EP2955336B1 - Boîtier intermédiaire pour une turbine à gaz et turbine à gaz dotée d'un tel boîtier intermédiaire - Google Patents

Boîtier intermédiaire pour une turbine à gaz et turbine à gaz dotée d'un tel boîtier intermédiaire Download PDF

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Publication number
EP2955336B1
EP2955336B1 EP14172048.2A EP14172048A EP2955336B1 EP 2955336 B1 EP2955336 B1 EP 2955336B1 EP 14172048 A EP14172048 A EP 14172048A EP 2955336 B1 EP2955336 B1 EP 2955336B1
Authority
EP
European Patent Office
Prior art keywords
housing
hub
intermediate housing
gas
radial direction
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.)
Not-in-force
Application number
EP14172048.2A
Other languages
German (de)
English (en)
Other versions
EP2955336A1 (fr
Inventor
Hermann Klingels
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP14172048.2A priority Critical patent/EP2955336B1/fr
Priority to ES14172048T priority patent/ES2716100T3/es
Priority to US14/732,284 priority patent/US9938858B2/en
Publication of EP2955336A1 publication Critical patent/EP2955336A1/fr
Application granted granted Critical
Publication of EP2955336B1 publication Critical patent/EP2955336B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • F01D25/164—Flexible supports; Vibration damping means associated with the bearing
    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to an intermediate housing according to the preamble of claim 1 and a gas turbine with such an intermediate housing.
  • An intermediate housing for a gas turbine is for example the US 6,763,653 B2 to be known as known.
  • the intermediate housing comprises at least one outer housing element, in particular in the form of an outer housing shell, which is for example at least substantially annular.
  • the intermediate housing comprises at least one hub element arranged in the radial direction on the inside of the outer housing element.
  • the hub element is an at least substantially annular inner structure through which a hub or a hub chamber or a bearing chamber of the gas turbine is at least partially formed or delimited.
  • at least one rotor, in particular at least one turbine wheel, of the gas turbine is rotatably mounted on the hub element about an axis of rotation relative to the hub element.
  • the rotor is arranged, for example, at least partially in the hub element or the hub.
  • the intermediate housing further comprises at least one strut, which extends, for example, at least substantially in the radial direction.
  • the outer housing element is connected via the strut with the inner hub member.
  • a plurality of such struts is provided, via which the outer housing element is connected to the hub element.
  • the intermediate housing further comprises at least one trim element, which is also commonly referred to as "fairing".
  • the strut is at least partially lined on the outer circumference side.
  • the cladding element on a passage opening, which is penetrated by the strut.
  • the strut extends in the radial direction through the passage opening.
  • a channel through which gas can flow is at least partially delimited by the cladding element, at least in the radial direction.
  • the gas is, for example, hot gas, so that the channel is also referred to as "hot gas channel”.
  • Such an intermediate housing is usually used in multi-shaft gas turbines.
  • the channel formed as a hot gas flow channel is usually arranged in the flow direction of the gas between turbine regions of the gas turbine.
  • a first of the turbine sections is a high pressure turbine section, with the second turbine section being a low pressure turbine section.
  • the hot gas-carrying flow channel is arranged, for example, between the high-pressure turbine region and an intermediate-pressure turbine region of the three-shaft gas turbine.
  • such a hot gas leading flow channel is arranged between the intermediate-pressure turbine region and the low-pressure turbine region of the three-shaft gas turbine.
  • the arranged in the region of the channel strut provides a structural connection of the outer housing member with the hub member and crosses the gas flow.
  • the channel is often designed as an integral component.
  • a segmented construction of the channel is provided.
  • several channel segments such as the cladding element are provided, which are arranged sequentially in the circumferential direction of the outer housing element, that is, one behind the other.
  • At least one channel for guiding the gas is at least partially delimited by the respective channel segments.
  • the US 2010/0303610 A1 discloses an intermediate casing for a gas turbine, comprising at least one outer casing member having at least one hub member radially inwardly of the outer casing member, at least one strut via which the outer casing member is connected to the hub member, and at least one gas permeable member Channel at least partially in the radial direction at least partially delimiting and formed separately from the housing element cladding element, which for at least partially outer peripheral side cladding of the strut has a through opening, which is penetrated by the strut.
