Gas turbine casing support device

Abstract

Support device for a casing element (85) of a gas turbine (20), wherein the gas turbine (20) has a rotating shaft (40) which defines a radial direction perpendicular to it, wherein the device has: an outer casing block (80) which has a coupling that can be connected to a housing of the turbine (35); a shell element (85) with a front flange (310) and a rear flange (350), wherein the shell element (85) is attached to the outer shell block (80) via the front flange (310) and the rear flange (350); a damper arranged between the outer shell block (80) and the shell element (85) with a translational degree of freedom between the damper and the outer shell block (80), wherein the degree of freedom defines a direction of movement (265) of the damper, wherein the direction of movement (265) forms an angle greater than 0° to the radial direction of the turbine (35); a preload element (220) arranged in the outer shell block (80), wherein the preload element (220) is in operational connection between the outer shell block (80) and the shell element (85) via the damper, wherein a preload force of the preload element (220) is directed along the direction of movement (265) of the damper, and a first pin (105) extending through an opening (315) of the front flange (310) or the rear flange (350), characterized by a deformation area (345) between a head (330) of the first pin (105) and the outer sheath block (80).

Description

[0001] The invention relates to gas turbines and in particular to gas turbine shroud supports.

[0002] In a gas turbine plant, such as might be used to generate electrical power, it is desirable for the rotor blades to rotate within a turbine casing or "shroud" at a reduced pitch to deliver increased efficiency relative to the amount of energy to be extracted from an expanding working fluid. Typically, by maintaining a reduced threshold for the clearance between the shroud and the tips of the rotor blades, unwanted "leakage" of hot gas over the tips of the rotor blades can be prevented and increased efficiency achieved. Increased pitches lead to leakage problems and cause a reduction in the overall efficiency of the turbine.

[0003] Ceramic matrix composites offer advantages in contact with the hot gas path as a material of choice for shroud elements in a turbine. These ceramic matrix composites can withstand high operating temperatures and are suitable for use in the hot gas path of gas turbines. Recently, melt-infiltrated (MI) silicon carbide / silicon carbide (SiC / SiC) ceramic matrix composites (CMC) have been processed into high-temperature static components, such as gas turbine shrouds. Due to their heat resistance, turbine components made of ceramic matrix composites, such as those made from MI-SiC / SiC components, generally enable a reduction in coolant flow compared to metallic components.

[0004] It is recognized that the shroud elements are subject to vibrations due to pressure pulses from the hot gases as the individual blades pass through the shroud. Furthermore, due to this proximity to the high-speed rotating blades, the vibrations may be at or near resonant frequencies, necessitating damping to extend the expected service life during long-term commercial turbine operation. Ceramic composites require special attachment and exhibit numerous failure mechanisms, such as wear, oxidation, stress concentration, and damage to the ceramic composite when the composite is adapted for attachment to the metallic components.Accordingly, there is a need to address the dynamic issues associated with the attachment of ceramic composite shells to metallic turbine components to minimize adverse natural vibration responses.

[0005] US 2007 / 0280820 A1 discloses a support device for a shroud element of a gas turbine, which has the features of the preamble of independent claim 1.

[0006] US 2005 / 0158168 A1 discloses a support device for a shroud element of a gas turbine, comprising an outer shroud block connected to a casing of the gas turbine via a coupling, and a shroud element having a front flange and a rear flange, via which the shroud element is attached to the outer shroud block. The shroud element is secured to the outer shroud block via threaded pins extending through openings in the front and rear flanges.

