EP1163430A1 - Covering element and arrangement with a covering element and a support structure - Google Patents
Covering element and arrangement with a covering element and a support structureInfo
- Publication number
- EP1163430A1 EP1163430A1 EP00916951A EP00916951A EP1163430A1 EP 1163430 A1 EP1163430 A1 EP 1163430A1 EP 00916951 A EP00916951 A EP 00916951A EP 00916951 A EP00916951 A EP 00916951A EP 1163430 A1 EP1163430 A1 EP 1163430A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cover element
- along
- wall
- cooling
- support
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
Definitions
- the invention relates to a cover element for protecting components in a thermally highly stressed machine, in particular components in a gas turbine.
- the invention further relates to an arrangement with a cover element and with a support structure.
- a thermally highly stressed machine is exposed to high temperatures during regular operation of this machine.
- a hot medium e.g. on
- Hot gas primarily the surfaces delimiting the hot medium and the associated components are subjected to very high thermal loads.
- components which are not directly exposed to the hot medium and are often installed in the housing of the machine are also subject to high thermal loads.
- the components exposed to the hot medium thus fulfill two functions: the inclusion of the hot medium and the protection of other, possibly less heat-resistant components from overheating or thermal destruction.
- requirements regarding the coolability of such components often have to be taken into account.
- US Pat. No. 3,892,497 describes an axial gas turbine with an inner and an outer housing insert.
- guide vanes and rotor blades are arranged along a turbine axis.
- Each guide vane has a platform (guide vane foot), which is used to fasten the guide vane to the inner housing insert.
- a guide ring is arranged on the inner housing insert in such a way that the guide ring adjoins the corresponding platforms of the guide vanes.
- Platforms and guides are held from the inside by the inner housing insert and connected to it via support elements.
- Each support element is firmly connected to the inner housing insert by a combination of locking plate with a screw engaging in the inner housing insert.
- the platforms of the guide vanes and the Fuhrungs ⁇ nge have grooves in which the support element engages.
- a support element engages either in a groove in a platform or in a guide ring, the engagement in the axial direction being produced in each case on the edge of the platform or guide ring.
- this fastening allows a relative thermal expansion and contraction between adjoining components in the axial direction and also enables simplified assembly and maintenance of the gas turbine.
- a fastening for a guide ring also emerges from the patent which is directly connected to the guide ring by means of a locking screw guided radially through the inner housing insert. The locking screw fixes the guide ring locally at a point between its axial edges. This configuration leads to considerable local heat stresses in the axial and especially in the radial direction when the guide is thermally stressed, since thermal expansion is only possible to a very limited extent.
- the invention has for its object to provide a thermally highly resilient and at the same time as efficiently coolable component.
- the component should be suitable for use at high working temperatures and large temperature differences between different load conditions.
- a further object of the invention is to provide an arrangement with a component and with a support structure which, in particular, enables the component to be fastened in the support structure in a manner which is tolerant of thermal expansion.
- the first-mentioned object is achieved by a cover element which has a longitudinal axis and a transverse axis, comprising a wall with a hot side which can be exposed to a hot medium and a cooling side opposite the hot side which has a cooling surface to which a cooling agent can be applied, and further comprising one along the longitudinal axis adjoining the wall with a first contact area and a second contact area along the longitudinal axis opposite the first contact area with a second contact area, and further comprising a first edge area along the transverse axis and one along the Transverse axis of the second edge area opposite the first edge area, wherein a holding element is provided on the cooling side, which is arranged between the first and the second support area.
- the invention is based on the consideration that a component in a thermal machine which is exposed to a hot medium, for example a hot gas or steam, is thermally very heavily stressed by the temperature of the medium. These high temperatures or large temperature changes are associated with heat-related deformations, especially thermal expansions, which must be taken into account when designing and assembling such components.
- the invention creates a new possibility of designing and arranging components that are tolerant of thermal expansion in machines that are subjected to high thermal loads.
- an above cover element With its hot side that can be exposed to the hot medium, an above cover element forms a defined boundary of the hot medium, for example the hot gas in the combustion chamber or in the flow channel of a gas turbine. Furthermore, the cover element serves as a thermally highly resilient component to protect further, possibly less heat-resistant components that are not directly exposed to the hot medium and are arranged in the housing of the thermal machine, in particular the gas turbine. In this function, the cover element prevents thermal overloading or even destruction of these components.
- a holding element On the cooling side of the cover element, a holding element is provided, which is arranged between the first and the second contact area.
- the mounting element is an integral part of the cover element and has the task of providing additional support between the first and the second support area.
- the cover element is in this case held by the cooling element from the cooling side in such a way that, in particular, forces which are normal to the wall, for example as a result of mechanical and / or thermal loading of the wall, can be efficiently absorbed and, if appropriate, also transmitted. At the same time, very good cow properties of the cover element can be guaranteed.
- This is realized in that the first and the second support area adjoin the wall along the longitudinal axis.
- the side of the hot medium is opposite Wall almost completely available as a cooling surface.
- the cooling surface can be applied uniformly with a cooling agent, for example cooling air, which enables very homogeneous cooling.
- the good cooling properties of the aode cover element also have a particularly favorable effect on the temperature distribution within the wall of the cover element. As a result, temperature gradients essentially only occur normally to the cooling surface, ie from the hot side in the direction of the cooling side. As a result, thermal stresses along the longitudinal or transverse axis of the cover element, which could possibly induce cracks, are largely avoided.