  • Object of the present invention is to provide an intermediate housing and a gas turbine of the type mentioned, in which an excessive heat input into the outer housing member can be avoided while achieving a weight and cost-effective construction of the intermediate housing.
  • a first aspect of the invention relates to an intermediate housing for a gas turbine, with at least one outer housing element.
  • the intermediate housing further has at least one hub element arranged in the radial direction on the inside of the outer housing element.
  • the intermediate housing comprises at least one strut, via which the outer housing element is connected to the hub element.
  • the intermediate housing comprises at least one cladding element formed separately from the housing element, through which a channel through which gas can flow is at least partially delimited, at least in the radial direction.
  • the cladding element thus acts as a channel segment.
  • the cladding element for at least partially outer peripheral side cladding of the strut.
  • the cladding element on a passage opening, which is penetrated by the strut.
  • the strut is covered on the outer circumference at least partially by means of the cladding element.
  • the cladding element is coupled at least in the radial direction exclusively with the hub member.
  • the hub member By this is meant that there is no radial coupling between the cladding element and the outer casing element, which for example constitutes an outer casing shell.
  • a plurality of housing elements separately formed lining elements is provided, which follow one another in the circumferential direction of the housing member and each at least partially delimit a gas-flow channel in the radial direction at least partially. From the avoidance of the excessive heat input also results in a particularly long life of the intermediate housing, as acting on the outer housing element loads can be kept low.
  • the cladding element is coupled in the radial direction via at least one support element with the hub member.
  • at least one vane for at least partially conducting the gas flowing through the channel is provided, wherein the guide vane is supported in the radial direction on the support element.
  • the guide vane is used to divert or divert the gas flowing through the channel, so that an advantageous flow or flow direction can be impressed on the gas.
  • the gas aerodynamically particularly advantageous to flow through the gas channel it is possible to direct the gas or its flow by means of the guide vane in such a way that a turbine wheel arranged downstream of the vane in the direction of flow of the gas can be flown particularly advantageously by the gas.
  • a particularly efficient and thus efficient operation of the gas turbine can be realized.
  • the vane is supported in the radial direction inwardly on the support element, an excessive heat input from the vane into the outer housing element can be avoided, since for example a direct connection of the vane to the outer housing element can be dispensed with.
  • the vane is held on the support member at least in the radial direction and held on the support member on the inner hub member. Direct contact of the vane with the outer housing member and any resulting excessive heating of the outer housing member during operation of the gas turbine can thus be avoided.
  • the support element has a double function.
  • the support element serves for fastening or holding the cladding element on the hub element.
  • the support member on the other hand serves to support the guide vane in the radial direction, in particular inwardly. It is preferably provided that a direct contact of the cladding element and / or the vane is avoided with the outer housing element. In other words, it is preferably provided that the cladding element is completely spaced at least in the radial direction of the outer housing member and / or not attached to the outer housing member.
  • the heating of the outer casing element that is to say the heat input into the outer casing element, can be kept particularly low.
  • a material from which the outer housing member is formed thermally less heavily loaded than in the prior art, so that a cost-effective material for producing the outer housing member can be used.
  • the cost of the intermediate housing and the gas turbine can be kept low overall.
  • fasteners such as suspensions for attaching the cladding element and the vane can be avoided on the outer housing element, so that the number of parts, the weight and the cost of the intermediate housing can be kept very low .
  • These fasteners are, for example, usually provided openings such as holes in the outer housing member to screws, nuts and small parts. Also usually provided thickenings can be omitted in the usual holes provided.
