EP0083896B1 - Dispositif de refroidissement des talons d'aubes mobiles d'une turbine - Google Patents

Dispositif de refroidissement des talons d'aubes mobiles d'une turbine Download PDF

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Publication number
EP0083896B1
EP0083896B1 EP82402404A EP82402404A EP0083896B1 EP 0083896 B1 EP0083896 B1 EP 0083896B1 EP 82402404 A EP82402404 A EP 82402404A EP 82402404 A EP82402404 A EP 82402404A EP 0083896 B1 EP0083896 B1 EP 0083896B1
Authority
EP
European Patent Office
Prior art keywords
cooling
turbine
rotor blades
air
platforms
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.)
Expired
Application number
EP82402404A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0083896A1 (fr
Inventor
Jean Georges Bouiller
Jean-Claude Lucien Delonge
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0083896A1 publication Critical patent/EP0083896A1/fr
Application granted granted Critical
Publication of EP0083896B1 publication Critical patent/EP0083896B1/fr
Expired 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades cooled platforms
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the present invention relates to a turbomachine turbine fitted with a device for cooling the heels of movable blades.
  • the constant research related to the improvement of turbomachines aims in particular to increase the performances obtained while respecting the multiple constraints imposed as much by the possibilities of industrial implementation as by the conditions of exploitation of the materials.
  • the pursuit of these objectives leads to taking into account two conditions: on the one hand, increasing the operating temperatures and on the other hand, reducing or avoiding the losses affecting the main circulation vein gases.
  • U.S. Patent 3,034,298 describes a turbine cooling system.
  • the cooling air from a manifold 76 is directed by holes 168, on the one hand, in the distributor blades 65 and on the other hand, on the turbine ring 102 that the air passes through to be discharged radially into the main vein.
  • An additional cooling circuit is provided for the radially internal parts.
  • French patent 1,548,541 relates to a method and devices for cooling gas turbines.
  • the system described associates the cooling of a wheel disc with the supply by a tube of an internal cavity from which the cooling air is directed on the region of the base of the blades or on a hoop or rim surrounding the blade heads.
  • Patent of the United Kingdom of Great Britain 1,519,449 relates to a turbomachine into which air for cooling the turbine is supplied. in chambers in the turbine ring. This air is introduced into the main gas stream by passages through a complementary blade orienting this air in the direction of the flow obtained at the outlet of the main distributor. The exit of this air into the vein retains a centripetal radial component.
  • GB-A 1524956 proposes a solution for cooling a fixed turbine ring by air inlets making impact from pierced tubes and placed in a chamber, this air flowing in the vein forming a film cooling on the internal diameter of the ring.
  • the object of the present invention is therefore to define a turbine provided with a device for cooling the peripheral heels of movable blades in which, according to techniques known from the state of the art, an external enclosure is provided at the inside the outer casing of the turbine.
  • This enclosure is supplied with air and a first direct circuit by passages formed from said enclosure, directs the air on the peripheral heels of the moving blades of the turbine rotor so as to ensure the cooling of said blade heels from their leading edge is located on the upstream side with respect to the direction of gas flow in the main vein.
  • This turbine is characterized in that said cooling passages are arranged parallel to the axis of the turbine and at a circumferential inclination so as to orient the impacts on the leading edge of the heels of movable blades at the optimum angle and to obtain cooling air inlets parallel to the flow or in slight divergence, without centripetal radial component and in that said external enclosure also supplies cooling air to the fixed blades
  • said cooling air passages can be formed by multiple holes machined in the heels of the fixed distributor vanes on the downstream side according to a multi-hole arrangement. A remarkable film cooling is thus obtained by its efficiency for said heels of movable blades, from the capacity provided at the head of the fixed distributor blades. By this means, a constant ejection section is obtained.
  • the choice of the arrangement and the diameter of these holes makes it possible to obtain an accurate calibration of the cooling air flow.
  • said cooling air passages are made through an axial annular space formed between two parts of a flange downstream of the distributor and opening at its radially internal end by a multitude of millings made in the end of the downstream part of said flange creating orifices between said flange and an associated connecting square.