[0007] US 2006 / 0067815 A1 discloses a shroud support device having a stationary shroud element, a movable shroud element surrounding rotor blades, and biasing means holding the movable shroud element and biasing it radially against the rotor blades. Brief description of the invention

[0008] According to the invention, a support device for a shroud element of a gas turbine is provided, wherein the gas turbine has a rotating shaft that defines a radial direction perpendicular to the shaft. The device includes an outer shroud block with a coupling that is connectable to a casing of the gas turbine, and a shroud element with a front flange and a rear flange. The shroud element is attached to the outer shroud block via the front flange and the rear flange. The device further includes a damper arranged between the outer shroud block and the shroud element, and a biasing element arranged within the outer shroud block. A translational degree of freedom between the damper and the outer shroud block defines a direction of movement of the damper. The direction of movement forms an angle greater than 0° to the radial direction of the gas turbine.The preloading element is operatively connected to and between the outer shell block and the shell element via the damper, with a preload force of the preload element being directed along the direction of movement of the damper. The device further includes a first pin extending through an opening in the front flange or the rear flange, and a deformation region between a head of the first pin and the outer shell block.

[0009] Particularly preferred embodiments of the invention are the subject of the dependent claims.

[0010] These and other advantages and features will be more readily understood from the following detailed description of preferred embodiments of the invention taken in conjunction with the accompanying drawings. Short description of the drawings

[0011] Reference is made to the exemplary drawings, in which the same elements are numbered the same in the attached figures: Fig. 1 shows a schematic drawing of an embodiment of a turbine according to an embodiment of the invention; Fig. 2 shows an isometric exploded view of a shroud assembly according to an embodiment of the invention; Fig. 3 shows a cross-sectional view of the jacket arrangement of Fig. 2, viewed circumferentially around an axis of the turbine, according to an embodiment of the invention; Fig. 4 shows a cross-sectional view of the jacket arrangement of Fig. 2 viewed in the axial forward direction according to an embodiment of the invention; Fig. 5 shows a perspective top view of shell surfaces according to an embodiment of the invention; Fig. 6 shows another isometric exploded view of the shroud assembly according to an embodiment of the invention; Fig. 7 shows an enlarged cross-sectional view of a front flange portion of a shell member and a connecting pin according to an embodiment of the invention; and Fig. Figure 8 shows an enlarged end view of a front flange portion of the shell member and the connecting pin of Fig. 7 according to an embodiment of the invention. Detailed description of the invention

[0012] One embodiment of the invention provides a shroud assembly with a canted damper block for improved sealing and vibration tolerance. Other features described herein improve sealing within the assembly and reduce the operating clearances to the rotating blades to reduce leakage across the rotating blades, thereby increasing engine efficiency.

[0013] Fig. 1 shows a schematic drawing of one embodiment of a turbine system 20, such as a gas turbine 20. The gas turbine 20 includes a combustor 25. The combustor 25 burns a mixture of fuel and oxidizer to produce a gas flow 30 that is hot and energetic. The gas flow 30 from the combustor 25 then moves to a turbine 35. The turbine 35 includes an array of turbine blades (not shown). The gas flow 30 transfers energy to the blade assembly, causing the blade assembly to rotate. The blade assembly is connected to a shaft 40. The shaft 40 rotates in response to rotation of the blade assembly. The shaft 40 is then used to drive a compressor 45. The shaft 40 can optionally supply energy 50 to another output device (not shown), such as an electrical generator.Compressor 45 receives and compresses an oxidant flow 55. Following compression of oxidant flow 55, a compressed oxidant flow 60 is supplied to combustion chamber 25. The compressed oxidant flow 60 from compressor 45 is mixed with a fuel flow 65 from a fuel supply system 70 to form the fuel / oxidant mixture within combustion chamber 25. The fuel / oxidant mixture then undergoes combustion within combustion chamber 25.

[0014] Fig. Figure 2 shows an isometric exploded view of a shroud assembly 75, which in its cross-sectional views with reference to the Fig. 3 and Fig. 4 is further explained.

[0015] The Fig. 3 and Fig. 4 show the shroud assembly 75 having an outer shroud block 80 or body for securing a plurality of shroud members 85, such as stationary shroud members 85, disposed proximate a row of turbine blades (not shown). Fig. 3 is a view in a circumferential direction, wherein a flow of the hot and energetic gas 30 moving through the engine 20 is directed from left to right, and rotation of the blades (not shown) about an axis 90 of the shaft 40 determines an axial direction of the turbine 35 and the outer shroud block 80. Accordingly, the pressure of the hot and energetic gas 30 is greater at a forward end 95 of the outer shroud block 80 (before transferring energy from the hot and energetic gas 30 to the blade assembly) than at a rearward end 100 (following the transfer of some energy to the blades).

