EP4102033A1 - Boîtier de chambre de palier pour une turbomachine - Google Patents

Boîtier de chambre de palier pour une turbomachine Download PDF

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Publication number
EP4102033A1
EP4102033A1 EP22176572.0A EP22176572A EP4102033A1 EP 4102033 A1 EP4102033 A1 EP 4102033A1 EP 22176572 A EP22176572 A EP 22176572A EP 4102033 A1 EP4102033 A1 EP 4102033A1
Authority
EP
European Patent Office
Prior art keywords
housing
bearing chamber
shell
chamber housing
support ribs
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.)
Pending
Application number
EP22176572.0A
Other languages
German (de)
English (en)
Inventor
Florian Neuberger
Daniel Kirchner
Georg Kempinger
Stephan Döppl
Kaspar Wolf
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
Publication of EP4102033A1 publication Critical patent/EP4102033A1/fr
Pending legal-status Critical Current

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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
    • F01D25/16—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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings 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
    • F01D25/18—Lubricating arrangements
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • 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
    • F05D2260/98—Lubrication

Definitions

  • the present invention relates to a bearing chamber housing for bearing a shaft of a turbomachine.
  • the turbomachine can, for example, be a jet engine, e.g. B. a turbofan engine. Functionally, the turbomachine is divided into compressor, combustion chamber and turbine. In the case of the jet engine, for example, the air drawn in is compressed by the compressor and burned in the downstream combustion chamber with added kerosene. The resulting hot gas, a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process.
  • the turbine is usually made up of several stages, each with a stator (guide blade ring) and a rotor (rotor blade ring), the rotors are driven by the hot gas. In each stage, a proportion of the internal energy is withdrawn from the hot gas, which is converted into a movement of the respective rotor blade ring and thus the shaft.
  • the present subject matter relates to a bearing chamber housing for bearing the shaft, the reference to a jet engine not initially intended to limit the generality of the inventive concept.
  • the turbomachine can also be a stationary gas turbine, for example.
  • the present invention is based on the technical problem of specifying a particularly advantageous bearing chamber housing for a turbomachine and an advantageous method for its manufacture.
  • the bearing chamber housing has an outer housing shell and an inner housing shell. There is an oil space in the bearing chamber housing between the housing shells, in which the oil can collect.
  • the outer shell of the housing delimits the oil chamber radially outwards in relation to an axis of rotation of the shaft.
  • the housing inner shell is arranged radially inside it and preferably forms a bearing seat in which a bearing for supporting the shaft, such as a ball or roller bearing, can be arranged. It is radially connected to the outer shell of the housing via support ribs that extend axially at least in part, and these are in one piece with the inner and outer shells of the housing.
  • the bearing forces are at least partially absorbed by the inner shell of the housing, with the resultant flow of forces running through the support ribs.
  • the support ribs thus form a supporting structure between the inner and outer shell of the housing.
  • Two supporting ribs that are closest to one another delimit a cavity (together with the housing shells), which in the present case is open to the axial rear, ie opens into a rear opening. Viewed in tangential sections, this has a clear width that makes up at least 50% of a circumferential distance between the next adjacent supporting ribs, preferably essentially corresponding to the circumferential distance.
  • the inner housing shell is then suspended on the outer housing shell without a cantilever extending in the direction of rotation, that is to say it is designed without cantilevers.
  • the housing shells can then be connected to one another exclusively via the support ribs. This can reduce or avoid overhangs at the axially rear ends of the support ribs, which z. B. manufacturing technology can be advantageous.
  • the bearing chamber housing can thus in particular be amenable to additive manufacturing, the housing shells and the support ribs are preferably an additively manufactured part, see below in detail.
  • the tangential sections for viewing the rear opening of the cavity are taken, for example, between 10% and 90% of the radial extent of the cavity, taken from radially inward to radially outward (0% is on the outer wall surface of the housing inner shell, 100% on the inner wall surface of the housing outer shell).
  • the clear width of the rear opening makes up at least 50%, and in the order in which they are named, more preferably at least 60%, 70%, 80%, 90%, 100% of a circumferential distance between the next adjacent support ribs.
  • the circumferential distance is taken at least partially, preferably completely, in the circumferential direction.
  • the reference surfaces for the distance between the ribs are the respective side surfaces of the ribs facing the cavity.