- the proposed cover element also proves to be very advantageous in terms of mechanical stability. This primarily concerns the forces that occur due to possible pressure differences that may exist between the hot side and the cooling side of the cover element. Both the mechanical load and the thermal load of the cover element described above lead to a deformation of the wall, which normally manifests itself as a deflection of the wall in the direction of the hot side. This effect is limited to a defined level by the invention.
- Another mounting element is preferably arranged on the cooling surface, on the first or on the second edge region.
- Another mounting element makes it possible to give the cover element additional support from the cooling side of the wall at a further point.
- the total load due to mechanically and / or thermally induced forces normal to the wall is distributed through to several mounting elements, which means that the load per mounting element is correspondingly lower. Possible deflections of the wall in the direction of the hot side as a result of these forces are either further restricted as a result or can be limited to a predetermined dimension by appropriate arrangement of the holding elements.
- the good cooling properties of the cover element are retained by the additional holding element, ie above all the formation of a coherent cooling surface on the cooling side.
- Different combinations of two mounting elements can be realized, which lead to the same desired result with regard to a predetermined maximum deformation of the wall. This gives you a certain amount of freedom with regard to the arrangement of the mounting elements.
- the mounting element preferably has a mounting surface. Furthermore, the holding element preferably has a recess, in particular a groove, for engaging in a support structure.
- This configuration makes it possible to achieve a thermal expansion-tolerant arrangement with the cover element and with a support structure via the support element, in combination with the first and second support areas and with a support structure.
- the manufacture of the mounting support surface as a partial surface of the recess, in particular of the groove, in the mounting element can be carried out easily in terms of production technology.
- the recess could be produced, for example, by milling a groove or, in the case of a cast part, by undercutting using a simple core during casting.
- the bracket support surface serves to absorb the forces due to thermal and / or mechanical loading of the cover element and to transmit it effectively to a support structure. Due to the mounting surface, the sometimes considerable forces are not transmitted selectively, but rather distributed over an area. For a given thermal or mechanical load, the load per area can be reduced by dimensioning the holding rungsauflagefach be limited to a dimension adapted to the material properties of the cover.
- the wall preferably has a wall thickness between approximately 1.0 mm to 5.0 mm, in particular between approximately 1.5 mm to
- the wall is consequently comparatively thin compared to the first and the second support area or the first or second edge area of the cover element.
- the temperature difference between the hot side with the hot medium and the cooling side of the wall with the coolant can be very large during operation.
- temperature differences of up to 800 ° C. between the hot gas and the coolant, in particular cooling air removed from the compressor of the gas turbine can occur. It is therefore of decisive advantage to make the wall as thin as possible so that the temperature gradient between the hot side and the cooling side of the wall is as large as possible and the heat can be dissipated very efficiently with the lowest possible amount of cooling agent.
- Efficient heat dissipation takes place primarily through the coolant.
- a small part of the heat flow, which flows into the wall from the hot side, can also be diverted along the longitudinal axis and the transverse axis m to the first / second contact area and the first / second edge area of the cover element, since these areas, because of their opposite to the Wall of larger cross section, represent an additional heat sink.
- the cooling surface preferably has a support structure for increasing rigidity and thermal conductivity.
- the increase in the rigidity of the cover element due to the support structure on the cooling surface has a very advantageous effect on preventing deformations, in particular deformations and deflections of the wall in the direction of the hot side of the wall.
- this support structure increases the effective cooling surface, which leads to an increase in cooling efficiency.
- the support structure ensures an improved mixing of cooling agents with different temperatures in the immediate vicinity of the cooling surface. As a result, the temperature on the cooling surface decreases on average, and the temperature gradient and, accordingly, the heat transport through the cooling medium is increased.
- the thermal conductivity is increased somewhat due to the enlarged cross section of the support structure along the support structure.
- the support structure is preferably designed by at least one longitudinal step along the longitudinal axis on the cooling surface. Furthermore, the support structure preferably has a further longitudinal step, which is carried out along the longitudinal axis on the cooling surface.
- the execution of the support structure in the form of one or more Langs ⁇ ppen is a ne technically very inexpensive solution that can be implemented easily and inexpensively, for example, in a casting. With regard to the improved heat conduction properties, this configuration leads to heat dissipation through the
- the longitudinal ribs increase the rigidity of the component, which in turn is advantageous in relation to possible deformations, in particular bending of the wall from the cooling side to the hot side, under thermal or mechanical stress.
- At least two longitudinal steps spaced apart in the direction of the transverse axis are preferably connected to a holding element. Due to this design, the mounting element can be understood as part of the support structure. This design serves to increase the rigidity and increase the thermal conductivity, but above all the mechanical and thermal stability of the cover element at high temperature and / or pressure loads. Another advantage is the simple implementation of this embodiment in terms of production technology.
- the number and arrangement of the holding elements are preferably determined by a predetermined thermal deflection of the wall.
- the predefined thermal deflection is more preferably 0.1 mm to 1.0 mm, in particular 0.3 mm to 0.7 mm.
- the resulting thermal deflection depends on the temperature load and / or pressure load on the cover element and on its material properties as well as the structural design, primarily with regard to the number and arrangement of the mounting elements.