[0016] Fig. Fig. 4 is a view in an axial forward direction opposite to the direction of flow of the hot and energetic gas 30 through the turbine 35. The flow of the hot and energetic gas 30 is shown in, for example, Fig. 4 is directed out of the plane of the drawing, resulting in a counterclockwise rotation 103 of the turbine blades about the axis 90. The tips of the blades (not shown) are arranged in close proximity to the shroud elements 85. Any leakage of the hot and energy-rich gas 30 between the blades and the shroud elements 85 results in a loss of efficiency of the engine 20. For example, if the distance between the tips of the blades and the shroud elements 85 is increased, the efficiency of the engine 20 decreases.

[0017] With reference to Fig. 4: The shroud block 80 preferably carries three individual shroud elements 85. It will be appreciated that a number of shroud blocks 80 are arranged in a circumferential row around the axis 90 and support a plurality of shroud elements 85 that surround the hot gases flowing through the turbine 35 and form part of the hot gas path. The shroud elements 85 are constructed of a ceramic composite material, secured by pins 105, 110 (best shown in Fig. 3) are attached to the jacket blocks 80 and have an inner surface 115 in contact with the hot and energetic gas 30 of the hot gas path.

[0018] Fig. 5 represents a graphic representation of a photograph of an underside of the jacket assembly 75 Fig. 4 with three cladding elements 85. In one embodiment, the cladding elements 85 include a ceramic matrix composite (CMC) material, which offers enhanced suitability for high temperatures. Embodiments of the CMC material are contemplated including an environmental barrier coating (EBC) in conjunction with a multidirectional ply architecture, such as melt-infiltrated silicon carbide fiber-reinforced silicon carbide ceramic matrix composites (SiC / SiC CMCs). In one embodiment, the inner surface 115 of the cladding element containing the CMC material further includes a raised pattern 120.It has been found that applying the raised pattern 120 to the inner surface 115 of the shroud member 85 increases the surface area of ​​the inner surface 115 and reduces the flow between the rotating blades and the shroud member 85 to act in a manner similar to reducing the distance between the rotating blades and the shroud member 85, thereby increasing efficiency.In another embodiment, the raised pattern 120 includes an abradable CMC material such that blade tips abut the inner surface 115 of the shroud elements 85 and abrade or wear away a small amount of the abradable raised pattern 120 of CMC material from the inner surface 115, thereby creating a reduced clearance arc on the inner surface 115 of the shroud elements 85 that closely matches the arc resulting from rotation of the blade tips. Furthermore, the use of an abradable material allows the reduced clearance to closely match the arc resulting from rotation of the blade tips on the inner surface 115 of the shroud element 85 without the complexity and cost associated with manufacturing such an arc.

[0019] Again referring to the Fig. 3 and Fig. 4: The outer shroud block 80 fits into a casing 125 (also referred to herein as a "shroud") of the gas turbine 35. The shroud block 80 is attached to a housing 125 that extends radially inward from an inner wall 130 of the housing 125 toward the axis 90. A T-hook 135 may be arranged as an annular series of teeth that engage opposite sides of a groove 140 that extends the length of the outer shroud block 80 such that the groove 140 provides attachment to the T-hook 135 of the housing 125. The outer shroud block 80 may be a unitary block that slides over the T-hook 135, or a pair of left and right block halves that clamp over the T-hook 135. Each block 80 fits into a cavity 145 within the housing 125 proximate the rotating part of the turbine 35.

[0020] The outer shroud blocks 80 may be formed from a metal alloy sufficiently temperature-tolerant to withstand the temperatures of the combustion exhaust gases. A small portion of the metallic outer shroud block 80, for example, near the shroud 85, may be exposed to the hot and energetic gases 30 from the flow path of the turbine 35.

