular interstage seal (60) having a wall extending between the first and second impellers (38B, 38A), the wall having an inner radius (66), which is greater than or equal to both the first and second inner radii (74, 72) of the first and second grooves (52B, 52A), and the inner radius (66) is greater than or equal to at least the first and / or second outer Radius (70, 68) of the first and second grooves (52B, 52A) is.
    [10]
    The multi-stage turbine (22) of claim 9, wherein the wall defines an outer radial boundary of an air cooling chamber between the first and second impellers (38).
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    同族专利:
    公开号 | 公开日
    CN102418563A|2012-04-18|
    US8511976B2|2013-08-20|
    US20120027584A1|2012-02-02|
    DE102011052240A1|2012-02-02|
    JP6018367B2|2016-11-02|
    JP2012031865A|2012-02-16|
    CN102418563B|2015-11-25|
    CH703590A2|2012-02-15|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2018-02-28| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/848,906|US8511976B2|2010-08-02|2010-08-02|Turbine seal system|
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