- a typical temperature difference between the hot side and the cooling side of the cover element of approx. 800 ° C., as occurs, for example, in a stationary gas turbine, the limits given above for thermal deflection are found to be useful values.
- a suitable configuration will be found by computer-aided optimization of the competing requirements between the bending of the wall on the one hand, and therefore the number and arrangement of the mounting elements on the cooling surface, and an acceptable limitation of the effective cooling surface by the mounting elements on the other hand .
- the proposed concept therefore offers great flexibility in terms of adapting to a specific task.
- At least two mounting elements are preferably arranged spaced apart from one another along the transverse axis. More preferably, at least two mounting elements are arranged spaced apart from one another along the longitudinal axis.
- cover elements which are dimensioned such that they extend predominantly along the longitudinal axis or along the transverse axis, a plurality of holding elements are provided along the respective preferred axis. This design is well adapted to the symmetry properties of the cover element and, with a given thermal deflection of the wall, requires as few number of mounting elements as possible.
- support elements are preferably arranged in both dimensions in order to achieve the desired effect.
- the advantage here is that the mounting elements are spaced from each other and thus the cooling surface always remains a coherent surface in all embodiments. This allows the cooling air to flow freely from one location on the cooling surface to another location on the cooling surface, and additional coolant supplies or coolant feedthroughs are not required.
- the object based on an arrangement is achieved according to the invention by an arrangement with a cover element according to one of the above embodiments and with a support structure which has a longitudinal axis, a transverse axis and a first receiving region arranged along the longitudinal axis with a first
- the holder support surface and the support surface are spaced apart from one another by a gap without thermal stress, in particular at room temperature.
- the cover element is usually inserted into the support structure at room temperature. Due to the fact that the first receiving area adjoins the first contact area and the second receiving area adjoins the second contact area, the cover element is already held in the supporting structure.
- the spacing of the mounting support surface of the mounting element and the supporting surface of the supporting element by a gap proves to be very favorable with regard to the mounting of the cover element in the supporting structure.
- the mounting surface and the wing will come to cover and the forces due to the thermal load are effectively absorbed.
- the distance between the bracket support surface and the wing surface chosen at room temperature determines the thermal load at which the bracket support surface and the wing surface come to congruence and thus the resulting thermal deflection of the wall.
- the cover element is held firmly in the supporting structure in this way, the thermal deflection of the wall in the direction of the hot side being specifiable, in particular limited to a maximum value.
- a configuration formed between a receiving area and the adjoining support area is preferably designed as a fixed bearing and the other configuration as a floating bearing.
- This embodiment proves to be particularly advantageous since the arrangement with a cover element and with a support structure generally represents a mechanically highly determined system.
- This system has a number of bearing configurations, which are formed by the receiving and the adjacent support areas and also by the overlapping support elements and support elements.
- the design with a fixed bearing and a floating bearing ensures easy mounting of the cover element in the support structure in the thermally unloaded state.
- thermal expansion of the cover element along the longitudinal axis is made possible. The thermal expansion takes place when the temperature rises from the fixed bearing towards the floating bearing.
- the fixed bearing configuration is designed in such a way that the corresponding receiving area and the adjacent bearing area come into contact with one another even when the temperature rises slightly compared to room temperature.
- the floating bearing on the other hand, is dimensioned in such a way that even at very high temperatures, such as occur in the operation of a gas turbine. ten, the cover element can still expand along the longitudinal axis. In particular, this results in the advantages of simple assembly and the thermal expansion-tolerant arrangement of the cover element in a support structure. Thermally induced deformations, in particular thermal expansions, are taken into account, and at the same time the cover element is held firmly in the support structure via the mounting elements at high temperatures.
- the fixed bearing preferably has a tolerance of between approximately
- the floating bearing has a tolerance between approximately .0 mm to 10.0 mm.
- the cover element and the support structure are preferably arranged in a thermal machine, in particular in a gas turbine.
- the thermal expansion-tolerant fastening concept is particularly suitable for a platform for fixing a gas turbine blade, for a guide ring in a gas turbine, for a head platform for a guide blade for a gas turbine or for a heat shield element in the combustion chamber of a gas turbine.
- a distinction is made between guide vanes and rotor blades, which are each arranged on rings radially to the axis of rotation of the gas turbine.
- a guide vane has a platform which is arranged to fix the guide vane to the inner turbine housing, in particular to the guide vane segment.
- a rotor is attached to the turbmenlaufer arranged along the axis of rotation via a platform.
- a guide ring is arranged as a wall element in a gas turbine between the platforms of two axially spaced successive guide vanes.
- the outer surface of the guide is exposed to the hot medium, in particular the hot gas, and is spaced in the radial direction from the outer ends of the rotating blades by a gap.
- cover element is possible, for example as a wall element in an oven, in combustion chambers or in containers that can be filled with hot media.