[0021] A damper system 150 is disposed within the outer shroud block 80. The damper system 150 includes a damper block / shroud element transition region 155, a damper force transfer device 160, and a damper device 165. The damper block / shroud element transition 155 includes a damper block 170 in contact with the shroud element 85. In one embodiment, the damper block 170 is constructed of a metallic material, such as PM2000, a superalloy material with high temperature service limits of up to 1204°C (2200°F). As shown in the Fig. 3 and Fig. 4, a radially inwardly facing surface 175 of the damper block 170 and a radially outwardly facing surface 180 of the shell member 85 are parallel and adjacent and are in substantially surface contact. In one embodiment, substantially the entire surface of the radially inwardly facing surface 175, such as the surface defined within a perimeter 183 (as best shown in Fig. 6) of the damper block 170, contacts the radially outwardly facing surface 180 of the shroud member 85. Increasing the area of ​​such surface-to-surface contact reduces the amount of stress that develops within the shroud member 85 in response to a force between the shroud member 85 and the damper block 170, such as pressure pulses generated by the rotating blades. The reduced contact stresses on the damper block 170 result in reduced wear and thereby extend the useful life of the damper block 170. Furthermore, the surface contact seals the surfaces 175, 180, thereby reducing the flow of the hot and energetic gas 30 between the shroud member 85 and the damper block 170 from the forward end 95 to the aft end 100 of the shroud assembly 75. In one embodiment, for example,the radially inwardly facing surface 175 and the radially outwardly facing surface 180 are each planar surfaces 175, 180 in surface-to-surface contact.

[0022] Fig. 6 shows an isometric exploded view of the jacket assembly 75. Referring now to the Fig. 4 and Fig. 6: An upper guide 185 of the damper block 170 is shown. The upper guide 185 has a prism geometry that abuts the outer shell block 80 (as best shown in Fig. 4). A close tolerance contact area between the upper guide 185 and the outer shroud block 80 reduces the leakage of cooling air between the upper guide 185 and the outer shroud block 80. The upper guide 185 has a geometry with guide surfaces 190, 195 that mate with or abut corresponding guide surfaces 200, 205 of the outer shroud block 80. The guide surfaces 200, 205, in conjunction with the guide surfaces 190, 195, define a translational degree of freedom of the damper block 170 relative to the outer shroud block 80, thereby establishing a direction of movement 265 of the damper block 170. In one embodiment, the surfaces 190-205 are planar surfaces 190-205 such that the close tolerance contact area between the planar surfaces 190-205 provides a side-by-side arrangement and prevents rotation of the damper block 170 within and relative to the outer shell block 80.In one embodiment, the outer guide 185 has four sides 190, 195, 207, 208 having a rectangular geometry.

[0023] Again referring to the Fig. 3 and Fig. 4: The damper force transfer device 160 also includes a disk cup 210 and a thermally insulating disk 215. The disk 215 is disposed within the cup 210, which is in direct mechanical communication with the damper block 170. The cup 210 provides a support for the thermally insulating disk 215, which interrupts the thermal conduction path from the upper guide 185 of the damper block 170 to a biasing element 220, such as a spring, disposed proximate a first portion 222 of the outer shell block 80. In one embodiment, the thermally insulating disk 215 includes materials such as monolithic ceramic silicon nitride and a machinable glass-ceramic, such as MACOR (commercially available from Corning Inc., Corning, New York).

[0024] The damper assembly 165 includes the spring 220. The spring 220 is pre-rated for temperature and load prior to assembly to improve compliance with design specifications. The spring 220 is mounted within a cup-shaped block 225, which is mechanically retained, e.g., via threads, in the shell block 80. The spring 220 is biased to engage the insulating disc 215 at one end to bias the damper block 170 radially inward via the disc cup 210. The opposite end of the spring 220 is operatively connected to the outer shell block 80 via the cup-shaped block 225.