  • the supporting ribs which extend at least partially axially, have such a basic shape, for example, that the ratio of the average wall thickness to the axial extent is at least 3, 4 or 5 (with possible upper limits of e.g. at most 100 or 50 ).
  • the basic shape of the support ribs is therefore elongated in the axial direction.
  • the support ribs each extend “at least partially axially”, which designates a proportion in the axial direction of increasingly preferably at least 70%, 80%, 90% in the order in which they are named, with a complete axial extension (100%) being preferred.
  • the terms “axial” and “radial” and the associated directions relate to the axis of rotation of the shaft, which coincides with the longitudinal axis of the turbomachine as a whole.
  • the rotors turn "around” the axis of rotation, namely in the "direction of rotation”.
  • "Ein” and “an” are indefinite articles and therefore always to be read as “at least one” or “at least one” unless expressly stated otherwise. For example, as will be seen in more detail below, there may be a plurality of cavities throughout a complete circuit.
  • the oil that collects in the cavity is typically sucked out during operation by means of oil return pumps and pumped into a collection line, via which it is returned to the oil tank is transported.
  • the oil flow required for this removal can also be improved by the cavity, which is open towards the rear in the axial direction.
  • the invention can enable a bearing chamber housing that is advantageous in operation and at the same time light and at the same time stiff.
  • the side surfaces of a respective support rib which are opposite one another in the circumferential direction, converge exclusively convexly at their axially rear end.
  • the "convex" shape of their side surfaces viewed from outside the support rib can in turn help to avoid overhangs or undercuts, e.g. B. based on an assembly direction from axially front to back.
  • the rear end of the respective support rib can be designed as an edge or, in general, as a surface. Viewed in tangential sections, two correspondingly shaped support ribs that are closest to each other form a circumferential distance that does not decrease in the axial direction towards the rear, but rather remains the same or increases.
  • At least one of the support ribs has a wall thickness that is variable over an axial and/or radial extent of the support rib, that is, changes.
  • the wall thickness is taken in the circumferential direction between the two side faces of the support rib.
  • the variable wall thickness which is possible in particular with generative manufacturing, can e.g. B. ensure a better thermal or thermomechanical balance between the housing outer and inner shell, e.g. take into account thermal expansion during operation.
  • the support ribs have different wall thicknesses among one another, that is to say in a comparison from support rib to support rib. At least some of the support ribs therefore have a different mean wall thickness, which is taken as the mean value of the respective support rib.
  • the different wall thicknesses can, for example, promote more uniform rigidity in the direction of rotation.
  • At least one of the support ribs forms an angle of at least 20° and at most 80° with the inner and outer shell of the housing with its front edge, viewed in an axial sectional plane.
  • the front edge thus runs obliquely into the inner and outer shell of the housing, i.e. not vertically.
  • At least one of the supporting ribs forms an angle of at least 20° and at most 80° with the inner or outer shell of the housing with its rear edge, viewed in an axial section plane.
  • the rear edge thus runs obliquely into the inner and outer shell of the housing, i.e. not vertically. Again, the smaller of two angles that enclose the rear edge and the inner or outer shell of the housing is considered.
  • the front and/or the rear edge are preferably inclined in such a way that the axial length of the support rib increases from radially inside to outside.
  • a total of at least 3 support ribs are provided, in the order in which they are named, increasingly preferably at least 4, 5, 6, 7, 8.
  • Advantageous upper limits can be, for example, a maximum of 200, 150, 100.
  • a fluid channel is integrated into one of the support ribs.
  • This can e.g. B. be an oil or air channel, that is flowed through by a corresponding fluid during operation.
  • the fluid channel can in particular be part of the oil system of the bearing chamber housing, via which the oil can be transported from outside into the bearing chamber housing and distributed.
  • integrated means z. B. that the housing material itself encloses the fluid channel, in particular surrounds all around.
  • the extent of the fluid channel does not extend in a straight line at least in sections, for example with a radial component in addition to an axial component, it being possible for the ratio of the components to change along the channel.
  • this refers to the course of its center line, which extends centrally in the fluid channel along its length. Viewed in sectional planes perpendicular to the flow, it lies in the centroid of the area of the internal cross section, i.e. the flow cross section. This center line then has a curvature over at least one section of the fluid channel, ie it does not run linearly.
  • a fluid channel is (also) integrated into the inner shell of the housing and can thus in particular transport oil between the support ribs.