- FIG. 1 shows a half section through a gas turbine with a compressor, combustion chamber and turome
- FIG. 3 shows a perspective illustration of a guide ring of a gas turbine
- FIG. 4 shows a plan view of a guide ring of a gas turbine with a cooling surface and mounting elements
- FIG. 5 shows a view of the guide shown in FIG. 4 along the section line VI-VI
- FIG. 6 shows a further exemplary embodiment (top view) of a guide of a gas turbine with a cooling surface and mounting elements
- FIG. 7 shows a view of the guide ring shown in FIG. 6 along the section line VII-VII
- FIG 8 shows a longitudinal section of an arrangement of a guide element in the guide vane segment of a gas turbine without thermal stress (at room temperature),
- FIG. 9 shows a longitudinal section of an arrangement of a guide ring in the guide vane segment of a gas turbine during thermal loading.
- the same reference numerals have the same meaning in the individual figures.
- the gas turbine 1 shows a half section through a gas turbine 1.
- the gas turbine 1 has a compressor 3 for combustion air, a combustion chamber 5 with burners 7 for a liquid or gaseous fuel with heat shield elements arranged on the wall inside the combustion chamber 5, not shown in FIG. 1, and a turbine 9 for driving the compressor 3 and 1 m not shown
- stationary guide vanes 11 and rotatable rotor blades 13 are arranged on respective radially extending rings, not shown in half section, along the axis of rotation 21 of the gas turbine 1.
- a consecutive pair along the axis of rotation 21 of a ring of guide vanes 11 (guide blade ring) and a ring of rotor blades 13 (rotor blade ring) is referred to as a turbine stage.
- Each guide vane 11 has a platform 17, which is arranged as a wall element for fixing the guide vane 11 in question to the inner turbine housing 29.
- this platform 17 is a thermally highly stressed component, which forms the outer boundary of a hot medium M, in particular the hot gas duct m of the turbine 9.
- the rotor blade 13 is fastened on the turbine rotor 19 arranged along the axis of rotation 21 of the gas turbine 1 via a corresponding platform 17.
- a guide ring 15 is arranged on the wall as a cover element m of a gas turbine 1 between the platforms 17 of two axially spaced adjacent guide vanes 11.
- the outer surface 31 of the guide ring 15 is exposed to the hot medium M, in particular the hot gas, and is spaced in the radial direction from the outer end 27 of the rotor blade 13 by a gap.
- the guide rings 15 arranged between adjacent guide vane rings serve as cover elements which protect against thermal overloading of housing components by the heat transfer from the flowing hot medium M. In the operation of the gas turbine 1 fresh air L is sucked in from the environment.
- the air L is compressed in the compressor 3 and thereby preheated at the same time.
- the air L is brought together with the liquid or gaseous fuel and burned.
- a portion of the air L previously removed from the compressor 3 serves as cooling air K for cooling the turbine stages, the first turbine stage, for example, being subjected to a turbine inlet temperature of approximately 750 ° C. to 1200 ° C.
- the hot medium M is relaxed and cooled, in particular the hot gas which flows through the turbine stages.
- FIG. 2 shows, in somewhat more detail, a longitudinal section through a section of the turbine 9 shown in FIG. 1.
- Guide vanes 11 and rotor blades 3 are arranged in succession along the axis of rotation 21 of the turbine 9.
- the guide blades 11 each have a platform 17 which is arranged as a wall element for fixing the guide blade 11 to the inner turbine housing 29, which is only incompletely shown in FIG. 2.
- the inner turbine housing 29 has a radially arranged guide vane segment 25, in which a support structure 34 is formed in the direction of the axis of rotation 21.
- the support structure 29 receives the platforms 17 of the guide vanes 11 and in this way fixes the guide vanes 11.
- the rotor blades 13 are each secured to the turbine rotor 19 arranged along the axis of rotation 21 via a platform 17.
- Fuhrungs ⁇ nge 15 are arranged as cover elements 2 in the turbine 9 between the platforms 17 of two axially spaced successive Leitschau- 11.
- the outer surface 31 of a cover element 2, in particular a guide ring 15, is exposed to the hot medium M, in particular the hot gas, and is spaced in the radial direction from the outer ends 27 of the rotor blades 13 by a gap 23.
- the outer surface 31 forms the hot side 10 of the cover element 2.
- the support structure 34 of the guide vane segment 25 shown in FIG. 2 is designed such that it supports the guide vanes 11 for several Takes turbine stages.
- the guide vane segment 25 with cover elements 2 each of which represents a guide ring 15, which is arranged in the support structure 34, before thermal overloading due to the heat transfer from the flowing hot medium M , especially the hot gas, effectively protected.
- the guide rings 15 are inserted in the supporting structure 34 such that the first receiving area 40 of the supporting structure 34 adjoins the first contact area 18 of the cover element 2 and the second receiving area 44 of the supporting structure 34 adjoins the second contact area 16 of the cover element 2 and the mounting element 28 of the cover element 2 and the support element 48 of the support structure 34 overlap.
- FIG. 3 A perspective view of a guide ring 15 of a gas turbine 1 is shown in FIG. 3.
- the guide ring 15 extends along a longitudinal axis 4 and a transverse axis 6. It comprises a wall 8 with a hot side 10 which can be exposed to a hot medium and a cooling side 12 opposite the hot side 10 which has a cooling surface 14 which can be acted upon with a cooling agent K.
- a first bearing area 16 with a first bearing surface 20 borders on the wall 8 of the guide ring 15 along the longitudinal axis 4.
- a second contact area 18 with a second contact area 22 adjoins the wall 8 along the longitudinal axis 4 and lies opposite the first contact area 16.