  • the weight and manufacturing costs for producing the intermediate housing, in particular the outer housing element can be kept particularly low.
  • the radial position of the trim element and the vane is usually determined by the outer housing element, which has a lower temperature during operation of the gas turbine than the cladding element and the vane itself, since during operation of the gas turbine, the vane and the Cladding element come into direct contact with the hot gas.
  • the radial position or location of the trim element and the vane is primarily determined by the stretching behavior of the support element.
  • the support element is formed separately from the hub element and separately from the cladding element and in particular separately from the guide vane.
  • the guide vane is attached to the cladding element.
  • the effort to attach and hold the vane can be kept very low.
  • a particularly advantageous flow of the gas from the cladding element to the vane or vice versa can be realized.
  • the guide blade is fastened in a form-fitting manner to the lining element, in particular in the axial direction.
  • This can be a special simple yet effective fixation of the vane can be ensured.
  • a particularly simple assembly of the intermediate housing can be realized.
  • the cladding element, the vane, the inner hub member and the outer housing member are formed as components separately manufactured from each other.
  • Another embodiment is characterized in that the cladding element and the strut have respective form-fitting elements, via which the cladding element can be supported or supported on the strut in a form-fitting manner in the axial direction.
  • This embodiment is based on the finding that the gas flowing through the channel undergoes a pressure change through the channel and the guide vane. This results in pressure forces, which act in particular in the axial direction. These pressure forces are preferably conducted into the outer housing element. About the interlocking elements, the pressure forces can be conducted particularly advantageous and only a very small way in the outer housing element, at the same time an excessive heat input into the outer housing element can be avoided. In particular, the pressure forces can be conducted with a very small lever arm almost directly into the outer housing element.
  • the positive-locking elements are arranged in the radial direction closer to the outer housing element than to the hub element.
  • the positive-locking elements are arranged on a side facing away from the hub member in the radial direction of the outer side facing the cladding element. In this way, the path, in particular the lever arm, via which forces can be passed into the outer housing element, are kept particularly low.
  • the guide vane has a radially outer shroud, wherein a channel at least partially surrounding the channel is at least partially limited by the outer shroud and the cladding element.
  • This chamber can be supplied with gas, in particular with sealing air.
  • the sealing air has a low temperature.
  • the sealing air has a lower temperature than the gas flowing through the channel.
  • the sealing air has a higher pressure than the gas flowing through the channel. This can avoid gas from the duct due to leaks with structural parts and supply lines, especially for the hub element, come in contact.
  • the blocking air thus serves, in particular, to prevent the penetration of hot gas from the channel into the chamber.
  • the chamber is sealed against the channel by means of at least one sealing element which is supported at least on a support flange of the outer shroud.
  • a second aspect of the invention relates to a gas turbine with at least one intermediate housing according to the invention. It is provided that the channel is arranged in the flow direction of the gas between two turbine regions of the gas turbine.
  • Fig. 1 2 shows a schematic longitudinal sectional view of a gas turbine according to a first embodiment, with an intermediate housing 10, a first turbine region 12 arranged in the axial direction in front of the intermediate housing 10 and a second turbine region 14 arranged in the axial direction downstream of the intermediate housing 10.
  • the turbine regions 12, 14 are, for example, turbine stages of the gas turbine. These turbine stages include respective rotors 16, 18 with respective turbine wheels 20, 22.
  • the intermediate housing 10 has an outer housing element 24 which is formed, for example, as an at least substantially annular housing shell.
  • the intermediate housing 10 comprises a generally designated 26 hub element, which is formed for example as at least substantially annular inner structure.
  • the hub element 26 is arranged in the radial direction of the gas turbine and thus of the intermediate housing 10 on the inside of the outer housing element 24.