[0025] Fig. 3 shows a cooling channel 230 in fluid communication with the compressor 45 for delivering a cooling flow of exhaust air via an internal cavity 235 to the spring 220. The cup-shaped block 225 has openings 240 that allow the cooling flow via the cooling channel 230 to maintain the temperature of the spring 220 below a predetermined temperature and thus control the degree of stress recovery through forced convection. Accordingly, the spring can be made of low-temperature metal alloys and have a positive preload on the damper block 170 in the direction of travel 265, as described further below. The discharged coolant is expelled via a path 245. The disc cup 210 ensures the retention and preload of the spring 220 in the event of a rupture of the insulating disc 215.

[0026] A vent plug 250 is disposed in a counterbore 255 of the cooling channel 230. The vent plug 250 has a surface 260 having a bore to control the amount and rate of coolant flow toward the spring 220. For example, following simulated or instrumented testing, it may be determined that a particular coolant flow rate maintains a desired maximum temperature of the spring 220. A greater coolant flow than the specified flow rate is undesirable because it increases the performance requirements of the compressor 45 and results in a loss of efficiency of the machine 20. Furthermore, such coolant reductions enable transient (warm-up) improvements in the heat expenditure coefficient.Accordingly, calculations can determine a suitable geometry of surface 260 to provide the desired flow rate and prevent unnecessary coolant flow greater than that determined to produce the desired temperature of spring 220. In the event of a change in operating parameters within machine 20 or in the desired coolant flow, vent plug 250 can be replaced with one having a suitable geometry of surface 260.

[0027] A radial direction R of the turbine 35 is perpendicular to the axis 90. A preload force provided by the spring 220 between the block 180 and the damper block 170 is aligned with the direction of movement 265 of the damper block 170, which is offset with respect to the radial direction R. The direction of movement 265 and the radial direction R can, for example, include an offset angle θ between them. Accordingly, the preload force of the spring 220 exerted on the damper block 170 is directed along the direction of movement 265 and can be divided into an axial component 270, which is aligned with the axis 90 and directed towards the rear end 100 of the outer shroud block 80, and a radial component 275, which is aligned with the radial direction R and directed radially inward.

[0028] In operation, the radial component 275 of the biasing force of spring 220 maintains a radially inward force on the damper block 170. The damper block 170, in turn, presses against the radially outward-facing surface 180 of the shell member 85 to dampen vibrations and, in particular, to prevent a vibrational response of the shell member 85 at or near resonant frequencies. The axial component 270 of the biasing force of spring 220 exerts an axial force on the damper block 170 directed toward the rear end 100 of the second portion 278 of the outer shell block 80, which is disposed proximate the shell member 85. Therefore, a sealing surface 280 is arranged at the rear end 283 of the damper block 170, which is in contact with the rear end 100 of the second portion 278 of the outer shell block 80 and is biased towards it.The sealing surface 280 provides axial support to the damper block 170, reduces the vibration response of the damper block 170, and seals the damper block 170 against the outer shroud block 80. Sealing the damper block 170 against the outer shroud block 80 reduces the bypass of hot and energetic gas 30 from the front end 95 to the rear end 100 around the blades, thereby increasing the efficiency of the engine 20.

[0029] Fig. 4 shows seals 285 disposed within adjacent seal receiving areas 290, such as seal receiving grooves of adjacent damper blocks 170. The seals 285 and the receiving areas 290 are aligned along the axis 90. Accordingly, the seals 285 are axial seals 285 and seal between the damper blocks 170, thereby reducing the bypassing of the hot, energetic gas 30 around the turbine blades. The axial seals 285 are made of a suitable material to withstand the temperatures of the hot, energetic gas 30 and may be known as "dog-bone seals" (having a bone-shaped cross-section).The bypassing of the hot, energetic gas 30 around the blades is further reduced by arranging the shroud elements 85 such that the gaps 295 between adjacent shroud elements 85 are circumferentially offset from the gaps 300 between adjacent damper blocks 170. Arranging the shroud elements 85 such that the gaps 295 are circumferentially offset from the gaps 300 results in a tortuous flow path 305, which reduces the flow of the hot, energetic gas 30 around the blades.

