EP2050930A1 - Gekühlte Turbomaschinenschaufel - Google Patents

Gekühlte Turbomaschinenschaufel Download PDF

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Publication number
EP2050930A1
EP2050930A1 EP08167046A EP08167046A EP2050930A1 EP 2050930 A1 EP2050930 A1 EP 2050930A1 EP 08167046 A EP08167046 A EP 08167046A EP 08167046 A EP08167046 A EP 08167046A EP 2050930 A1 EP2050930 A1 EP 2050930A1
Authority
EP
European Patent Office
Prior art keywords
blade
spacers
opening
cavity
jacket
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.)
Granted
Application number
EP08167046A
Other languages
English (en)
French (fr)
Other versions
EP2050930B1 (de
Inventor
Jean-Michel Bernard Guimbard
Philippe Jean-Pierre Pabion
Jean-Luc Soupizon
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
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP2050930A1 publication Critical patent/EP2050930A1/de
Application granted granted Critical
Publication of EP2050930B1 publication Critical patent/EP2050930B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage

Definitions

  • the present invention relates to the field of turbomachines including gas turbine engines and is more particularly aimed at cooled distributor vanes.
  • a gas turbine engine such as the turbojet turbofan engine 70 before the figure 7
  • the incoming air is compressed in a compressor before being mixed with a fuel and burned in a combustion chamber.
  • the hot gases produced in the chamber drive the downstream turbine (s) and are ejected.
  • the various stages of turbines 72 are separated by distributors which provide a guide of the gas for a suitable orientation at the turbine inlet. Because of the temperature of the gases, the blades, in particular those forming the inlet distributor of the high pressure turbine and receiving the gas directly from the combustion chamber, are subjected to very severe operating conditions.
  • Cooling means are provided in the walls which are in contact with the hot gases. The cooling is done by forced convection or by air impact on the inner faces of the blade walls.
  • the figure 1 represents, in longitudinal section, a vane 1 forming a dispenser of the prior art in which the cooling is provided by air impingement from a tubular insert forming a multiperforated internal longitudinal liner 4, housed in the cavity 6 of the vane.
  • the blade of the blade 1 extends radially between two platforms, a radially inner platform 3 and a radially outer platform 2.
  • the two platforms define the annular vein 5 for circulating the engine gases.
  • the vein is subdivided circumferentially by the blade blades 1.
  • the two platforms and the blade form a single piece from the foundry.
  • the liner 4 is made by sheet metal forming and includes dimples 41 projecting on its outer face.
  • the bosses formed by stamping are of determined height and form spacers between the outer face of the jacket and the inner face of the cavity 6. They are distributed between the ends of the jacket. Here there are two dimples near each end on each side, intrados side and extrados side respectively.
  • the figure 2 shows in longitudinal section parallel to the axis of the blade, the arrangement of the bosses 41 on the sleeve. They keep the jacket away from the walls of the blade to allow both the impact of the air flow on the wall and the flow of air in the space thus formed.
  • An opening 7 in the outer platform feeds the jacket 4 in cooling air taken from the compressor, for example.
  • the blade is opened, at 9 and 10, at the two longitudinal ends of the blade, at the level of its outer platform 2 and its inner platform 3 respectively.
  • the shirt which has been previously shaped is slid into the cavity 6 of the blade through the opening 9.
  • the jacket is then secured to the blade by welding or brazing along its edge in contact with the wall of the opening 9.
  • the opposite part of the shirt is guided in the interior opening 10 of the dawn which forms a slide to allow relative movements between the dawn and the shirt.
  • the turbomachine cooled blade comprising a platform and a blade, and comprising a cavity along the blade and the platform with a first opening at one end and a second opening at the other end, a tubular jacket being housed in the cavity with a first end in the first opening and a second end in the second opening, first struts on the side of the first end and second struts on the side of the second end the liner providing a space between the outer face of the liner and the wall of the cavity, the blade being arranged so that the liner is introduced into the cavity through the first opening, is characterized in that the first spacers are secured of the jacket and the second spacers are integral with the wall of the cavity along the blade.
  • the solution of the invention allows with minor modifications both on the metal jacket and on the inner face of the blade to reserve a greater lateral play between the insert and the wall of the cavity. There is therefore a greater freedom in the choice of the geometry of the blade from an aerodynamic point of view.
  • the first spacers are arranged in a direction forming an angle with the rope of the blade.
  • the angle is zero in particular.
  • the liner is formed of a metal sheet, the first spacers being bosses obtained by deformation of the sheet.
  • the bosses are for example domed.
  • the first spacers are advantageously formed in the half of the liner located on the side of the first end, thus leaving a maximum lateral displacement capacity, taking into account the congestion, as the first spacers are not engaged in the cavity.
