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
  • F01D9/02—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
  • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
• • 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
  • F01D25/246—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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/02—Blade-carrying members, e.g. rotors
  • F01D5/08—Heating, heat-insulating or cooling means
  • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
  • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
• • 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
• • 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
• • 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
  • F05D2250/12—Two-dimensional rectangular
• • 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
  • F05D2250/13—Two-dimensional trapezoidal
  • F05D2250/131—Two-dimensional trapezoidal polygonal
• • 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

Definitions

• the invention relates to an assembly for a turbomachine. More specifically, the invention relates to the architecture of a turbine and in particular the mounting bracket of a distributor in a high-pressure turbine.
• the published patent document FR 3 066 226 A1 discloses in its Figure 1 a high-pressure turbine distributor, mounted on an annular casing.
• the distributor comprises a platform supporting an annular row of fixed vanes.
• An annular row of pins (denoted 22) allows the circumferential and radial positioning of a flange of the platform to a flange of the housing.
• a stopper (denoted 21) completes the connection between the distributor and the housing, the stopper axially maintaining the flanges resting against each other.
• the stopper bears radially on a support ring (denoted 3).
• removing the distributor requires disassembly of the stopper and disassembling the stopper can only be done by removing the support ring, attached to the housing.
• the object of the invention is to provide a design for coupling the distributor and the high-pressure turbine housing which allows faster maintenance operations, and in particular aimed at eliminating the need to remove the support ring and of the crankcase.
• the invention relates to an assembly for a turbomachine, comprising: a turbine nozzle comprising an annular platform, an internal radial flange extending radially inward from the platform, and one or more blades extending radially towards the exterior from the platform; a housing comprising an outer radial flange; and a stopper ensuring axial retention of the outer radial flange in contact with the inner radial flange; remarkable in that the stopper is formed by a head and a body assembled in a removable manner to the head.
• the assembly can include one or more of the following technical characteristics, in any possible combination:
• the head respectively the body
• the body has an internal thread
• the body, respectively the head has a thread capable of cooperating with the internal thread.
• the body is assembled to the head by means of a bayonet mechanism.
• This type of non-permanent assembly allows rapid disassembly, without special tools.
• other types of clipping or interconnection are also possible;
• the body may have a portion that facilitates its gripping, such as a groove or a non-axisymmetric portion with a polygonal or fluted section, making it possible, using a tool, to separate the two parts of the stop;
• the head is T-shaped and comprises an internal portion with a polygonal section and an axisymmetric external portion.
• a shape allows disassembly or assembly of the body on the head blind, that is to say without having access to the head.
• a surface of the casing or of the support ring could, for example, serve as a stop in rotation when a side of the polygon of the head comes to rest on it.
• the polygonal section may have rounded vertices. These prevent any damage to the support ring or the housing when removing the body;
• the head passes through the casing.
• the head is housed in the housing without passing through it and is held there for example by welding or tight assembly;
• the stopper extends in the radial direction and pins extend axially, each of the pins passing through the housing flange and the distributor flange.
• turbomachine comprising a combustion chamber, the turbomachine being characterized in that it comprises a high-pressure turbine downstream of the combustion chamber, the turbine being equipped with an assembly according to one of the embodiments set out above.
• the invention finally relates to a method for maintaining a turbomachine, remarkable in that the turbomachine is according to the embodiment of the previous paragraph and in that the method comprises, in this order: a step of removing the body of the stopper; and a step of removing the distributor, during which the head of the stopper remains engaged in the casing and the support ring remains fixed to the casing, the method further preferably comprising a step of reassembling the distributor and then a step of fixing the body. of the stopper on the stopper head.
• the measures of the invention are advantageous in that only part of the stop must be detached from the housing to allow the distributor to be dismantled. This preserves the assembly of the housing and the support ring.
• the assembly of the two parts of the stopper can be done by simple means of the quick fixing type.
• Figure 1 describes a turbomachine according to the invention
• Figure 2 shows a partial sectional view of a known turbine
• FIG. 3 illustrates a view in partial section of a turbine according to the invention
• FIG. 4 shows an embodiment of the stop according to the invention
• FIG. 5 illustrates a detail of the stop, seen in the direction V: V defined in FIG. 4.
• the terms “internal” (or “interior”) and “external” (or “exterior”) refer to a positioning relative to the axis of rotation of an axial turbomachine which is also the axis of rotation of the turbine.
• the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
• the radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the flow in the turbomachine.
• integral is understood as integral in rotation, and in particular rigidly linked.
• distributedor is meant a set of angular sectors circumferentially adjacent and forming an annular row of fixed blades, each of the sectors possibly comprising at least one, for example two or three fixed blades.
• FIG. 1 schematically represents an axial turbomachine 2.
• the turbojet 2 comprises a low-pressure compressor 4 and a high-pressure compressor 6, a combustion chamber 8 and one or more turbines 9.
• the mechanical power of the turbine 9 transmitted to rotor 12 sets in motion the two compressors 4 and 6.
• the latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate a flow of air and to gradually compress the latter up to the entry of the combustion chambers 8.
• a fan 16 is coupled to the rotor 12 and generates an air flow which divides into a primary flow 18 and a secondary flow 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet.