  • film cooling is also obtained from multi-holes having the same advantages of efficiency and precise calibration of the air flow with a constant ejection section.
  • the device according to the invention is advantageously complete by placing associated means ensuring sealing between the external enclosure from which the cooling air is taken and the main gas circulation stream.
  • Said sealing means in a first advantageous embodiment, consist of a seal formed of elastic blades in sectors, one end of which is fixed to the downstream flange of the distributor and the other end of which bears on the ring. turbine.
  • This flexible seal makes it possible to absorb dimensional differences of various origins, manufacturing tolerances, deformations, differential thermal expansions, between the distributor and the turbine ring.
  • any risk of interference between distributor and ring is avoided and likewise, this solution does not affect the dismantling of the turbine modules.
  • the seal consists of elastic tabs, one end of which is fixed to a radially external part of the downstream flange of the distributor. These tabs, at the other end, are welded to an annular flange which is supported on a front surface of the turbine ring and on an axial surface of the downstream part of the distributor blade platform.
  • FIG. 1 is shown in axial section a portion of a turbomachine and more specifically a portion of high pressure turbine 1 in a first embodiment of the invention.
  • This turbine 1 is bounded by an outer casing 2 carrying a radial flange 3 on which is bolted a support 4 which carries a turbine ring 5 delimiting the external contour of circulation of the main gas stream.
  • a perforated annular sheet 8 provides outside the turbine ring 5 a cooling chamber 7.
  • the turbine ring 5 is internally lined with a seal and wear coating 8 corresponding to the heel 9 of the blades mobile 10 of a first turbine rotor stage.
  • Inside the turbine casing 2 there is also fixed to said casing by a connection, not shown in the drawing, a casing 11 for dispenser support.
  • An upstream intermediate support 12 connects to a flange 13 of the casing 11 and a downstream flange 14 of the casing 11 carry the distributor stage, the platforms 15 of fixed vanes 16 of which are linked to each of them.
  • An outer enclosure 17 is formed between the outer casing 2 of the turbine, on the one hand, and, on the other hand, the turbine ring 5 and the distributor casing 11.
  • a closure plate 18 resting on the upstream part 19 and on the downstream part 20 of the platform 15 of the distributor vanes 18 provides a capacity 21 at the top of the distributor vanes 18.
  • the distributor housing 11, on the one hand, and the closure plate 18, on the other hand, have openings respectively 22 and 23 in which, via cylindrical sleeves, respectively 24 and 25 are mounted coils 26 which connect the external enclosure 17 and the capacity 21 formed at the head of the distributor vanes 18.
  • These coils 28 have at each end, respectively 27 and 28, a ball-shaped shape adapted to the cylindrical bore of the connecting sleeves, respectively 24 and 25.
  • the edge 30 of the heel 9 has, with respect to the extension of the heel itself, a slightly raised profile whose interest will appear later in the description of the operation.
  • the holes 29 in the platforms 15 of the distributor blades 16 are oblique holes, circumferentially inclined, at an a priori angle different from that of the trailing edge 31 of the distributor blades 16 and whose the optimal value is determined from criteria arising from the operation of the device as will be described later.
  • a seal 32 Between the downstream flange 14 of the distributor housing 11 and the annular sheet metal 6 of the turbine ring 5 is placed a seal 32.
  • This seal 32 consists of elastic strips 33 in sectors, for example twelve in number.
  • One end 34 of the blades 33 is bolted to the downstream flange 14 of the distributor housing 11 and the other end 35 of the blades 33 is in elastic support on the annular sheet metal 6 of the turbine ring 5.
  • FIG 3 there is shown, in a view similar to that of Figure 1 and in a second mode of embodiment of the invention, a part of a turbomachine in axial section and more precisely a part of a high-pressure turbine.
  • the downstream flange 14 of the distributor housing 11 is made up of two annular parts, an upstream part 14a and a downstream part 14b.
  • An annular space 36 is formed between these two parts 14a and 14b.
  • the connection between the platforms 15 of the distributor vanes 16 and the flange 14 is made by means of a bracket 37.
  • the upstream flange part 14a is fixed to the branch 37a of the bracket 37 in the radial position and the radially internal end 38 of the downstream flange portion 14b is supported on the branch 37b of the bracket 37 in the axial position.
  • the radially internal face 38a of the end 38 of the downstream flange portion 14b bearing on the branch 37b of the bracket 37 comprises a series of longitudinal millings 39 starting from the radially internal end of the annular space 36 and opening out in line with the leading edge 30 of the heel 9 of the movable blades 10. In a manner similar to the first embodiment and for the same purpose, these millings 39 have a circumferential inclination.
