Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
  • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
• • 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
  • F01D25/243—Flange connections; Bolting 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
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/30—Exhaust heads, chambers, 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
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/30—Exhaust heads, chambers, or the like
  • F01D25/305—Exhaust heads, chambers, or the like with fluid, e.g. liquid injection
• • 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
• • 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
  • F05D2240/55—Seals
  • F05D2240/56—Brush seals

Definitions

• the field of the invention is that of turbomachine sealing plates, and turbomachines comprising such plates.
• a turbomachine T conventionally comprises a high-pressure turbine 2 and a low-pressure turbine 3.
• the low-pressure turbine comprises several turbine stages, among which at least one rotor stage 4, that is to say mobile vane, and a stator stage 5, that is to say vane fixed distribution of the flow of air flowing in the turbine.
• the last stage of the turbine is a rotor stage, which is followed downstream with respect to the air flow in the turbomachine by a fixed blade called exhaust casing 6, which rectifies the flow of air before being discharged into the turbine. atmosphere by the nozzles.
• the flow of gas is from upstream to downstream, it is from left to right in Figures 1a and 1b.
• the exhaust casing 6 comprises a spoiler 60 extending upstream of the casing relative to the flow of air into the vein.
• This spoiler cooperates with a sectorized downstream spoiler assembly 40 of the last rotor stage 4 to form a dynamic seal, preventing air flowing in the vein of the turbine from flowing towards the space under the spoilers and vice versa.
• the seal is achieved by the natural recoil of the last rotor stage in operation, which causes the spoiler downstream of the rotor to be superimposed on the upstream spoiler of the exhaust casing in the direction of the axis of revolution of the turbomachine.
• the downstream spoiler 40 is a set of sectored parts juxtaposed 360 ° and the spoiler 60 is a single piece, both are considered as two pieces of revolution around this axis, and this results in a recovery not only axial but also circumferential of the two spoilers 40, 60.
• the recoil of this stage may be greater than its normal recoil and cause contact between the upstream spoiler of the exhaust casing and the rotor stage.
• the invention aims to overcome the disadvantages of the prior art, by providing an element for sealing between the exhaust casing and a rotor stage, while having a fuse function.
• the subject of the invention is an assembly comprising:
• an exhaust casing said casing being of revolution about a turbomachine motor axis, and comprising a bracket fixing flange, and
• said portions forming between them an angle of between 80 and 100 degrees, and the radially outer end portion having a length in an axial direction of between 15 and 35% of the height of the plate measured in the radial direction around the axis of revolution, and the end portion radially external device extending substantially parallel to said axis, and in that said elbow is angularly open downstream in the axial direction relative to the air flow in the turbomachine.
• the end portions of the plate form between them an angle of 90 degrees, the radially inner end portion extending substantially radially with respect to the axis of revolution of the plate,
• the plate further comprises an intermediate portion, the elbow interconnecting the radially outer end portion and the intermediate portion the plate further comprising a second elbow interconnecting the intermediate portion and the radially inner end portion,
• the radially inner end portion of the plate has a length between 25 and 45% of the height of the plate measured in the radial direction about the axis of revolution
• the radially outer end portion of the plate has a midpoint substantially aligned with the radially inner end portion
• the intermediate portion of the plate comprises a radially inner portion, a radially outer portion, and a bend forming a third bend of the plate, said bend interconnecting the inner and outer portions, the first and second bend being open towards the same side of the plate with respect to the axis, and the third bend being open towards the opposite side,
• the first elbow of the plate forms an angle, between the outer end portion and the outer portion of the intermediate portion, between 5 and 15 degrees
• the third elbow forms an angle between the two portions of the intermediate portion, between 60 and 80 degrees
• the first bend and the third bend of the turntable correspond to ends in the axial direction of the turntable, and the distance, measured in the axial direction, between the first bend and the radially inner end portion, substantially corresponds to a quarter of the distance, measured in the axial direction, between the first and the third elbow.
• the casing comprises a protruding spoiler extending parallel to the axis, upstream of the casing relative to the air flow, and the third elbow of the plate is downstream of the spoiler relative to the air flow
• the assembly further comprises a housing support, the housing being fixed to the housing support by the fixing flange, and the plate of revolution being fixed between the flange and the housing support, and
• the height of the plate is between 15 and 35% of the distance between the axis of revolution (Y-Y) and the radially outer end portion of the plate.
• the invention also proposes a turbomachine comprising an assembly as described above.
• the sealing plate according to the invention has a geometry for both sealing between the exhaust casing and a turbine stage, and a fuse role.