  • the invention also relates to a turbine center frame for a turbomachine, in particular a jet engine, with a bearing chamber housing disclosed here.
  • the turbine center frame can generally also be arranged between the combustor and the turbine module(s), preferably it is designed to be arranged between two turbine modules, e.g. B. between high pressure and medium or low pressure turbine.
  • One or more bearings for guiding the shaft can then be arranged in the bearing chamber housing, for example a roller bearing in the case of the exemplary embodiment.
  • the turbine center housing delimits a hot gas channel section radially outside of the bearing chamber housing, through which the hot gas flows downstream of the combustion chamber during operation of the turbomachine.
  • the invention also relates to a method for producing a bearing chamber housing or an intermediate turbine housing disclosed in the present case, the housing inner shell, the housing outer shell and the support ribs being built up generatively.
  • the generative build-up is preferably carried out from front to back in the axial direction, e.g. B. in a powder bed process (which may also be preferred regardless of the build direction).
  • the material from which the structure is built can therefore be applied sequentially layer by layer in powder form. For each layer, a predetermined area based on the data model (the component geometry) is selectively hardened.
  • the solidification takes place by melting using a beam source, in which case, for example, an electron beam source is generally also conceivable.
  • a laser source is preferred, i.e. it is melted with a laser beam, so the generative build-up is then selective laser melting (SLM).
  • the invention also relates to the use of a bearing chamber housing or intermediate turbine housing disclosed here for a turbomachine, in particular for an aircraft engine.
  • the bearing chamber housing then accommodates the shaft of the turbomachine, which rotates around the axis of rotation during operation, the oil chamber of the bearing chamber housing is filled with oil. Oil preferably flows through the fluid channel to supply oil to the bearing chamber housing.
  • FIG 1 shows a turbomachine 1 in a schematic view, specifically a jet engine.
  • the turbomachine 1 is functionally divided into a compressor 1a, a combustion chamber 1b and a turbine 1c.
  • both the compressor 1a and the turbine 1c are each made up of two modules.
  • the intermediate turbine casing 1cc is located between a high-pressure turbine module 1ca immediately downstream of the combustion chamber 1b and a low- or medium-pressure turbine module 1cb.
  • the rotors of the turbine module 1ca rotate on a shaft 3 about an axis of rotation 4.
  • a bearing for this shaft 3 is or are arranged in the turbine center housing 1cc.
  • FIG 2 shows a part of a bearing chamber housing 20 according to the invention in a partially axially sectioned side view, the sectional plane thus includes the axis of rotation 4.
  • the bearing chamber housing 20 has a housing outer shell 21 which delimits an oil chamber 33 radially.
  • the housing inner shell 22 is radially connected to the housing outer shell 21 via support ribs 23, these parts are constructed together generatively.
  • a front edge 28 of the support rib 23 forms an angle 29 of around 35° with the outer shell of the housing 21 (and the housing inner shell 22, not shown).
  • Its rear edge 27 forms an angle 30 of around 30° with the housing outer shell 21 (and the housing inner shell 22, not shown).
  • a fluid channel 25 (shown in dashed lines) with sections that are not straight, which also extends into the housing inner shell 22 and transports oil from the outside to the oil nozzles 24 that supply the roller bearings with oil.
  • the fluid channel 25 also transports oil between the ribs 23 in the inner housing shell 22.
  • Reference number 34 references the axially rear end of the rib 23 with the rear opening 32.
  • FIG 3 shows the bearing chamber housing in section AA according to figure 2 .
  • the reference numeral 43 references the circumferential distance between two next-neighboring support ribs 23.
  • the support ribs 23 each have two opposite side faces 42 in the circumferential direction, which each converge exclusively convexly at an axially rear end 34 of the respective rib 23.
  • the support ribs 23 have a wall thickness 44 taken in the circumferential direction, which is variable over the axial extent of the support rib 23 .
  • the support ribs 23 also differ in their mean wall thicknesses.
  • the clear width 35 of the rear opening 32 in the tangential section corresponds to the circumferential distance 43, so the cavity 41 is open axially at the rear without constriction, etc.
  • the fluid channel 25 can again be seen, which transports the oil in the housing inner shell 22 between the support ribs 23 and partially supplies the other oil nozzles 24 distributed over the circumference with oil.
  • the cavity 41 is delimited by the housing inner shell 22, the housing outer shell 21 and two supporting ribs 42 which are next to one another.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Rolling Contact Bearings (AREA)
EP22176572.0A 2021-06-11 2022-05-31 Boîtier de chambre de palier pour une turbomachine Pending EP4102033A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102021115229.1A DE102021115229A1 (de) 2021-06-11 2021-06-11 Lagerkammergehäuse für eine strömungsmaschine

