EP4127408A1 - Carter intermédiaire de turbomachine - Google Patents
Carter intermédiaire de turbomachineInfo
- Publication number
- EP4127408A1 EP4127408A1 EP21723322.0A EP21723322A EP4127408A1 EP 4127408 A1 EP4127408 A1 EP 4127408A1 EP 21723322 A EP21723322 A EP 21723322A EP 4127408 A1 EP4127408 A1 EP 4127408A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- arm
- space
- radial surface
- longitudinal axis
- radial
- 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
Links
- 238000004519 manufacturing process Methods 0.000 claims description 17
- 238000009412 basement excavation Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 244000261422 Lysimachia clethroides Species 0.000 description 5
- 238000013461 design Methods 0.000 description 5
- 230000007423 decrease Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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
- 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
- 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
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
-
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/73—Shape asymmetric
Definitions
- the invention relates to an intermediate casing of a turbomachine.
- the invention relates more specifically to the profile of the radial surfaces of the walls of a turbomachine intermediate casing, and to a method of manufacturing a turbomachine intermediate casing.
- an intermediate casing 1 known from the prior art is a structural part of a turbomachine, interposed between two rotors (not shown) of the turbomachine, said rotors being configured to be rotated at different speeds .
- an intermediate casing generally extends between the low pressure compressor and the high pressure compressor of a double-barrel, double-flow, direct-drive turbomachine.
- an intermediate casing In a triple-barrel turbomachine or in a geared turbomachine, an intermediate casing generally extends between the fan and the low-pressure compressor.
- the intermediate housing 1 slows down the air flow between the two rotors.
- it generally has a gooseneck structure ("gooseneck” or “swanneck” in English terminology), in which the passage section of the flow of air entering the intermediate casing 1 is smaller than the passage cross section of the air flow leaving the intermediate casing.
- the intermediate casing 1 comprises a plurality of arms 2 extending between the inner radial wall 3 and the outer radial wall 4 of the intermediate casing 1, and having an aerodynamic profile.
- the arms 2 make it possible to transfer forces to the structural and stator parts of the turbomachine, typically from the bearings of the low pressure shaft to the fan casing (not shown).
- the arms 2 form an aerodynamic fairing for the passage of easements 5 (e.g. drain, mechanical drive shaft of the compressor, rotation sensor) extending between the internal radial part and the external radial part of the turbomachine.
- the easements 5 do not all have the same size. Consequently, as particularly visible in FIG. 3, the arms 2 of the intermediate casing 1 do not all have the same thickness. Furthermore, the position of the maximum thickness, the along the chord of the aerodynamic profile, may also differ from one arm 2 to another. This position can moreover be determined during design in order to reduce the pressure losses induced by the arms 2 or to limit the distortion induced on one of the rotors.
- the shape of the internal radial wall 3 and of the external radial wall 4 is identical, and symmetrical, over the entire intermediate casing 1.
- the walls 3, 4 are generally designed in cross section. circular.
- a first section has an area A1 greater than a second section, itself having an area A2 greater than the area A3 of a third section.
- such heterogeneities are detrimental to the aerodynamic quality of the air flow through the intermediate casing 1, in particular with regard to pressure losses.
- the current design of the walls 3, 4 of the intermediate casing 1 is insufficient in this regard. In fact, it only makes it possible to control the slowing down of the air flow at the level of arms 2, the maximum thickness of which is close to the average of the maximum thicknesses. To do this, it provides for uniformly hollowing out the outer wall 4 of the intermediate casing 1, equidistant from the leading edges and the trailing edges of the arms 2, so as to avoid re-acceleration of the flow. The depth of this digging systematically depends on the average of the maximum thicknesses of the arms. Thus, the radius of the circular section of the walls 3, 4 depends on an average maximum thickness of the arms 2 of the intermediate casing 1.
- One of the aims of the invention is to improve the aerodynamic behavior of the flow within an intermediate casing.
- Another object of the invention is to improve the specific consumption of a turbomachine. Another object of the invention is to improve the operability of a rotor disposed downstream of an intermediate casing.