- the guide ring 15 also has a first edge region 24 adjoining the wall 8 along the transverse axis 6 and one along the Transverse axis 6 on the second edge region 26 opposite the first edge region 24. In comparison to the first / second edge area 24, 26 and the first / second support area 16, 18, the wall 8 is made thin.
- support elements 28 are provided, which are arranged between the first and the second support area 20, 22.
- five mounting elements 28 are arranged along the transverse axis 6 on the cooling side 12 of the wall 8.
- the first and second edge areas 24, 26 each have a holding element 28, while three holding elements 28 are arranged on the cooling surface 14 of the wall 8.
- the mounting elements 28 are an integral part of the guide ring 15 and have the function between the first and the second support area 16, 18 to provide additional support.
- the guide ring 15 can be held by the holding elements 28 from the cooling side in such a way that, in particular, forces directed normal to the wall, for example as a result of mechanical and / or thermal stress on the wall 8, can be efficiently absorbed and, if appropriate, also transmitted.
- the mounting elements 28 each have a recess 32, in particular a groove, with a mounting contact surface 30.
- the respective recess 32 m of the holding elements 28 is provided for engagement in a support structure 34, not shown in FIG. 3 (see FIGS. 8 and 9).
- the mounting elements 28, in combination with the first and the second support areas 16, 18 and with a support structure 34 (not shown in FIG. 3), achieve a thermally expansion-tolerant connection between the guide ring 15 and the support structure 34. Because the first and the second support areas 16, 18 adjoin the wall 8 along the longitudinal axis 4, the side of the wall 8 opposite the hot medium M is virtually completely available as a cooling surface 14.
- the cooling surface 14 can be acted upon uniformly with a cooling agent K, for example cooling air, which enables very homogeneous cooling becomes.
- the holding elements 28 are arranged at a distance from one another along the transverse axis 6, as a result of which the cooling surface 14 is designed as a coherent surface and, as a result, the cooling agent K, provided it is supplied at one point to the cooling side 12, can reach all areas of the cooling surface 14 .
- An unhindered and uniform distribution of the coolant K along the cooling surface 14 is thereby ensured and thus also a particularly efficient heat dissipation covering the entire surface.
- the cooling surface 14 has a support structure 36. This serves to increase the rigidity and thermal conductivity of the guide ring 15.
- This support structure is implemented by a series of aquid-resistant longitudinal steps 38, which uniformly cover the cooling surface 14 along the transverse axis 6. Both longitudinal ribs 38 are provided, which extend from the first contact area 16 to the second contact area 18 of the guide ring 15, and also longitudinal ribs 38, which extend from the first contact area 16 along the longitudinal axis 4 and between the first contact area 16 and the second The contact area 18 of the guide ring 15 ends on the cooling surface 14.
- the support structure 36 prevents deformations, in particular deformations and deflections of the wall 8 in the direction of the hot side 10 of the wall 8. Furthermore, this support structure 36 increases the effective cooling surface 14, which leads to an increase in the cooling efficiency.
- the support structure 36 additionally brings about an improved mixing of cooling agent K with different temperatures in the immediate vicinity of the cooling surface 14.
- the temperature on the cooling surface 14 is reduced on average, and the temperature gradient and, accordingly, the heat transport the coolant K is increased.
- the thermal conductivity is increased somewhat due to the enlarged cross section of the support structure 36 along the support structure.
- the holding elements 28 arranged on the cooling surface 14 are connected to at least three longitudinal ribs 38 spaced apart in the direction of the transverse axis 6. As a result of this design, the holding elements 28 on the cooling surface 14 can be understood as part of the support structure 36.
- This embodiment serves both to increase the rigidity and to increase the thermal conductivity, but above all the mechanical and thermal stability of the guide ring 15 under high temperature and / or pressure loads, in particular under temperature change loads. Simple manufacturing forms of the guide ring 15 with these favorable properties, for example as a cast part, are possible.
- FIG. 4 shows a guide ring 15 of a gas turbine 1 with an arrangement of the holding elements 28 and configuration of the longitudinal ribs 38 on the cooling side 12 that is alternative to FIG. 3, and FIG. 5 shows a view of the guide ring 15 shown in FIG. 4 along the section line VI-VI.
- FIG. 4 shows a top view of the cooling side 12 of the guide ring 15, which has a cooling surface 14 that can be acted upon with a cooling agent.
- the cooling surface 14 is delimited along the longitudinal axis 4 by a first contact area 16 and a second contact area 18 opposite the first contact area 16 along the longitudinal axis.
- the cooling surface 14 is delimited along the transverse axis 6 by an adjacent first edge region 24 and a second edge region 26 lying along the transverse axis 6 and opposite the first edge region 24.
- the five mounting elements 28 are arranged exclusively on the cooling surface 14, ie the first and second edge areas 24, 26 of the guide ring 15 have no mounting elements 28 here.
- At least two longitudinal ribs 38 spaced apart in the direction of the transverse axis 6 are connected to a holding element 28. There are five mounting elements 28 on the cooling surface 14 spaced apart.
- the cooling surface 14 is thus designed as a coherent surface, and a cooling agent K, in particular cooling air L, can flow unhindered from one location on the cooling surface 14 to any other location on the cooling surface 14. This eliminates the need for complex coolant feeds or coolant feedthroughs and provides a particularly efficiently coolable guide ring 15.