[0030] Fig. 7 is an enlarged view of a portion of the front flange 310 of the shell member 85 and the pin 105, such as a front flange connecting pin 105. The pin 105 is inserted into an opening 315 of the front flange 310 of the shell member 85. The pin 105 holds the shell member 85 in place within the support block 80 and opposes the radially inward force of the spring 220 exerted via the damper block 170. The pin 105 fits into a pin opening 320 in the block 80 that has a recess 325 for a head 330 of the pin 105. The pin opening 320 extends across a gap 335 in the outer shell block 80 to receive the front flange 310.

[0031] Fig. Figure 8 shows an end view of the pin 105 of Fig. 7, which is inserted into the block 80. The head 330 of the pin 105 and the recess 325 of the block 80 have a complementary geometry, such as extended sides 340, which can be engaged with the block 80 to prevent rotation of the pin 105 following insertion into the block 80. A contact region 345 between the head 330 of the pin 105 and the recess 325 of the block 80 holds the pin 105 in the block 80. Embodiments of the contact region 345 are contemplated that include deformation regions 345, such as by methods such as punching and wobble riveting. Further embodiments of the contact region 345 are contemplated that include material transformation of the head 330 by methods such as welding, brazing, or soldering.The use of the contact area 345 eliminates the need for threads on the pin 105 or in the opening 320 of the block 80, thereby simplifying the manufacture of the pin 105 and the block 180, reducing the cost thereof, and also reducing the likelihood of abrasion during removal of the pin 105 following operation of the machine 20.

[0032] Again with reference to Fig. 3: A rear flange 350 and a pin 110, such as a rear flange connecting pin 110, are shown. Because the pin 110 is in direct contact with the shell member 85, the use of a contact area, such as contact area 345, to retain the front flange connecting pin 105 is not suitable because the ceramic material from which the shell member 85 is made is not suitable for such retention methods at the contact point.

[0033] The pin 110 is inserted through an opening 355 in the rear flange 350 of the shell member 85. The pin 110 holds the shell member 85 in place within the support block 80 and opposes the radially inward force of the spring 220 exerted via the damper block 170. The pin 110 fits into a pin opening 360 in the block 80. The pin opening 360 further includes a retaining bore 365 in which a retaining pin 370 is disposed. The pin 110 has a retaining opening 375 through which an end 380 of the retaining pin 370 is disposed, thereby retaining the pin 110 and preventing both rotation and translation of the pin 110. Following the arrangement of the retaining pin 370 in the retaining opening 375, a contact area 385 holds the retaining pin 370 in place in the retaining bore 365.Embodiments of the contact portion 385 are contemplated that include deformation of the retaining pin 370, such as by center punching and wobble riveting, and material conversion of the retaining pin 370, such as by welding, brazing, or soldering. The use of the retaining pin 370 in conjunction with the contact portion 385 eliminates the need for threads on the pin 110 or in the pin opening 360 of the block 80, thereby simplifying and reducing the cost of manufacturing the pin 110 and the block 80, as well as reducing the likelihood of abrasion upon removal of the pin 110.

[0034] While an embodiment having flat surfaces 175, 180 between the damper block 170 and the shroud member 85 has been described, it will be appreciated that the scope of the invention is not so limited, but that the invention is also applicable to embodiments of the shroud assembly 75 that utilize corresponding surfaces 175, 180 having a different geometry to effect sealing and transmission of the radial component of the force of the spring 220, such as a curved or oval geometry, meshing teeth, or other suitable geometry.