- the subject of the invention is an intermediate turbomachine casing, said intermediate casing: having a longitudinal axis, comprising: o an internal wall having an external radial surface with respect to the longitudinal axis, o an external wall having a inner radial surface with respect to the longitudinal axis, facing the outer radial surface, and o a first arm, a second arm, a third arm, and a fourth arm extending radially from the outer radial surface to the internal radial surface, and in which: the external radial surface, the internal radial surface, the first arm and the second arm define between them a first space having a first area in a first section plane of said intermediate casing, perpendicular to the longitudinal axis, where the outer radial surface and the inner radial surface are separated, in the first space and in the first section plane, by a radial distance of first space e, with respect to the longitudinal axis, o the outer radial surface, the inner radial surface, the
- each inter-arm surface has a profile adapted to the thickness of the adjacent arms, so that the flow is uniformly slowed down through the entire intermediate casing. This results in homogeneity in the aerodynamic behavior of the flow through the intermediate housing, which improves operability. of a rotor arranged downstream of the intermediate casing and, from there, the specific consumption of the turbomachine.
- the intermediate casing according to the invention can also include at least one of the following characteristics, taken alone or in combination:
- the first arm, the second arm, the third arm, and the fourth arm each have: o a plurality of thicknesses along the longitudinal axis, and o a maximum thickness among said plurality of thicknesses
- the first cutting plane passes through: o the first arm and the second arm at the level of a respective maximum thickness of the first arm and of the second arm, and / or o the third arm and the fourth arm at the level of a respective maximum thickness of the third arm and of the fourth arm,
- the first space has a third area in a second section plane of said intermediate housing, perpendicular to the longitudinal axis, and offset from the first section plane along the longitudinal axis
- the second space has a fourth area in the second section plane
- the third area and the fourth area are substantially identical
- the inner radial surface and the outer radial surface have, in the second section plane, circular profiles
- the profile of the internal radial surface has, in the first section plane, an additional concavity compared to a circular profile
- the profile of the external radial surface has, in the first section plane, an additional concavity compared to a circular profile
- the subject of the invention is also a turbomachine comprising a turbomachine casing as described above.
- a subject of the invention is a method of manufacturing an intermediate casing for a turbomachine, said intermediate casing: having a longitudinal axis, comprising: o an inner wall having an outer radial surface relative to the longitudinal axis, o an outer wall having an inner radial surface relative to the longitudinal axis, facing the outer radial surface, and o a first arm, a second arm, a third arm, and a fourth arm extending radially from the outer radial surface to the inner radial surface, and in which: the outer radial surface, the inner radial surface, the first arm and the second arms define between them a first space having a first area in a first section plane of said intermediate casing, perpendicular to the longitudinal axis, where the outer radial surface and the inner radial surface are separated, in the first space and in the first plane cutting, by a radial distance of first space, relative to the longitudinal axis, o the radial outer surface, the radial inner surface,
- the manufacturing process according to the invention can further include at least one of the following characteristics, taken alone or in combination:
- the first arm, the second arm, the third arm, and the fourth arm of the intermediate casing each have: o a plurality of thicknesses along the longitudinal axis, and o a maximum thickness among said plurality of thicknesses, the method further comprising the steps of: performing a first digging in the outer wall and / or in the inner wall, so that the outer radial surface and the inner radial surface are separated, in the first space and in the first section plane, by: o a first radial distance of first space, with respect to the longitudinal axis, the first radial distance of first space extending from a point of the external radial surface and / or of the internal radial surface outside the first hollow, and o a second radial distance of first space, with respect to the longitudinal axis, the second radial distance of first space extending from a point of the outer radial surface and / or the inner radial surface in the first recess, such that the distance between the first radial distance of first space and the second
- Figure 1 already described, is a perspective view of an intermediate casing known from the prior art.
- Figure 2 is a longitudinal sectional view of the intermediate housing illustrated in Figure 1.
- Figure 3 is another cross-sectional view perpendicular to the longitudinal axis of the intermediate housing shown in Figure 1.
- FIG. 4 is a view in a first transverse sectional plane perpendicular to the longitudinal axis of a first embodiment of a turbomachine intermediate casing according to the invention.
- Figure 5 is a circumferentially developed sectional view of a second embodiment of a turbomachine intermediate casing according to the invention.
- FIG. 6 is a view in a second transverse sectional plane perpendicular to the longitudinal axis of a third embodiment of a turbomachine intermediate casing according to the invention.
- FIG. 7 is a flowchart detailing the steps of a first example of implementation of a manufacturing process according to the invention.
- FIG. 8 is a view in a first sectional plane of an intermediate casing produced with the aid of a second exemplary implementation of a manufacturing process according to the invention.
- an intermediate casing 1 is a structural part of a turbomachine, interposed between two rotors (not shown) of the turbomachine, said rotors being configured to be rotated at different speeds.