- the sectional view shown in FIG. 5 of the guide ring 15 shown in FIG. 4 shows a wall 8 with a hot side 10 which can be exposed to a hot medium and a cooling side 12 opposite the hot side 10 which has a cooling surface 14 which can be acted upon by a cooling agent K.
- a first contact area 16 with a first contact surface 20 adjoins the wall 8 along the longitudinal axis 4.
- a second contact area 18 with a second contact surface 22 is adjacent to the wall 8 along the longitudinal axis 4 and lies opposite the first contact area 16.
- two mounting elements 28 are arranged at a distance from one another along the longitudinal axis 4, a coherent cooling surface 14 being formed.
- the support elements 28 each have a recess 32, in particular a groove, with a support contact surface 32 for engaging in a support structure 34 (not shown in FIG. 5) (see FIGS. 8 and 9).
- the wall 8 is designed with a wall thickness D1 which is comparatively thin compared to the wall thickness of the first and the second contact areas 16, 18.
- the wall thickness Dl is approximately 1.0 mm to 5.0 mm, in particular approximately 1.5 mm to 3.0 mm. This has an advantageous effect on the cooling properties of the guide ring 15.
- the temperature difference between the hot side 10 to which the hot medium M can be applied and the cooling side 12 of the wall 8 which can be subjected to the cooling agent K can be very large.
- Wall 8 becomes as large as possible and the heat can be dissipated very efficiently with the least possible use of coolant. Efficient heat dissipation takes place primarily through the cooling air K. A smaller part of the heat flow, which flows from the hot side 10 into the wall 8, is also along the longitudinal axis and the transverse axis m the first / second contact area and the first / second edge area derived from the cover element, since these areas form a heat sink because of their larger cross section than the wall 8.
- FIG. 6 shows a further exemplary embodiment of a guide ring 15 of a gas turbine 1 with a cooling surface 14 and mounting elements 28, and FIG. 7 shows a view of the guide ring 15 shown in FIG. 5 along the section line VII-VII.
- the guide ring 15 shown is dimensioned such that it extends predominantly along the longitudinal axis 4.
- the longitudinal axis 4 thus forms the preferred direction of expansion of the guide ring 15. Therefore, on the cooling surface 14, three mounting elements 28 are arranged at a distance from one another along the longitudinal axis 4, a coherent cooling surface 14 being formed.
- the first edge region 24 and the second edge region 26 each have a holding element 28.
- a support structure 36 m in the form of aquidistant long ribs 38 is carried out along the long axis 4.
- the longitudinal ribs 38 extend from the first contact area 16 to the second contact area 18 and cover the cooling surface 14 evenly along the transverse axis 6 of the guide ring 15.
- the mounting elements 28 are each provided with a recess 32 which has a mounting contact surface 30.
- the recesses 32 are designed here as grooves, which serve to engage in a support structure 34 not shown in FIG. 6 (see FIGS. 8 and 9).
- the sectional view VII-VII in FIG. 7 shows a wall 8 with a hot side 10 that can be exposed to a hot medium M and a cooling side 12 opposite the hot side 10, which has a cooling surface 14 that can be acted upon with a cooling agent.
- the first support area 16 adjoining the wall 8 along the longitudinal axis 4 has a first support surface 20.
- a second contact area 18 with a second contact area 22 is adjacent to the wall 8 along the longitudinal axis 4 and is opposite the first contact area 16.
- the wall 8 is made comparatively thin with respect to the first and second contact areas 16, 18.
- the wall 8 of the guide ring 15 has the tendency to bend in the direction of the hot side 10.
- the resulting deflection of the wall 8 depends on the temperature and pressure conditions to which the guide ring 15 is subjected and the material properties and the structural design of the guide ring 15, in particular with regard to the number and the arrangement of the holding elements 28 on the cooling surface 14.
- FIG. 8 shows a longitudinal section of an arrangement of a cover element 2, which represents a guide ring 15, in the guide vane segment 25 of a gas turbine 1 without thermal stress, ie at room temperature.
- the guide ring 15 comprises a wall 8 with a wall thickness D1 and with a hot side 10 which can be exposed to a hot medium M and a cooling side 12 opposite the hot side which has a cooling surface 14 which can be acted upon with a cooling agent K.
- a first support area 16 adjoins the wall 8 with a first support surface 20.
- a second contact area 18 with a second contact surface 22 is adjacent to the wall 8 along the longitudinal axis 4 and lies opposite the first contact area 16.
- a mounting element 28 is arranged on the cooling surface 14 and has a recess 32, in particular a groove, and a mounting contact surface 30.
- the mounting element 28 is designed and arranged on the cooling surface 14 in such a way that a coherent cooling surface 14 is formed.
- the guide vane segment 25 has a support structure 34, m the guide ring 15 is inserted.
- the support structure 34 extends along a longitudinal axis 4 and has a first receiving region 40 with a first receiving surface 42 and a second receiving region 44 opposite along the longitudinal axis with a second receiving surface 46 and a supporting element 48 with a supporting surface 50.
- the guide ring 15 is arranged in the support structure 34 in such a way that the first receiving area 40 adjoins the first contact area 16 and the second Adjacent the receiving area 44 to the second support area 18 and the support element 28 and the support element 48 overlap, the support support surface 30 and the support surface 50 being opposite one another.