  • the second spacers form individual bosses. They are aligned preferably parallel to the rope.
  • the second spacers have an elongate shape parallel to a rope of the blade. More particularly the second spacers form a continuous rail, they thus provide an additional sealing function limiting air leakage from inside the jacket by the space left free between the jacket and the slide.
  • the solution of the invention is of particular interest when the liner is perforated for air impingement cooling of the walls of the blade.
  • the first opening is either the outer side of the gas vein or the inner side of the gas stream.
  • the invention further relates to a method of assembling the blade according to which the jacket is placed in the cavity by introducing it through its second end through the first opening.
  • the blade 20 profile of distributor of the figure 3 has a leading edge 21 and a trailing edge 28 whose curvatures vary between the foot of the blade and its top.
  • the longitudinal guidelines 23 and 24 for example or 26 and 27 also see their curvature evolve. It is understood that a tubular inner liner to the volume defined by this profile can not be moved along the longitudinal direction without the envelopes interfering in their translation. Any interference corresponds to an impossibility of movement. In this case assembly or disassembly becomes impossible.
  • the figure 3 illustrates this problem; the sliding of the jacket in the cavity can be achieved only in the case where the blade has the same orientation of curvature between the leading edge and the trailing edge.
  • the envelope of the shirt is defined by the bosses that project from its surface. Insofar as these bosses have a spacer function and maintain a well-defined air gap, their envelope is very close to the geometrical envelope of the inner surface of the wall of the blade. Any variation in curvature is therefore likely to prevent their relative displacement.
  • the solution of the invention consisted in modifying the distribution of the spacers between the jacket and the blade.
  • the blade 20 extends between an inner platform 23 and an outer platform 22.
  • the two platforms are the boundaries of the annular vein traveled by the engine gases.
  • the jacket 24 inside the cavity 26 of the blade is welded or soldered by its first end 243 to the wall of the first opening 29, this opening 29 is made in the wall of the outer platform 22.
  • the other end 244 of the jacket is engaged in the second opening 30 formed in the inner platform 23. Being secured to the blade by one end, 243 and free at its other end, 244, the two parts can expand. independently of one another.
  • the liner comprises on the side of its first end 243, bosses formed by deformation of the sheet. These bosses form spacers maintaining the wall of the liner away from the wall of the cavity. They are for example aligned parallel to the direction of the rope of dawn.
  • the shirt does not include other bosses as we see well on the figure 4 .
  • Projections 25 formed on the inner face of the wall of the blade 20 form spacers and keep the jacket away from the wall of the cavity. These projections are located near the second opening 30. They are made with dawn, by foundry. Preferably they form spacers of the same height as the bosses 241 so that the circulation space of the cooling air is the same between the foot of the blade and its top. However, the solution of the invention allows a different arrangement of the spacers. These projections can be parallel to a rope of dawn. Advantageously, they are elongated in shape.
  • the cooling air is introduced through the first end 243 into the tubular channel of the jacket; a part of this air passes through the jacket through the perforations 242 and divides into fine jets which cool the wall of the blade 20.
  • the air then circulates in the space between the jacket and the wall to be evacuated towards the trailing edge . Another portion of the air flows through the second end and is guided to another cooling circuit.
  • the figure 5 shows the interest of the solution at the time of assembly.
  • the liner is introduced through its second end 244 into the cavity 26 through the first opening 29 of the blade.
  • the shirt is at this time close to its engagement in the second opening. His move is almost complete.
  • the figure 6 shows an alternative embodiment. Only the part of the blade 40 is shown near the second opening 41.
  • the liner 34 is engaged by its second end 344 in the second opening 41 of the blade.
  • the bosses have been replaced by a rail 35 running around the entire periphery, preferably parallel to the plane of the opening 41. Its function is to form a baffle limiting the flow of air from one side to the other of the rail.
  • the advantage of this variant comes from the air leaks that occur between the jacket 344 and the wall of the blade in the slide of the opening 41. Indeed, in order not to prevent the free sliding of the shirt in the slide resulting from the dimensional variations between them, we must maintain a certain clearance which is at the origin of the air leaks. Part F of this air is diverted from the direction D provided. The passage of this air in the space between the jacket and the blade is not desired because it is lost without having participated in the cooling.
  • the arrangement of such a baffle thus contributes to containing the air inside the liner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08167046A 2007-10-19 2008-10-20 Gekühlte Turbomaschinenschaufel Active EP2050930B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0707342A FR2922597B1 (fr) 2007-10-19 2007-10-19 Aube refroidie de turbomachine