  • the hub member 26 includes, for example, a first hub portion 28 on which the rotor 16 is rotatably supported about an axis of rotation relative to the hub member 26 and relative to the intermediate housing 10.
  • a bearing 30 is provided, which is designed for example as a rolling bearing.
  • the rotor 16 is supported in the radial direction outwardly on the hub member 26 and mounted thereon.
  • the bearing 30 is arranged in a receiving space 34, which is sealed by means of seals 36, for example.
  • a storage chamber is at least partially limited. In this storage chamber, for example, the rotor 16 is at least partially received. It is also conceivable that the rotor 18 is at least partially received in the bearing chamber.
  • the hub element 26 furthermore comprises a second hub part 38, which in the present case is designed as a profile component and has a closed hollow cross-section 40.
  • the second hub portion 38 is also referred to as a "hub” or “hub body”.
  • the hub (second hub part 38) is at least substantially annular or designed as a torsionally stiff, box-shaped ring, on which the bearing chamber formed by the hub part 28 is fixed.
  • the hub portions 28, 38 are formed as separately manufactured and interconnected components.
  • the hub member 26 may be formed by a simple ring or formed by two axially spaced rings.
  • the hub part 38 can be omitted.
  • the hub part could have an open cross section, in particular a hollow cross section.
  • the housing member 24 and the hub member 26 are disposed concentric with the axis of rotation, which is also referred to as "engine axis".
  • the intermediate housing 10 preferably comprises a plurality of struts, of which in Fig. 1 a strut designated 42 can be seen.
  • the following statements about the strut 42 can be easily transferred to the other struts.
  • the struts are distributed in the circumferential direction of the hub member 26 about its circumference, in particular evenly distributed, wherein the outer housing shell (outer housing member 24) are connected via the struts with the hub member 26.
  • the strut 42 is connected at one end to the outer housing member 24 and the other end to the hub portion 38.
  • the hub part 38 is used in particular when a duct 44, designed as a hot gas duct, of the intermediate housing 10 is arranged in the radial direction far away from the axis of rotation.
  • the strut 42 is connected via the hub part 38 to the hub part 28 and thus to the hub element 26.
  • the hub portion 38 is not provided, then the strut 42 formed as a rib is directly connected to the bearing chamber, that is, the hub portion 28.
  • the intermediate housing 10 further comprises a trim element 46, which is also referred to as "fairing" and is designed as a channel segment.
  • a trim element 46 which is also referred to as "fairing" and is designed as a channel segment.
  • the lining element 46 namely the channel 44 is at least partially limited at least in the radial direction.
  • the channel 44 is at least partially bounded by the cladding element 46 in the radial direction towards the outside and in the radial direction inwards.
  • a plurality of cladding elements is provided, wherein the channel 44 and / or respective channels of the intermediate housing 10 through which gas can flow are at least partially delimited by the respective cladding elements at least in the radial direction.
  • the following comments on the trim element 46 can readily be applied to the other, in Fig. 1 unrecognizable cladding elements are transmitted.
  • a segmented construction of the channel 44 or the channels is provided. The individual channel segments are consecutive, for example, in the circumferential direction of the housing element 24, that is arranged one behind the other.
  • the cladding element 46 is a component produced separately from the housing element 24 and from the hub element 26 and also serves for at least partially cladding the strut 42 on the outer peripheral side.
  • the cladding element 46 has a through opening 48, which is penetrated by the strut 42.
  • the strut 42 extends at least substantially in the radial direction from the housing element 24 toward the hub part 38 and thereby through the passage opening 48, so that the strut 42 is surrounded on the outer peripheral side at least partially by the lining element 46.
  • the strut 42 is surrounded by the lining element 46 completely circumferentially in this length region with respect to its radial extension, at least in a longitudinal region and in its circumferential direction.
  • the lining element 46 By means of the lining element 46 thus the gas flowing through the channel 44 is guided around the strut 42, without touching the strut 42 directly. This protects the strut from direct contact with the hot gas.
  • the turbine portion 12 In the flow direction of the gas through the channel 44, the turbine portion 12 is disposed upstream of the channel 44, wherein the turbine portion 14 is disposed downstream of the channel 44.
  • Fig. 2 shows the strut 42 and the cladding element 46 in a schematic cross-sectional view.