- the mounting support surface 30 and the support surface 50 are spaced apart from one another by a gap 52.
- the configuration formed between the first receiving area 40 and the adjoining first contact area 16 is designed as a bearing 56.
- the configuration formed between the second receiving area 44 and the adjoining second contact area 18 is designed as a fixed bearing 54.
- the design with a fixed bearing 54 and a floating bearing 56 facilitates the assembly of the guide ring 15 in the support structure 34 in the thermally unloaded state. At the same time, thermal expansion of the guide ring 15 along the longitudinal axis 4 is made possible in the event of a load. In the event of a temperature rise, the thermal expansion takes place from the fixed bearing 54 in the direction of the floating bearing 56.
- the fixed bearing configuration is designed in such a way that the second receiving area 44 and the adjacent second contact area 18 come into contact with one another even when the temperature rises slightly compared to room temperature .
- the fixed bearing is designed with a tolerance between about 0.2 mm to 0.5 mm.
- the floating bearing 56 is dimensioned such that the guide ring 15 can expand along the longitudinal axis 4 even at high temperatures.
- the floating bearing has a tolerance between approximately 4 mm to 10 mm.
- the guide ring 15 is usually inserted into the support structure 34 at room temperature. Because the first receiving area 40 adjoins the first contact area 16 and the second receiving area 44 adjoins the second contact area 18, the guide ring 15 is already held in the support structure 34. The spacing of the mounting support surface 30 of the mounting element 28 and the support surface 50 of the mounting element 48 by a gap 52 facilitates the assembly of the guide ring 15 m and the support structure 34.
- the guide ring 15 is arranged as a cover element 2 in a gas turbine 1 between the platforms, not shown in FIG.
- FIG. 9 illustrates the behavior of the system discussed in FIG. 8 under thermal loading, that is to say in the operation of a stationary gas turbine 1.
- the wall 8 of the guide ring 15 has the tendency to bend in the direction of the hot side 10.
- the bracket support surface 30 and the support surface 50 come to coincide, and the forces due to the thermal and mechanical loads are absorbed effectively.
- the distance selected between the support surface 30 and the support surface 50 at room temperature (cf. FIG.
- the gap 23 formed between the hot side 10, which is exposed to the hot medium M, in particular the hot gas, and the outer end 27 of the rotor blade 13 has a gap dimension ⁇ x which is smaller than the gap dimension ⁇ o at room temperature (cf. FIG 8th). The difference between these gap dimensions ⁇ o, ⁇ i corresponds approximately to the thermal deflection D2 of the wall 8.
- the resulting thermal deflection D2 depends on the temperature and pressure load on the guide ring 15, and on the material properties and the design, in particular with regard to the number and the arrangement of the holding elements 28 on the cooling surface 14.
- the gap dimension ⁇ i can be set to a predetermined, as small as possible, dimensioning the arrangement shown.
- the gap losses in follow the mass flow of hot medium M, in particular hot gas, through the gap 23 can be minimized in this way, which has a positive effect on the turbine efficiency.
- grinding of the rotating rotor blade 13 against the guide ring 15 can be reliably prevented during operation.
- this is preferably the downstream formed bearing configuration as a fixed bearing 54 and the upstream bearing configuration designed as a floating bearing 56. This ensures free thermal expansion of the guide ring 15 along the longitudinal axis 4. The thermal expansion takes place when the temperature rises from the fixed bearing 54 in the direction of the floating bearing 56.
- the fixed bearing configuration in particular the fixed bearing 54, is carried out in such a way that the receiving area 44 and the adjacent contact area 18 n come into contact with one another even with a slight rise in temperature compared to the room temperature , so that in particular the receiving surface 40 and the support surface 22 lie directly opposite one another.