- the intermediate casing 1 can extend between a low pressure compressor and a high pressure compressor of a double-body, double-flow, direct-drive turbomachine.
- the intermediate housing 1 can extend between the fan and the low pressure compressor.
- the intermediate casing 1 has a longitudinal axis X-X.
- the intermediate casing 1 further comprises:
- the arms 21, 22, 23, 24 make it possible to transfer forces to structural and stator parts of the turbomachine (not shown), which are connected to the internal wall 3 and to the external wall 4.
- the arms 21 , 22, 23, 24 form an aerodynamic fairing for the passage of easements (not shown).
- the intermediate casing 1 makes it possible to slow down an air flow which passes through it.
- it generally has a gooseneck structure (“gooseneck” or “swanneck” in English terminology), in which a section of passage of the air flow at the inlet of the intermediate casing 1 is smaller. that a section of passage for the air flow at the outlet of the intermediate casing 1.
- passages for the air flow are formed between the arms 21, 22, 23, 24. More precisely, the surface external radial 30, the internal radial surface 40, the first arm 21 and the second arm 22 define between them a first space 6, and the external radial surface 30, the internal radial surface 40, the third arm 23 and the fourth arm 24 define between them a second space 7.
- the second arm 22 and the third arm 23 are merged, so that the first space 6 and the second space 7 are adjacent in a circumferential direction around the longitudinal axis X-X.
- first space 6 has a first area A1
- second space 7 has a second area A2.
- Figure 4 is a view of the intermediate casing 1 in the first section plane P1.
- the outer radial surface 30 and the inner radial surface 40 are separated, in the first space 6 and in the first section plane P1, by a radial distance from the first space D1
- the outer radial surface 30 and the surface internal radial 40 are separated, in the second space 7 and in the first section plane P1, by a radial distance from the second space D2.
- the concept of “radial” is here defined with respect to the longitudinal axis XX.
- the internal radial surface 30 and / or the external radial surface 40 have, in the first section plane P1, profiles adapted so that:
- the radial distance of the first space D1 and the radial distance of the second space D2 are different.
- the flow passage section within the intermediate casing 1 is identical throughout said intermediate casing 1, at least at the level of the first plane. cutting P1, which allows greater control of the slowing down of the flow flowing through the intermediate casing 1.
- only one of the two radial surfaces 30, 40, for example the internal radial surface 40, as visible in Figure 4 shows different inter-arm profiles around the longitudinal axis XX, and is dimensioned so that its profile is adapted to the different geometries of the arms 21, 22, 23, 24.
- it s ' is an intermediate casing element 1 easy to design and / or to profile during the manufacture and / or maintenance of the turbomachine.
- the profile of the internal radial surface 40 (illustrated in solid lines) has, in the first section plane P1, an additional concavity 401, 402, 403, 404 with respect to a profile circular (shown in dotted lines).
- This concavity 401, 402, 403, 404 forms a hollow, the depth of which depends on the thickness of the arm 21, 22, 23, 24 closest to said hollow. The greater the thickness of the arm 21, 22, 23, 24 compared to the average thickness of the arms 21, 22, 23, 24, the deeper the concavity 401, 402, 403, 404.
- the profile of the outer wall 40 comprises several additional concavities 401, 402, 403, 404 relative to a circular profile, for example concavities 401, 402 of the same orientation, and deeper than the profile.
- circular, and concavities 403, 404 of orientation opposite to the circular profile This is not, however, limiting since, in another embodiment, alternately or in combination, the profile of the outer radial wall 30 has, in the first section plane, an additional concavity 401, 402, 403, 404 relative to to a circular profile.
- each of the arms 21, 22, 23, 24 has a plurality of thicknesses e1, e2, e3, e4 along the longitudinal axis XX. More precisely, each arm 21, 22, 23, 24 has a chord C1, C2, C3, C4 connecting a leading edge 210, 220, 230, 240 to a trailing edge 212, 222, 232, 242 of a aerodynamic profile of said arm 21, 22, 23, 24, in a plane substantially parallel to the average flow within the intermediate casing 1.
- Each thickness e1, e2, e3, e4 is therefore taken perpendicular to the chord C1, C2, C3 , C4, along the longitudinal axis XX, between a lower surface 211, 221, 231, 241 and an upper surface 213, 223, 233, 243 of the aerodynamic profile of the arm 21, 22, 23, 24.
- profiling of the walls 30, 40 as described above is carried out in the inter-arm space, at the level of the thick maximum urs em1, em2, em3, em4 respective arms 21, 22, 23, 24.