  • the fairing (cladding element 46) is formed as a hollow aerodynamic profile with an outer and inner portion.
  • the channel 44 or the channels can be limited by so-called panels. Such panels are at least substantially flat components, for example, limit the remaining annulus between the fairings. Depending on the dimensions of the channel 44 and the number of struts used different designs are conceivable.
  • the channel 44 may, for example, by fairings and panels, each inside and on the outside, or by fairings and panels, each outside, or limited only by fairings or formed.
  • the lining element 46 is coupled at least in the radial direction exclusively with the hub element 26.
  • the cladding element 26 is not coupled to or fastened to the housing element 24, but the cladding element 46 is supported via support elements 50, 52 in the radial direction exclusively on the hub element 26 and in this case on the hub part 38.
  • the cladding element 46 is fastened to the support elements 50, 52, which in turn are fastened to the hub part 38.
  • the support members 50, 52 are relatively soft in the axial direction compared to the radial direction.
  • the support elements 50, 52 are membrane-like or membrane-shaped.
  • the support elements 50, 52 are formed as a membrane over which the cladding element 46 is supported in the radial direction on the hub member 26.
  • the support elements 50, 52 may be fastened directly to the bearing chamber, that is to say to the hub part 28, and / or directly to the strut 42.
  • the support elements take over radial forces and serve for circumferential fixation of the lining element 46.
  • the intermediate housing 10 further includes at least one vane element 54, which is also referred to as a "vane segment".
  • the vane element 54 includes at least one vane 56 for at least partially directing the gas flowing through the channel 44.
  • the intermediate housing 10 may have a plurality of stator blade segments, of which in Fig. 1 the vane element 54 can be seen.
  • the following explanations about the vane element 54 may also be readily applied to the other vanes. Through the vanes, a guide grid for guiding the gas is formed. Therefore, the vanes are also referred to as "Leitgittersegmente".
  • Fig. 1 It can be seen that the vane 56 is arranged in the flow direction of the gas through the channel 44 downstream of the lining element 46 and upstream of the turbine region 14.
  • the guide vane 56 serves to redirect or divert at least a portion of the gas flowing through the channel 44 in such a way that the gas can flow aerodynamically advantageously to a blading of the rotor 18. As a result, a particularly efficient operation of the gas turbine can be realized.
  • the guide vane 56 is not held approximately on the outer housing member 24, but the vane 56 is supported in the radial direction on the support member 52. As a result, the guide vane 56 is supported by the support element 52 on the hub element 26 in the radial direction inwardly and in particular held.
  • the guide vane 56 is positively connected to the corresponding cladding element 46.
  • the guide vane 56 is fastened in a form-fitting manner to the corresponding cladding element 46 in the axial direction.
  • the vane 56 is supported in the axial direction on the trim element 46.
  • the guide vane 56 comprises a receiving element 58, through which a receptacle is limited.
  • a flange 60 of the cladding element 46 is at least partially received, wherein the flange 60 is at least partially covered in the axial direction by the receiving element 58. This results in the positive fastening of the guide vane 56 on the cladding element 46 in the axial direction.
  • the support element 52 has a flange 62, which is accommodated at least in regions in a receptacle of a corresponding receiving element 64 of the lining element 46.
  • the cladding element 46 is fastened via the receiving element 64 and the flange 62 to the support element 52 and via this on the hub element 26 in the radial direction.
  • the receiving element 64 has a further receptacle in which a flange 66 of the guide vane 56 is at least partially received.
  • the guide vane 56 is supported by the receiving element 64 on the support member 52 at least in the radial direction.
  • the vane 56 has a radially outer shroud, which is referred to as "outer shroud 82".
  • outer shroud 82 By the support members 50, 52, the cladding element 46 and the outer shroud 82, a chamber 68 is at least partially limited, which surrounds the channel 44 on the outside at least partially.
  • the chamber 68 is supplied with sealing air, which opposite the gas flowing through the channel 44 has a higher pressure and a lower temperature.
  • sealing air can be ensured that structural parts and supply lines, in particular the storage chamber, do not come into contact with the channel 44 flowing through the hot gas. In particular, can be prevented by the sealing air that hot gas from the channel 44 flows through a gap in the chamber 68.