[0035] While an embodiment having flat surfaces to provide a "side-by-side" arrangement and prevent rotation of the damper block 170 within the outer shroud block 80 has been described, it is recognized that the scope of the invention is not so limited, but that the invention is also applicable to embodiments of the shroud assembly 75 that utilize corresponding surfaces 190-205 with a different geometry to provide a sealing "side-by-side" arrangement and prevent rotation, such as a curved, oval, elliptical, triangular, or other suitable geometry. While an embodiment having a spring 220 as the biasing element 220 has been described, it is recognized that the scope of the invention is not so limited, but that the invention is also applicable to embodiments of the shroud assembly that utilize other biasing elements 220, such asuse an assembly with resilient properties of the damper block 170 and / or the outer shell block 80.

[0036] As mentioned, some embodiments of the invention may provide some of the following advantages: Increased machine efficiency through: improved sealing between the damper block and the outer shroud block, improved sealing between adjacent damper blocks; improved sealing through shroud member gaps circumferentially offset from the damper block gaps; improved sealing between the close tolerance upper guide contact area and the outer shroud block; increased surface-to-surface contact between the damper block and the shroud member; reduced blade-to-shroud clearance via abradable shroud materials; reduced manufacturing costs and ease of maintenance through threadless shroud retaining pins; and increased operational flexibility through replaceable cooling passage vent plugs.

[0037] A support device for a shroud 85 of a gas turbine 35 is described. The device includes an outer shroud block 80 with a coupling that can be connected to a casing of the gas turbine 35 and a shroud element 85 with a front flange 310 and a rear flange 350. The shroud element is attached to the outer shroud block 80 via the front flange 310 and the rear flange 350. The device further includes a damper arranged between the outer shroud block 80 and the shroud element and a biasing element 220 arranged in the outer shroud block 80. A translational degree of freedom between the damper and the outer shroud block 80 defines a direction of movement 265 of the damper.The preload element 220 is operatively connected to the outer shell block 80 and the shell element 85 via the damper, with a preload force of the preload element 220 being directed along the direction of movement 265 of the damper.

[0038] While the invention has been described with reference to exemplary embodiments, it will be recognized that various changes may be made and equivalents may be substituted for the elements of the examples without departing from the scope of the invention. Furthermore, numerous modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best or only mode contemplated for carrying out the invention, but that the invention will include all embodiments falling within the scope of the appended claims.Also disclosed in the drawings and description are exemplary embodiments of the invention, and although specific terms may have been used, unless otherwise indicated, these are used in a generic and descriptive sense only and not for purposes of limitation, and the scope of the invention is therefore not so limited. Moreover, the use of the terms first, second, etc. does not indicate order or importance; rather, the terms first, second, etc. are used only to distinguish one element from another. Furthermore, the use of the terms a, an, etc. does not imply a limitation on the quantity, but rather indicates the presence of at least one of the designated elements. List of reference symbols: 20 gas turbine plants 25 Combustion chamber 30 gas 35 turbines 40 wave 45 compressors 50 Energy 55 Oxidant flow 60 Compressed oxidizer flow 65 Fuel flow 70 Fuel supply system 75 Sheath arrangement 80 jacket block 85 Sheath element 90 axis 95 Front end 100 Rear End 103 Counterclockwise rotation 105 pen 110 pen 115 Inner surface 120 Raised Patterns 125 housing 130 Inner Wall 135 T-hooks 140 groove 145 cavity 150 damper system 155 Damper block / shell element transition area 160 Damper force transmission device 165 Damping device 170 damper block 175 Inward-facing surface 180 Outward-facing surface 183 Scope 185 Senior Leadership 190 guide surface 195 guide surface 200 guide surface 205 guide surface 207 page 208 pages 210 disc cups 215 Heat-insulating pane 220 preload element 222 First section of the mantle block 225 cup-shaped block 230 cooling channel 235 Inner cavity 240 openings 250 ventilation plugs 255 countersunk hole 260 surface 265 Direction of movement 270 Axial component 275 Radial component 278 Second Section 280 sealing surface 283 Rear end 285 Seal 290 Seal receiving area 295 gap 300 gap 305 Winding Flow Path 310 Front flange 315 Opening 320 opening 325 recess 330 head 335 gap 340 Extended Page 345 Contact area 350 Rear flange 355 Opening 360 pen opening 365 retaining hole 370 retaining pin 375 Holding opening 380 End 385 Contact area