• Reduction means such as an epicyclic reduction gear 22, can reduce the speed of rotation of the fan and / or of the low-pressure compressor relative to the associated turbine.
• the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
• the turbine or turbines 9 comprise an alternation of rotating blades and fixed blades.
• the terminology of "distributor” will be used in the present application to refer to a set of fixed vanes and their support platform.
• the platform can be an entire ring or a circumferential segment (partial ring).
• the first distributor downstream of the combustion chambers 8 is indicated by the number 10 in Figure 1. It is followed by a 1 1 wheel.
• FIG. 2 is a sectional view partially showing a stage of the turbine 9 according to a known construction.
• the stage of the turbine 9 is composed of a distributor 10 and a wheel 1 1.
• the wheel 1 1 comprises an annular row of movable vanes 1 10 each mounted in a cell 1 1 1 of a disc 1 12.
• the distributor 10 comprises an annular row of fixed vanes 101 connected by their internal ends (foot) to a lower platform 102, annular.
• the platform 102 has a flange 103 extending radially inward. This flange 103 makes it possible to make the blades 101 integral with the annular casing 30, fixed.
• the vanes 101, 110 extend radially into the hot, high pressure air stream 18.
• the housing 30 includes an internal spindle 301, an external spindle 302, an external radial flange 303 and an internal radial flange 304.
• the spindles 301, 302 are coaxial along axis 14.
• the outer radial flange 303 is in axially contact with the inner flange 103, the flange 303 being downstream of the flange 103.
• the flanges 103, 303 are positioned and held radially and circumferentially between them by means of pins 32, distributed angularly around of the axis 14.
• the pins 32 extend axially through the flanges 103, 303.
• the pin 32 visible in the section of FIG. 2 extends along an axis denoted A, parallel to the axis 14.
• a stop 34 The axial retention of the flanges 103, 303 against one another is provided by a stop 34.
• This stop extends radially along an axis denoted B.
• the axes A and B are shown in FIG. 2 to facilitate understanding of the invention but these axes are not in the same plane, the stop 34 being circumferentially offset with respect to the pins 32.
• the stop 34 extends through an orifice 305 made in the housing 30.
• a seal 36 housed in the flange 303 prevents air leakage from the vein 18 inwards.
• the stop 34 is radially supported by a support ring 40.
• the support ring 40 is assembled to the casing 30 at the level of its internal flange 304 by screws (not shown) extending along the axis C.
• the ring of support 40 is also radially supported by the internal stub 301 of the housing 30.
• the support ring 40 may bear on a lip 306 of the housing 30.
• the support ring 40 is provided with a layer of abradable 50 to ensure a seal by cooperating with wipers 62 of a rotating flange 60, integral with the wheel January 1.
• Figure 2 illustrates the assembly in its assembled condition.
• the stopper 34 In order to remove the distributor 10, it is necessary to first remove the stopper 34.
• the stopper 34 can only be removed from the housing 30 after disassembly of the support ring 40.
• the objective of the invention is to reduce the number of disassembly steps required to remove the distributor.
• Figure 3 shows a partial sectional view of an assembly according to the invention. Parts similar to the known assembly shown in Figure 2 retain their reference numbers. The invention differs essentially from the known assembly in the design of the stop.
• the stop is referenced 70.
• the latter consists of a head 72 and a body 78.
• the head 72 comprises an internal portion 74 and an external portion 76 which passes through the orifice 305 of the housing 30.
• the internal portion 74 has a dimension (diameter if it is a cylinder or diagonal if it is a polygon) which is greater than the diameter of the orifice 305 so that the internal portion 74 does not penetrate into it. orifice 305.
• the head 72 is supported via its internal portion 74 by the support ring 40, fixed to the housing 30.
• the head 72 is removably assembled to the body 78.
• the head 72 and the body 78 are reversibly separable from each other.
• the head does not pass through the casing. She is received in accommodation provided for this purpose.
• the head is welded to the housing or mounted tight in its housing, so as to remain integral with the housing when the body is dismantled.
• the body 78 is able to be in contact with the flange 103 to prevent the axial separation of the flanges 103, 303.
• the body radially overlaps the internal flange 103.
• radial overlap is meant that geometric points of the body 78 have radial coordinates identical to those of geometric points of the flange 103.
• the head 72 is at a radial distance from the internal flange 103 in order to allow, once the body 78 has been removed, the axial sliding of the distributor 10 upstream (towards the left in figure 3).
• FIG. 4 illustrates an exemplary embodiment of the stop 70.
• the head 72 comprises in this example an internal thread 761 in which a threaded portion 781 of the body 78 engages.
• the body 78 may have a portion facilitating its gripping at unscrewing purposes, such as a portion with a square section 782.
• body 78 and outer portion 76 of head 72 have generally axisymmetric shapes around the B axis.
• FIG. 4 also partially shows the lip 306 of the housing which is close to the internal portion 74.
• FIG. 5 illustrates the internal portion 74 seen in the direction V: V defined in FIG. 4.
• the substantially polygonal section 741 of the internal portion 74 which in this example is a square.
• the square 741 may have rounded corners 742.
• the dotted line shows a position of the internal portion 74 in contact with the lip 306.
• the stop surface is a surface of the lip 306.
• the rotation of the internal portion 74 can be stopped by the internal flange 304 of the housing or by a surface of the support ring 40.
• the contact surface between the support ring 40 and the stop 70 can also stop the head 72 in rotation: for example, the support ring 40 can be provided with splines and the internal portion 74 can be fitted with grooves (radial with respect to the axis B) which can engage in the grooves.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Applications Claiming Priority (2)

Publications (2)

Family

ID=67384146

Family Applications (1)

Country Status (5)

Families Citing this family (1)

Family Cites Families (18)

• 2019
  • 2019-05-21 FR FR1905298A patent/FR3096397B1/fr active Active
• 2020
  • 2020-04-27 US US17/604,519 patent/US11603775B2/en active Active
  • 2020-04-27 CN CN202080034973.0A patent/CN113811669A/zh active Pending
  • 2020-04-27 EP EP20720100.5A patent/EP3973146B1/de active Active
  • 2020-04-27 WO PCT/EP2020/061624 patent/WO2020233947A1/fr unknown

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