  • the chamber 68 is sealed against the channel 44 by means of sealing elements 70, 72, which in the present case are shown particularly schematically and can be designed, for example, as leaf seals or brush seals.
  • the sealing element 72 is supported on the one hand on the guide vane 56, in particular on a support flange 74, of the outer end band 82, and on the other hand on a housing element 76 of the turbine region 14.
  • the support flange 74 thus acts as a sealing flange.
  • the sealing element 70 is supported, on the one hand, on the lining element 46 and, on the other hand, via a supporting element 78 on a housing element 80 of the turbine region 12. This means that the sealing elements 70, 72 in combination with the support elements 50, 52 form the chamber 68, in particular around the lining element 46, wherein the sealing elements 70, 72 enclose the guide vane 56.
  • the gas flowing through the channel 44 undergoes a pressure change.
  • the pressure of the gas upstream of the turbine section 14 is lower than downstream of the turbine section 12. This results in compressive forces which are to be introduced into the housing element 24.
  • the front support member 50 may be provided with an axial stop which is supported on the hub member 26 and / or the strut 42. In this case, however, the pressure forces are then introduced via the strut 42 with a relatively long lever arm in the housing member 24.
  • the cladding element 46 can be supported directly on the housing element 24 in the axial direction.
  • this can result in a complex assembly.
  • Another possibility for supporting the pressure force is, for example, the pressure forces on the outer shroud 82 of the vane 56 against a connected to the housing member 24, downstream in the flow direction Housing such as the housing element 76 initiate.
  • this could result in a complicated assembly.
  • the cladding element 46 has first positive locking elements in the form of integral tabs 84.
  • the strut 42 has corresponding, second positive locking elements in the form of forks 86, through which receptacles 88 are limited.
  • the tabs 84 are at least partially received in the receptacles 88 and are covered in the axial direction by the forks 86 to the respective turbine sections 12, 14 out.
  • the forks 86 are an integral part of the struts 42. This means that the forks 86 are formed integrally with the strut 42.
  • the tabs 84 are formed integrally with the trim element 46.
  • the advantage of this support is that the pressure forces can be introduced with a very small lever arm, that is, over a very short or short path and thus almost directly into the housing element 24.
  • the interlocking elements are arranged on a side facing away from the hub member 26 in the radial direction 90 of the cladding element 46.
  • the cladding element 46 and the vane 56 can be supported in a particularly simple manner in the radial direction inwardly on the hub member 26 and thus held.
  • the chamber 68 can be particularly well sealed by simple means, so that sealing air leakage can be kept at least low.
  • thermally induced movements of the vane elements and / or the cladding elements relative to each other can be kept low, so that the wear of the intermediate housing 10 can be kept in a small frame.
  • neither the cladding element 46 nor the vane 56 is attached directly to the housing element 24, so that the heating of the outer housing element 24, that is, the heat input into the outer housing element 24, are kept particularly low.
  • Fig. 3 shows the gas turbine according to a second embodiment.
  • at least one latch 92 is provided by which the vane 56 is circumferentially supported on the housing member 24 so that circumferential forces resulting from the deflection of the gas caused by the vane 56 are introduced from the vane 56 into the housing member 24 can be.
  • this latching 92 By means of this latching 92, the above-mentioned, relatively long lever arm can be avoided.
  • Fig. 4 shows a third embodiment of the gas turbine, in which also the latch 92 is provided.
  • the cladding element 46 on circumferential webs 94 through which in the axial direction a circumferential groove 96 of the cladding element 46 is limited or formed. Via the webs 94 and the groove 96, axial forces can be transmitted to a separate component 98, which is fastened to the outer housing element 24. In the radial direction, the cladding element 46 can move relative to the component 98. The fixing of the lining element 46 in the circumferential direction takes place via the abovementioned, at least one latch 92.
  • axial support is shown.
  • the axial support of the cladding element 46 via at least one web 100 which is an integral part of the guide vane 56 and is supported on a surface of the downstream of the housing element 76.
  • the contact point between the web 100 and the housing member 76 serves as a seal.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)