- the first section plane P1 previously described passes through:
- the first space 6 has a third area A3, and the second space 7 has a fourth area A4.
- the third area A3 and the fourth area A4 are substantially identical, and the internal radial surface 30 as well as the external radial surface 40 have, in the second section plane P2, circular profiles. Indeed, as visible in Figure 5, it is not necessary to modify the profile of the radial surfaces 30, 40 of the walls 3, 4 over the entire length of the arms 21, 22, 23, 24, along the longitudinal axis XX.
- the aerodynamic profiles of the arms 21, 22, 23, 24 are substantially identical at positions sufficiently far from the respective maximum thicknesses em1, em2, em3, em4 of the arms 21, 22, 23, 24, along the axis longitudinal XX. Consequently, the flow is homogeneous and uniform as the second section plane P2 passes, without it being necessary to modify the profile of the radial surfaces 30, 40 of the walls 3, 4.
- the intermediate casing 1 has a longitudinal axis X-X, and further comprises:
- the external radial surface 30, the internal radial surface 40, the first arm 21 and the second arm 22 define between them a first space 6, and the external radial surface 30, the internal radial surface 40, the third arm 23 and the fourth arm 24 define between them a second space 7.
- the first space 6 has a first area A1
- the second space 7 has a second area A2.
- each of the arms 21, 22, 23, 24 has a plurality of thicknesses along the longitudinal axis XX. More precisely, each arm 21, 22, 23, 24 has a chord connecting a leading edge to a trailing edge of an aerodynamic profile of said arm 21, 22, 23, 24, in a plane substantially parallel to the flow means within the intermediate casing 1.
- Each thickness is therefore taken perpendicular to the chord along the longitudinal axis XX, between an intrados and an extrados of the aerodynamic profile of the arm 21, 22, 23, 24.
- a maximum thickness em1, em2, em3, em4 the position of which along the rope may be different from one arm 21, 22, 23, 24 to the other.
- the method E comprises a profiling step E1 of the internal radial surface 30 and / or the external radial surface 40 so that, in the first section plane P1:
- the radial distance of the first space D1 and the radial distance of the second space D2 are different.
- This profiling provides the intermediate casing 1 with the same advantages as those described above. Indeed, an air flow circulating through an intermediate casing 1 produced using such a manufacturing process E, exhibits a limited number of Mach number heterogeneities around the longitudinal axis X-X. In fact, the intermediate casing 1 no longer exhibits cross-section size disparities from one inter-arm flow channel to the other. The Mach number then decreases uniformly along the longitudinal axis X-X, at the level of the internal wall 3 and / or the external wall 4, regardless of the inter-arm flow channel considered.
- the manufacturing method E further comprises the steps of performing E2 of a first digging 401 and of performing E3 of a second digging 402 in the internal wall 3 and / or the outer wall 4 of the intermediate casing 1. More precisely, the first digging 401 is then carried out so that the external radial surface 30 and the internal radial surface 40 are separated, in the first space 6 and in the first section plane P1, by:
- first radial distance from the first space D11 a first radial distance from the first space D11, relative to the longitudinal axis XX, the first radial distance from the first space D11 extending from a point on the external radial surface 30 and / or from the internal radial surface 40 outside of the first 401 digging, and
- the second radial distance from the first space D12 extending from a point on the external radial surface 30 and / or from the internal radial surface 40 in the first dig 401.
- these radial distances D11, D12 are made such that the deviation between the first radial distance of first space D11 and the second radial distance of first space D12 is an increasing function of the deviation between:
- the second hollowing 402 is made so that the outer radial surface 30 and the inner radial surface 40 are separated, in the second space 7 and in the first section plane P1, by:
- these radial distances D21, D22 are made so that the difference between the first radial distance of second space D21 and the second radial distance of second space D22 is an increasing function of the difference between:
- an intermediate casing 1 such as that illustrated in FIGS. 4 or 8 can be obtained.
- the dotted lines represent a circular profile of internal radial surface 40, in the first section plane P1.
- the radius R of this profile depends on the average of the maximum thicknesses em1, em2, em3, em4 of the arms 21, 22, 23, 24 of the intermediate casing 1.
- this radius R is determined so that, if the arms 21, 22, 23, 24 all had the same maximum thickness em1, em2, em3, em4 equal to the average of the maximum thicknesses em1, em2, em3, em4, then this circular profile of the internal radial surface would ensure that the Mach number decreases uniformly along the longitudinal axis XX, at the level of the internal wall and / or of the external wall 4, regardless of the channel d inter-arm flow considered.