- the floating bearing 56 is designed in such a way that the guide 15 along the longitudinal axis 4 can expand sufficiently even at high temperature loads.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00916951A EP1163430B1 (en) | 1999-03-24 | 2000-03-15 | Covering element and arrangement with a covering element and a support structure |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99105944 | 1999-03-24 | ||
EP99105944 | 1999-03-24 | ||
PCT/EP2000/002296 WO2000057033A1 (en) | 1999-03-24 | 2000-03-15 | Covering element and arrangement with a covering element and a support structure |
EP00916951A EP1163430B1 (en) | 1999-03-24 | 2000-03-15 | Covering element and arrangement with a covering element and a support structure |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1163430A1 true EP1163430A1 (en) | 2001-12-19 |
EP1163430B1 EP1163430B1 (en) | 2003-08-20 |
Family
ID=8237850
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00916951A Expired - Lifetime EP1163430B1 (en) | 1999-03-24 | 2000-03-15 | Covering element and arrangement with a covering element and a support structure |
Country Status (6)
Country | Link |
---|---|
US (1) | US6602050B1 (en) |
EP (1) | EP1163430B1 (en) |
JP (1) | JP2002540337A (en) |
CA (1) | CA2366357A1 (en) |
DE (1) | DE50003360D1 (en) |
WO (1) | WO2000057033A1 (en) |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2819010B1 (en) | 2001-01-04 | 2004-05-28 | Snecma Moteurs | STATOR RING SUPPORT AREA OF THE TURBINE HIGH PRESSURE TURBINE ROTATOR WITH A TURBOMACHINE |
JP4698847B2 (en) * | 2001-01-19 | 2011-06-08 | 三菱重工業株式会社 | Gas turbine split ring |
EP1256695A1 (en) * | 2001-05-07 | 2002-11-13 | Siemens Aktiengesellschaft | Element for a gas turbine guiding ring and gas turbine comprising such element |
GB2391045A (en) * | 2002-07-19 | 2004-01-28 | Corac Group Plc | Rotary machine with means for separating impurites from a gas flow |
US7052235B2 (en) * | 2004-06-08 | 2006-05-30 | General Electric Company | Turbine engine shroud segment, hanger and assembly |
US20060078429A1 (en) * | 2004-10-08 | 2006-04-13 | Darkins Toby G Jr | Turbine engine shroud segment |
EP1717419B1 (en) | 2005-04-28 | 2010-10-13 | Siemens Aktiengesellschaft | Method and device for adjustement of a radial clearance of a compressor of an axial turbomachine |
US20070237629A1 (en) * | 2006-04-05 | 2007-10-11 | General Electric Company | Gas turbine compressor casing flowpath rings |
US7604456B2 (en) * | 2006-04-11 | 2009-10-20 | Siemens Energy, Inc. | Vane shroud through-flow platform cover |
DE102007031711A1 (en) * | 2007-07-06 | 2009-01-08 | Rolls-Royce Deutschland Ltd & Co Kg | Housing shroud segment suspension |
FR2933458B1 (en) * | 2008-07-01 | 2010-09-03 | Snecma | AXIALO-CENTRIFUGAL COMPRESSOR WITH STEERING SYSTEM |
US8376705B1 (en) | 2011-09-09 | 2013-02-19 | Siemens Energy, Inc. | Turbine endwall with grooved recess cavity |
US9574455B2 (en) * | 2012-07-16 | 2017-02-21 | United Technologies Corporation | Blade outer air seal with cooling features |
US20140064969A1 (en) * | 2012-08-29 | 2014-03-06 | Dmitriy A. Romanov | Blade outer air seal |
JP5889266B2 (en) * | 2013-11-14 | 2016-03-22 | 三菱重工業株式会社 | Turbine |
GB201410264D0 (en) * | 2014-06-10 | 2014-07-23 | Rolls Royce Plc | An assembly |
WO2016133486A1 (en) * | 2015-02-16 | 2016-08-25 | Siemens Aktiengesellschaft | Ring segment system for gas turbine engines |
US9863265B2 (en) * | 2015-04-15 | 2018-01-09 | General Electric Company | Shroud assembly and shroud for gas turbine engine |
US10697314B2 (en) | 2016-10-14 | 2020-06-30 | Rolls-Royce Corporation | Turbine shroud with I-beam construction |
EP3369892B1 (en) * | 2017-03-03 | 2020-08-19 | MTU Aero Engines GmbH | Contouring of a blade row platform |
US10557365B2 (en) | 2017-10-05 | 2020-02-11 | Rolls-Royce Corporation | Ceramic matrix composite blade track with mounting system having reaction load distribution features |
US11149563B2 (en) | 2019-10-04 | 2021-10-19 | Rolls-Royce Corporation | Ceramic matrix composite blade track with mounting system having axial reaction load distribution features |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3892497A (en) | 1974-05-14 | 1975-07-01 | Westinghouse Electric Corp | Axial flow turbine stationary blade and blade ring locking arrangement |
GB2019954B (en) * | 1978-04-04 | 1982-08-04 | Rolls Royce | Turbomachine housing |
US5127793A (en) * | 1990-05-31 | 1992-07-07 | General Electric Company | Turbine shroud clearance control assembly |
US5167488A (en) | 1991-07-03 | 1992-12-01 | General Electric Company | Clearance control assembly having a thermally-controlled one-piece cylindrical housing for radially positioning shroud segments |
FR2683851A1 (en) * | 1991-11-20 | 1993-05-21 | Snecma | TURBOMACHINE EQUIPPED WITH MEANS TO FACILITATE THE ADJUSTMENT OF THE GAMES OF THE STATOR INPUT STATOR AND ROTOR. |
US5320487A (en) * | 1993-01-19 | 1994-06-14 | General Electric Company | Spring clip made of a directionally solidified material for use in a gas turbine engine |
-
2000
- 2000-03-15 JP JP2000606878A patent/JP2002540337A/en not_active Withdrawn
- 2000-03-15 CA CA002366357A patent/CA2366357A1/en not_active Abandoned
- 2000-03-15 DE DE50003360T patent/DE50003360D1/en not_active Expired - Fee Related
- 2000-03-15 EP EP00916951A patent/EP1163430B1/en not_active Expired - Lifetime
- 2000-03-15 WO PCT/EP2000/002296 patent/WO2000057033A1/en active IP Right Grant
- 2000-03-15 US US09/937,214 patent/US6602050B1/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO0057033A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP1163430B1 (en) | 2003-08-20 |
DE50003360D1 (en) | 2003-09-25 |
US6602050B1 (en) | 2003-08-05 |
CA2366357A1 (en) | 2000-09-28 |
WO2000057033A1 (en) | 2000-09-28 |
JP2002540337A (en) | 2002-11-26 |
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