Claims (9)

  1. Boîtier intermédiaire (10) pour une turbine à gaz, comprenant au moins un élément de boîtier extérieur (24), comprenant au moins un élément de moyeu (26) disposé à l'intérieur de l'élément de boîtier extérieur (24) dans une direction radiale, comprenant au moins une entretoise (42) au moyen de laquelle l'élément de boîtier extérieur (24) est relié à l'élément de moyeu (26), et comprenant au moins un élément de revêtement (46) délimitant au moins en partie, au moins dans une direction radiale, un canal (44) pouvant être parcouru par un gaz et étant réalisé séparément de l'élément de boîtier (24), lequel élément de revêtement (46) présente une ouverture de passage (48) pour le revêtement au moins partiel de l'entretoise (42) sur le pourtour extérieur, laquelle ouverture de passage est traversée par l'entretoise (42), l'élément de revêtement étant couplé à l'élément de moyeu (26) dans une direction radiale au moyen d'au moins un élément d'appui (50, 52), et au moins une aube de guidage (56) étant prévue pour le guidage au moins partiel du gaz parcourant le canal (44), et l'au moins une aube de guidage (56) prenant appui sur l'élément d'appui (50, 52) dans une direction radiale, caractérisé en ce que l'élément de revêtement (46) est couplé exclusivement à l'élément de moyeu (26) au moins dans une direction radiale.
  2. Boîtier intermédiaire (10) selon la revendication 1,
    caractérisé en ce que
    l'aube de guidage (56) est fixée à l'élément de revêtement (46).
  3. Boîtier intermédiaire (10) selon la revendication 2,
    caractérisé en ce que
    l'aube de guidage (56) est fixée par complémentarité de forme à l'élément de revêtement (46), en particulier dans une direction axiale.
  4. Boîtier intermédiaire (10) selon l'une des revendications 1 et 2,
    caractérisé en ce que
    l'aube de guidage (56) présente un carénage extérieur (82) dans une direction radiale, une chambre (68) entourant au moins en partie le canal (44) étant délimitée au moins en partie par le carénage extérieur (82) et l'élément de revêtement (46).
  5. Boîtier intermédiaire (10) selon la revendication 4,
    caractérisé en ce que
    la chambre (68) est étanchéifiée contre le canal (44) à l'aide d'au moins un élément d'étanchéité (72), lequel prend appui au moins sur une bride d'appui (74) du carénage extérieur (82).
  6. Boîtier intermédiaire selon l'une des revendications 1 à 5,
    caractérisé en ce que
    l'élément d'appui (50, 52) est réalisé séparément de l'élément de moyeu (26) et séparément de l'élément de revêtement (46).
  7. Boîtier intermédiaire (10) selon l'une des revendications précédentes,
    caractérisé en ce que
    l'élément de revêtement (46) et le moyeu (42) présentent des éléments d'emboîtement (84, 86) respectifs, au moyen desquels l'élément de revêtement (46) peut prendre appui sur l'entretoise (42) par complémentarité de forme dans une direction axiale.
  8. Boîtier intermédiaire (10) selon la revendication 7,
    caractérisé en ce que
    les éléments d'emboîtement (84, 86) sont disposés dans une direction radiale plus près de l'élément de boîtier extérieur (24) que de l'élément de moyeu (26).
  9. Turbine à gaz comprenant au moins un boîtier intermédiaire (10) selon l'une des revendications précédentes, dans laquelle le canal (44) est disposé entre deux zones de turbine (12, 14) de la turbine à gaz dans la direction d'écoulement du gaz.
EP14172048.2A 2014-06-12 2014-06-12 Boîtier intermédiaire pour une turbine à gaz et turbine à gaz dotée d'un tel boîtier intermédiaire Not-in-force EP2955336B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP14172048.2A EP2955336B1 (fr) 2014-06-12 2014-06-12 Boîtier intermédiaire pour une turbine à gaz et turbine à gaz dotée d'un tel boîtier intermédiaire
ES14172048T ES2716100T3 (es) 2014-06-12 2014-06-12 Carcasa intermedia para una turbina de gas y turbina de gas con dicha carcasa intermedia
US14/732,284 US9938858B2 (en) 2014-06-12 2015-06-05 Mid-frame for a gas turbine and gas turbine having such a mid-frame