• the first elbow of the plate provides an outer end portion having a superposition in the axial direction with both the upstream spoiler of the exhaust casing, and the downstream spoiler of the rotor stage.
• This geometry also confers a flexibility to the plate, allowing it to retreat downstream relative to the flow of air in the turbomachine, in case of too great a retreat of the rotor, while preserving the housing. It thus acts as a fuse.
• the second bend makes it possible to readjust geometrically the external part of the plate with respect to the clamping place.
• the third bend makes it possible, by stiffening the plate, to modify its own frequencies of vibration to separate them from the operating frequencies of the turbomachine.
• a sheet with three elbows is indeed more rigid than a sheet comprising only two elbows.
• FIG. 1 already described, schematically represents an example of a turbomachine
• FIG. 1b already described also, shows a partial sectional view of a turbomachine at an exhaust casing.
• FIGS. 2a and 2b show a radial sectional view of two embodiments of a plate
• Figures 3a and 3b show a radial sectional view of a turbomachine assembly comprising an exhaust casing and a plate, respectively according to the embodiments of Figures 2a and 2b.
• FIG. 3c represents the deformation of the plate of the embodiment of FIGS. 2b and 3b in the event of maximum retraction of the rotor stage placed upstream.
• the gases flow from upstream to downstream through a turbomachine, from left to right in the representations of the present application.
• FIGS. 3a and 3b there is shown a turbomachine assembly 1 comprising a low-pressure turbine rotor stage 10 (visible in FIG. 3b) and an exhaust casing 20, these two parts being of revolution around each other.
• an axis XX of the turbomachine shown schematically to illustrate the directions with respect to this axis, the exhaust casing being placed downstream of the rotor stage relative to the air flow in the turbomachine.
• the turbomachine assembly also comprises a sealing plate 30, which is attached to the exhaust casing.
• This plate is a piece in one piece, of revolution about a Y-Y axis which, when the plate is mounted in the assembly, coincides with the X-X axis of revolution of the turbomachine.
• the plate can be made by turning or stamping. It is advantageously made of Hastelloy® X.
• Figures 2a and 2b there is shown a radial sectional view of such a plate, according to two embodiments, the second embodiment being preferred.
• the plate has an identical radial section over its entire circumference.
• the radial section of the plate comprises a radially inner end portion 32, and a radially outer end portion 34, these two parts forming between them an angle of between 80 and 100 degrees, and preferably equal to 90 degrees.
• the radially inner end portion 32 extends substantially radially with respect to the axis of revolution of the plate, and the radially outer end portion 34 extends substantially parallel to this axis. This allows, as described below, when the plate is fixed in an assembly 1, that the outer end portion 34 of the plate extends parallel to the axis of rotation XX of the turbomachine and that it can be superimposed on an upstream spoiler of the exhaust casing.
• the plate also comprises a first elbow 31 extending between the two end portions.
• the radially outer end portion 34 has a length L 34 between 15 and 35% of the height H of the plate, measured in the radial direction relative to the axis of revolution.
• the length in the axial direction L 34 of the portion 34 is between 18 and 25%, for example of the order of 20% of the height of the plate.
• the plate also has a small thickness, allowing it to easily deform to ensure its fuse function.
• the thickness e of the plate is less than 0.5 mm, preferably between 0.3 and 2 mm.
• the plate 30 further comprises an intermediate portion 36 and a second bend 33.
• the intermediate portion 36 is disposed between the end portions 32, 34, and the first bend 33 connects the intermediate portion 36 to the radially outer end portion 34, and the second bend 33 connects the intermediate portion 36 to the portion of the intermediate portion 36. radially inner end 32.
• This second elbow 33 makes it possible to readjust geometrically the external part of the plate 30 with respect to the clamping place by compensating the offsets. Axial.
• the plate 30 could thus be provided with a radial part devoid of elbow 33, which would give it a general shape in L.
• the radially inner end portion 32 then has, between the end and the second bend 33, a length in the radial direction L 32 of between 25 and 45% of the total height H of the plate 30 measured in the radial direction, and advantageously of the order of 30 to 35%.
• the two elbows 31, 33 of the plate 20 are open towards opposite sides with respect to the radial direction about the axis of revolution of the plate, that is to say that the centers of curvature of the plate at the two elbows lie on either side of a radial direction around the axis.
• the plate is shaped so that the radially outer end portion 34 has a midpoint substantially aligned with the radially inner end portion 32, the alignment being in a direction radial to the axis.
• the extension in the radial direction of portion 32 intersects portion 34 at a point such that the length L 34 in the axial direction is distributed at 47% upstream and 53% downstream.
• the angle ⁇ of the first elbow 31, measured as in FIG. 2a between the radially outer end portion 34 and the intermediate portion 36, is between 80 and 100 °
• the angle ⁇ of the second bend 33 measured between the intermediate portion 36 and the radial direction relative to the axis, is between 0 and 20 °.
• the intermediate portion 36 of the plate 30 comprises a radially inner portion 36a and a radially outer portion 36b, and a bend 35 connecting these two portions, this elbow forming a third bend 35 for the platinum 30.