Publications (1)

Publication Number Publication Date
EP4102033A1 true EP4102033A1 (fr) 2022-12-14

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ID=81854875

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22176572.0A Pending EP4102033A1 (fr) 2021-06-11 2022-05-31 Boîtier de chambre de palier pour une turbomachine

Country Status (3)

Country Link
US (1) US20220397039A1 (fr)
EP (1) EP4102033A1 (fr)
DE (1) DE102021115229A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4365418A1 (fr) * 2022-11-07 2024-05-08 RTX Corporation Refroidissement par huile de zones thermiques dans un compartiment de palier
EP4365415A1 (fr) * 2022-11-07 2024-05-08 RTX Corporation Distributeur d'huile annulaire pour chambre de palier

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0251125B1 (fr) * 1986-06-24 1989-03-15 Klöckner-Humboldt-Deutz Aktiengesellschaft Centrage d'un carter
JP2005180418A (ja) * 2003-12-22 2005-07-07 General Electric Co <Ge> ガスタービンエンジンを組立てるための方法及び装置
US20190301302A1 (en) * 2018-03-30 2019-10-03 United Technologies Corporation Gas turbine engine case including bearing compartment
US20200080435A1 (en) * 2018-09-10 2020-03-12 Pratt & Whitney Canada Corp. Turbine exhaust structure for a gas turbine engine
US20200256213A1 (en) * 2019-02-08 2020-08-13 United Technologies Corporation Fluid transfer assembly for rotational equipment

Family Cites Families (7)

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Publication number Priority date Publication date Assignee Title
GB2136886A (en) 1983-03-18 1984-09-26 Rolls Royce Gas turbine engine bearing cooling
DE102014208040B4 (de) * 2014-04-29 2019-09-12 MTU Aero Engines AG Lagerkäfig und Lagereinrichtung mit einem derartigen Lagerkäfig sowie Verfahren zum Ausbilden, Reparieren und/oder Austauschen eines solchen Lagerkäfigs
CA2911812A1 (fr) * 2014-12-09 2016-06-09 Phillip H. Burnside Dispositif de palier ameliorant l'ecoulement d'huile
US10767690B2 (en) * 2018-09-21 2020-09-08 Pratt & Whitney Canada Corp. Bearing housing with damping arrangement
US10794222B1 (en) * 2019-08-14 2020-10-06 General Electric Company Spring flower ring support assembly for a bearing
US11499447B2 (en) * 2020-01-15 2022-11-15 Pratt & Whitney Canada Corp. Bearing support with frangible tabs
US11313248B2 (en) * 2020-05-05 2022-04-26 Raytheon Technologies Corporation 3-D lattice bearing support structure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0251125B1 (fr) * 1986-06-24 1989-03-15 Klöckner-Humboldt-Deutz Aktiengesellschaft Centrage d'un carter
JP2005180418A (ja) * 2003-12-22 2005-07-07 General Electric Co <Ge> ガスタービンエンジンを組立てるための方法及び装置
US20190301302A1 (en) * 2018-03-30 2019-10-03 United Technologies Corporation Gas turbine engine case including bearing compartment
US20200080435A1 (en) * 2018-09-10 2020-03-12 Pratt & Whitney Canada Corp. Turbine exhaust structure for a gas turbine engine
US20200256213A1 (en) * 2019-02-08 2020-08-13 United Technologies Corporation Fluid transfer assembly for rotational equipment

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4365418A1 (fr) * 2022-11-07 2024-05-08 RTX Corporation Refroidissement par huile de zones thermiques dans un compartiment de palier
EP4365415A1 (fr) * 2022-11-07 2024-05-08 RTX Corporation Distributeur d'huile annulaire pour chambre de palier

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Publication number Publication date
US20220397039A1 (en) 2022-12-15
DE102021115229A1 (de) 2022-12-15

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