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14172048.2A EP2955336B1 (fr) 2014-06-12 2014-06-12 Boîtier intermédiaire pour une turbine à gaz et turbine à gaz dotée d'un tel boîtier intermédiaire

Publications (2)

Publication Number Publication Date
EP2955336A1 EP2955336A1 (fr) 2015-12-16
EP2955336B1 true EP2955336B1 (fr) 2019-02-27

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EP14172048.2A Not-in-force EP2955336B1 (fr) 2014-06-12 2014-06-12 Boîtier intermédiaire pour une turbine à gaz et turbine à gaz dotée d'un tel boîtier intermédiaire

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US (1) US9938858B2 (fr)
EP (1) EP2955336B1 (fr)
ES (1) ES2716100T3 (fr)

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JP6614407B2 (ja) * 2015-06-10 2019-12-04 株式会社Ｉｈｉ タービン
US10364705B2 (en) * 2017-05-04 2019-07-30 United Technologies Corporation Strut assembly for bearing compartment
US10781721B2 (en) * 2018-02-09 2020-09-22 General Electric Company Integral turbine center frame
US11674400B2 (en) * 2021-03-12 2023-06-13 Ge Avio S.R.L. Gas turbine engine nozzles

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2938863A1 (fr) * 2012-12-29 2015-11-04 United Technologies Corporation Liaison mécanique destinée à un écran thermique segmenté

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Publication number Priority date Publication date Assignee Title
US6763653B2 (en) 2002-09-24 2004-07-20 General Electric Company Counter rotating fan aircraft gas turbine engine with aft booster
US6983608B2 (en) * 2003-12-22 2006-01-10 General Electric Company Methods and apparatus for assembling gas turbine engines
SE527711C2 (sv) * 2004-10-06 2006-05-16 Volvo Aero Corp Lagerstativstruktur och gasturbinmotor som innefattar lagerstativstrukturen
US20100303610A1 (en) 2009-05-29 2010-12-02 United Technologies Corporation Cooled gas turbine stator assembly
FR2956695B1 (fr) * 2010-02-25 2012-11-16 Turbomeca Support de palier arriere souple avec butee pour turbomachine
US8702377B2 (en) * 2010-06-23 2014-04-22 Honeywell International Inc. Gas turbine engine rotor tip clearance and shaft dynamics system and method
WO2014052007A1 (fr) * 2012-09-28 2014-04-03 United Technologies Corporation Cadre de turbine intermédiaire ayant une fixation de carénage

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
EP2938863A1 (fr) * 2012-12-29 2015-11-04 United Technologies Corporation Liaison mécanique destinée à un écran thermique segmenté

Also Published As

Publication number Publication date
US20150361893A1 (en) 2015-12-17
ES2716100T3 (es) 2019-06-10
EP2955336A1 (fr) 2015-12-16
US9938858B2 (en) 2018-04-10

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