Claims

[1] Support device for a shroud element (85) of a gas turbine (20), the gas turbine (20) having a rotating shaft (40) defining a radial direction perpendicular to it, the device comprising: an outer shell block (80) having a coupling connectable to a housing of the turbine (35); a shell member (85) having a front flange (310) and a rear flange (350), the shell member (85) being attached to the outer shell block (80) via the front flange (310) and the rear flange (350); a damper arranged between the outer shroud block (80) and the shroud element (85) with a translational degree of freedom between the damper and the outer shroud block (80), the degree of freedom defining a direction of movement (265) of the damper, the direction of movement (265) forming an angle greater than 0° to the radial direction of the turbine (35); a biasing element (220) arranged in the outer shell block (80), wherein the biasing element (220) is in operative connection between the outer shell block (80) and the shell element (85) via the damper, wherein a biasing force of the biasing element (220) is directed along the direction of movement (265) of the damper, and a first pin (105) extending through an opening (315) of the front flange (310) or the rear flange (350), characterized by a deformation region (345) between a head (330) of the first pin (105) and the outer shell block (80). [2] A sheath support device according to claim 1, wherein: the outer shell block (80) has a first portion proximate the biasing member (220) and a second portion (278) proximate the shell member (85); and a component of the biasing force of the biasing element (220) biases a rear end (100, 283) of the damper toward the second portion (278) of the outer shell block (80). [3] A sheath support device according to claim 1, wherein: the damper has a guide surface (190); the outer casing block (80) has a guide surface (200, 205); and the guide surface (200, 205) of the outer casing block (80) fits to the guide surface (190) of the damper, thereby determining the translational degree of freedom of the damper relative to the outer casing block (80). [4] A sheath support device according to claim 1, wherein: the outer shell block (80) has a cooling channel (230) in fluid communication with the biasing element (220), and the device further comprises a vent plug (250) disposed in the coolant channel (230), the vent plug (250) having a surface (260) having an opening through the vent plug (250). [5] A sheath support device according to claim 1, wherein: the shell element (85) is a stationary ceramic shell element (85) for a turbine blade row of the turbine (35); and the stationary ceramic shroud member (85) has a surface proximate the turbine blade row, the surface having a raised pattern (120). [6] A sheath support device according to claim 5, wherein: the stationary ceramic shell element (85) is one of a number of stationary ceramic shell elements (85); and the damper is one of a number of dampers, each damper of the number of dampers being in contact with an associated shell element (85) of the number of stationary ceramic shell elements (85); and each damper of the plurality of dampers has a seal retaining portion (290); and the device further comprises a seal disposed in each of two adjacent seal support areas (290) of two adjacent dampers of the plurality of dampers. [7] A sheath support device according to claim 1, further comprising: the first pin (105) extendable through an opening (315, 320, 355) in the front flange (310) of the ceramic jacket element (85), the deformation region (345) between the head (330) of the first pin (105) and the outer shell block (80); the second pin (110) extendable through an opening (315, 320, 355) in the rear flange (350), the second pin (110) having a support opening (315, 320, 355, 375); and a support pin (370) disposed in the support opening (315, 320, 355, 375) of the second pin (110). [8] A sheath support device according to claim 1, wherein: the damper has a first surface; the ceramic shell element (85) has a second surface parallel to and adjacent to the first surface; and the first surface touches the second surface. [9] A sheath support device according to claim 8, wherein: the first surface comprises a periphery (183) of the damper; and substantially the entire area of ​​the first surface formed by the periphery (183) of the damper contacts the second surface. [10] A shroud support device according to any one of the preceding claims, wherein the shroud member (85) is an inner shroud member made of a melt-infiltrated ceramic matrix composite material.

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