  • FIG 4 there is shown a variant according to the invention for the seal 32 placed between the turbine ring 5 and the flange 14 of the turbine distributor support casing.
  • This seal 32 consists of elastic legs 40 in the shape of a butt which are for example twelve in number.
  • One end 41 of the legs 40 is bolted to the downstream flange 14 of the distributor housing.
  • the other end 42 is welded to an annular flange 42a which is, on the one hand, in front support on a radial upstream bearing 43 of the turbine ring 5 and, on the other hand, in radial support on an axial bearing 44 of the downstream part 20 of the platform 15 of the distributor blade 16.
  • the cooling of the heels of movable blades obtained by the device according to the invention which has just been described is combined with an overall solution for cooling the hot parts of a turbine combined with obtaining minimum operating clearances between fixed parts and moving parts taking into account the repercussions of expansion, in particular of thermal origin.
  • the external turbine enclosure 17 is supplied with cooling air by any known means and according to any method adapted to the configuration and to the particular operating conditions of the turbomachine considered. These means have not been shown in the drawings and will not, like the process, be described in more detail.
  • the cooling air through the multi-perforations of the annular sheet metal 6 cools in the form of impacts the turbine ring 5, the air jets passing through the cooling chamber 7.
  • the cooling air, from the enclosure 17 and through the swiveling coils 26 also feeds the capacity 21 at the head of the distributor blades 16.
  • a fraction of the air, from said capacity 21, is used for cooling the distributor vanes 16 in which the air circulates in suitable channels.
  • Another fraction of the air escapes from the capacity 21 through the holes 29 in the downstream part 20 of the platform 15 of the distributor blades 16.
  • the air inlets passing through the multi-hole system thus formed create a film on the leading edge 30 of the heels 9 of movable blades 10 of the turbine.
  • the calibration of the holes 29 allows precise control of the cooling air flow intended for the heels 9 of the movable blades 10 and the optimum value given to the circumferential angle of inclination of these holes 29 makes it possible to obtain the best efficiency of the blade stub cooling. This value is also chosen so as to avoid any disturbance created by the air jets in the vein.
  • the raised profile given to the leading edge 30 of the blade heel 9 contributes to the efficiency of the cooling obtained.
  • a constant ejection section of the cooling air is also obtained by this means according to the invention. It will be noted that the cooling of the blade heels obtained has a particularly advantageous application for high-performance equipment, such as certain turbojets, in which the rotor blades used are of the cavity type and also have their own cooling mode, by example, with emission on the blade.
  • the cooling air from the external turbine enclosure 17, enters the annular space 36 formed between the upstream 14a and downstream 14b parts of the downstream flange of the distributor housing 11. Then the air escapes through the millings 39 located at the radially internal end, and these air inlets create a film on the leading edge 30 of the heels 9 of moving blades 10 of the turbine.
  • the other operating conditions are similar to those which have been described for the first embodiment and similar advantageous results are also obtained.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP82402404A 1982-01-07 1982-12-31 Dispositif de refroidissement des talons d'aubes mobiles d'une turbine Expired EP0083896B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8200121 1982-01-07
FR8200121A FR2519374B1 (fr) 1982-01-07 1982-01-07 Dispositif de refroidissement des talons d'aubes mobiles d'une turbine

Publications (2)

Publication Number Publication Date
EP0083896A1 EP0083896A1 (fr) 1983-07-20
EP0083896B1 true EP0083896B1 (fr) 1986-02-26

Family

ID=9269753

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82402404A Expired EP0083896B1 (fr) 1982-01-07 1982-12-31 Dispositif de refroidissement des talons d'aubes mobiles d'une turbine

Country Status (5)

Country Link
US (1) US4522557A (enrdf_load_stackoverflow)
EP (1) EP0083896B1 (enrdf_load_stackoverflow)
JP (1) JPS58128401A (enrdf_load_stackoverflow)
DE (1) DE3269538D1 (enrdf_load_stackoverflow)
FR (1) FR2519374B1 (enrdf_load_stackoverflow)

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Also Published As

Publication number Publication date
DE3269538D1 (en) 1986-04-03
JPH0115683B2 (enrdf_load_stackoverflow) 1989-03-20
US4522557A (en) 1985-06-11
FR2519374B1 (fr) 1986-01-24
EP0083896A1 (fr) 1983-07-20
FR2519374A1 (fr) 1983-07-08
JPS58128401A (ja) 1983-08-01

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