- the solid line represents, for its part, the profile of the internal radial wall 40 obtained following the digging steps E2, E3 described above.
- the profile of the internal radial surface 40 obtained is therefore non-symmetrical and has a plurality of additional concavities 401, 402, 403, 404 with respect to a circular profile. It should be noted that the profile of the outer radial wall 30 could be modified according to the same design logic, and with the same effects. However, it must be taken into account that the air flow speeds are different near the internal radial surface 40 and the external radial surface 30. In addition, the aerodynamic friction can be specific, in particular because of the shape in gooseneck. The depth of the recesses in the external radial surface 30 is therefore adapted accordingly.
- the previously described recesses 401, 402 can be made so that:
- the first hollowing 401 is centered at a section plane P1 passing through the first arm 21 and the second arm 22 at the level of the maximum thickness em1, em2 respectively of the first arm 21 and of the second arm 22, and
- the second excavation 402 is centered at a section plane P1 passing through the third arm 23 and the fourth arm 24 at the level of the respective maximum thickness em3, em4 of the third arm 23 and the fourth arm 24.
- the recesses 401, 402 are made on either side of a line connecting the positions of the maximum thicknesses em1, em2, em3, em4 of the arms 21, 22, 23,24 along the longitudinal axis XX.
- the recesses 401, 402 are made in a substantially rectangular zone of the internal radial surface 30 and / or of the external radial surface 40, as visible in FIG. 5. Even more advantageously, this rectangular zone has a width equal to about 10% of the chord C1, C2, C3, C4 of an adjacent arm 21, 22, 2324, taken in a plane substantially parallel to the average flow within the intermediate casing 1.
- the manufacturing process E implies a limited modification of the walls 3, 4 of the intermediate casing 1.
- the position of the recesses 401, 402 is optimized as a function of the position of the maximum thicknesses em1, em2, em3, em4, along the longitudinal axis XX.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2003275A FR3108937B1 (fr) | 2020-04-01 | 2020-04-01 | Carter intermédiaire de turbomachine |
PCT/FR2021/050580 WO2021198624A1 (fr) | 2020-04-01 | 2021-04-01 | Carter intermédiaire de turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP4127408A1 true EP4127408A1 (fr) | 2023-02-08 |
Family
ID=70614313
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP21723322.0A Pending EP4127408A1 (fr) | 2020-04-01 | 2021-04-01 | Carter intermédiaire de turbomachine |
Country Status (5)
Country | Link |
---|---|
US (1) | US20230220786A1 (fr) |
EP (1) | EP4127408A1 (fr) |
CN (1) | CN115485454A (fr) |
FR (1) | FR3108937B1 (fr) |
WO (1) | WO2021198624A1 (fr) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009011924A1 (de) * | 2009-03-10 | 2010-09-16 | Rolls-Royce Deutschland Ltd & Co Kg | Nebenstromkanal eines Turbofantriebwerks |
WO2012086044A1 (fr) * | 2010-12-24 | 2012-06-28 | 三菱重工業株式会社 | Structure de trajet d'écoulement et diffuseur d'échappement de turbine à gaz |
GB201700777D0 (en) * | 2017-01-17 | 2017-03-01 | Rolls Royce Plc | Fan exhaust for a gas turbine engine |
FR3064298B1 (fr) * | 2017-03-23 | 2021-04-30 | Safran Aircraft Engines | Turbomachine |
US20180306041A1 (en) * | 2017-04-25 | 2018-10-25 | General Electric Company | Multiple turbine vane frame |
-
2020
- 2020-04-01 FR FR2003275A patent/FR3108937B1/fr active Active
-
2021
- 2021-04-01 CN CN202180033294.6A patent/CN115485454A/zh active Pending
- 2021-04-01 WO PCT/FR2021/050580 patent/WO2021198624A1/fr unknown
- 2021-04-01 EP EP21723322.0A patent/EP4127408A1/fr active Pending
- 2021-04-01 US US17/916,333 patent/US20230220786A1/en active Pending
Also Published As
Publication number | Publication date |
---|---|
WO2021198624A1 (fr) | 2021-10-07 |
FR3108937B1 (fr) | 2023-03-24 |
US20230220786A1 (en) | 2023-07-13 |
FR3108937A1 (fr) | 2021-10-08 |
CN115485454A (zh) | 2022-12-16 |
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