• first and second elbows 31, 33 are open to one side with respect to the radial direction relative to the axis, and the third elbow 35 is open to the opposite side.
• the first elbow 31 then forms an angle ⁇ ', measured as in Figure 2b between the radially outer end portion 34 and the outer portion 36b of the intermediate portion, between 5 and 15 degrees, preferably equal to 10 °.
• the second bend 33 forms an angle ⁇ ', measured between the radial direction and the inner portion 36a of the intermediate portion 36, between 10 and 40 degrees, preferably 30 degrees.
• the third bend 35 forms an angle ⁇ , measured between the two portions 36a, 36b of the intermediate portion 36, between 60 and 80 °, preferably equal to 70 °.
• the plate is shaped so that the radially outer end portion 34 always has a midpoint aligned with the radially inner end portion 32.
• the extension in the radial direction of portion 32 intersects the portion 34 at a point such that the length L 34 in the axial direction is distributed 47% upstream and 53% downstream.
• the plate 30 has, in the axial direction, two ends respectively corresponding to the first and third elbow 31, 35.
• the distance di measured in the axial direction, between the first bend 31 and the end portion radially inner 32, corresponds substantially to a quarter of the distance D, measured in the axial direction, between the first 31 and the third elbow 33. Therefore the distance d 2 , measured in the axial direction, between the radially inner end portion 32 and the third bend 35 corresponds to three quarters of the distance between the first 31 and the third bend.
• the di / D and d 2 / D ratios defined above have a margin of about 20%, ie 0.2 ⁇ di ⁇ 0.3 and 0.7 ⁇ d 2 / D ⁇ 0.8, given that
• This assembly comprises an exhaust casing 20, comprising a plurality of fixed blades mounted on a support ring 21.
• the housing further comprises a circumferential spoiler 22 extending upstream of the ring and blades relative to the air flow in the turbomachine.
• the assembly further comprises a movable blade 10, forming a rotor stage of the turbomachine.
• This blading comprises a plurality of blades mounted on a support ring January 1.
• This blading further comprises a set of sectored spoilers (a spoiler per blade) forming a spoiler 12 extending downstream of the ring and blades relative to the direction of the air flow in the turbomachine.
• the assembly also comprises an exhaust casing support 42.
• the exhaust casing comprises a fastening flange 23, through which the casing is mounted on the support 42 by bolting.
• the assembly comprises a plate 30, which is attached to the housing at the mounting flange.
• the plate is advantageously mounted by being clamped between the flange and the support 42.
• the height H (taken in the radial direction relative to the axis XX) of the plate is between 15 and 35% of the distance D x between the axis of revolution XX and the end portion radially outer of the plate.
• the sealing plate for sealing the vein the spoiler of the housing does not need to have a significant axial extension to be superimposed on the downstream spoiler of the rotor during operation thereof. Consequently, the upstream spoiler of the housing can have an axial extension reduced by up to 50% compared to the prior art.
• the first elbow 31 of the plate is angularly open downstream with respect to the air flow in the turbomachine, and the plate is dimensioned so that, in the radial direction, the upstream spoiler 22 of the casing 20 is located radially. internally relative to the radially outer end portion 34 of the plate 30, and advantageously facing the first bend in the axial direction. This allows the plate 30 to back towards the exhaust casing 20 in case of contact of the rotor stage, without coming into contact with the housing.
• the second elbow 33 is then angularly open upstream relative to the air flow.
• the radially outer end portion seals the vein of the rotor because, in operation, it is superimposed axially and circumferentially to a downstream rotor spoiler and the upstream rotor spoiler,
• the flexibility of the plate allows it to ensure a fuse role in case of overspeed of the rotor causing excessive movement of the latter.
• this bend is angularly open upstream relative to the flow, while the second bend 33 is open downstream.
• the third bend 35 is advantageously positioned, as in FIG. 3b, radially inwardly with respect to the upstream spoiler 22 of the exhaust casing 20, that is to say, with reference to FIG. 3b, under the spoiler (turned towards the axis XX) in a radial direction, and downstream of the spoiler 22 relative to the air flow.
• the third bend 35 stiffens the plate 30, which allows its own frequencies to be modified to deviate from the operating frequencies of the motor. This avoids excessive vibrations of the platen during operation of the turbomachine.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Supercharger (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Gasket Seals (AREA)

Applications Claiming Priority (2)

Publications (2)

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ID=51298826

Family Applications (1)

Country Status (8)

Families Citing this family (3)

Family Cites Families (20)

• 2014
  • 2014-05-27 FR FR1454802A patent/FR3021692B1/fr active Active
• 2015
  • 2015-05-26 US US15/313,521 patent/US10047621B2/en active Active
  • 2015-05-26 BR BR112016027482-2A patent/BR112016027482B1/pt active IP Right Grant
  • 2015-05-26 CN CN201580027804.3A patent/CN106460539B/zh active Active
  • 2015-05-26 RU RU2016151409A patent/RU2675165C2/ru active
  • 2015-05-26 CA CA2950263A patent/CA2950263C/fr active Active
  • 2015-05-26 EP EP15732804.8A patent/EP3149286B1/de active Active
  • 2015-05-26 WO PCT/FR2015/051386 patent/WO2015181489A1/fr active Application Filing

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