Publications (2)

Publication Number Publication Date
EP2050930A1 true EP2050930A1 (de) 2009-04-22
EP2050930B1 EP2050930B1 (de) 2011-08-31

Family

ID=39717683

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08167046A Active EP2050930B1 (de) 2007-10-19 2008-10-20 Gekühlte Turbomaschinenschaufel

Country Status (6)

Country Link
US (1) US8162594B2 (de)
EP (1) EP2050930B1 (de)
JP (1) JP5390163B2 (de)
CA (1) CA2641438C (de)
FR (1) FR2922597B1 (de)
RU (1) RU2489573C2 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2392775A1 (de) 2010-06-07 2011-12-07 Siemens Aktiengesellschaft Rotationsschaufel zur Verwendung in einem Fluidstrom einer Turbine und zugehörige Turbine
EP2949871B1 (de) * 2014-05-07 2017-03-01 United Technologies Corporation Variables leitschaufelsegment
US9957820B2 (en) * 2015-06-02 2018-05-01 United Technologies Corporation Heat shield for a vane assembly of a gas turbine engine
US9982543B2 (en) * 2015-08-05 2018-05-29 United Technologies Corporation Partial cavity baffles for airfoils in gas turbine engines
CN113236371B (zh) * 2021-06-04 2023-01-17 中国航发沈阳发动机研究所 一种叶片冷气导管

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR891635A (fr) * 1942-02-04 1944-03-13 Bmw Flugmotorenbau Gmbh Aube de turbine à refroidissement interne
BE685320A (de) * 1965-05-03 1967-01-16
FR2117034A5 (de) * 1970-12-11 1972-07-21 Gen Electric
FR2212485A1 (de) * 1973-01-02 1974-07-26 Gen Electric
FR2286277A1 (fr) * 1974-09-25 1976-04-23 Gen Electric Piece a inserer pour aube de turbomachine refroidie par air et aube ainsi obtenue
US4086757A (en) * 1976-10-06 1978-05-02 Caterpillar Tractor Co. Gas turbine cooling system
EP1508670A2 (de) 2003-08-12 2005-02-23 Snecma Moteurs Gekühlte Schaufel einer Gasturbine
EP1783326A1 (de) * 2005-11-07 2007-05-09 Snecma Kühlungsanordnung in einer Turbinenschaufel, Turbinenschaufel, Turbine und Flugantrieb damit ausgestattet

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3767322A (en) * 1971-07-30 1973-10-23 Westinghouse Electric Corp Internal cooling for turbine vanes
GB1550368A (en) * 1975-07-16 1979-08-15 Rolls Royce Laminated materials
JPS5231209A (en) * 1975-09-03 1977-03-09 Toshiba Corp Turbine blade
US4077205A (en) * 1975-12-05 1978-03-07 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
US4288201A (en) * 1979-09-14 1981-09-08 United Technologies Corporation Vane cooling structure
DE3629910A1 (de) * 1986-09-03 1988-03-17 Mtu Muenchen Gmbh Metallisches hohlbauteil mit einem metallischen einsatz, insbesondere turbinenschaufel mit kuehleinsatz
US5090866A (en) * 1990-08-27 1992-02-25 United Technologies Corporation High temperature leading edge vane insert
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
US6237344B1 (en) * 1998-07-20 2001-05-29 General Electric Company Dimpled impingement baffle
GB2365932B (en) * 2000-08-18 2004-05-05 Rolls Royce Plc Vane assembly
JP4087586B2 (ja) * 2001-09-13 2008-05-21 株式会社日立製作所 ガスタービン及びその静翼
US7008185B2 (en) * 2003-02-27 2006-03-07 General Electric Company Gas turbine engine turbine nozzle bifurcated impingement baffle
RU2283432C2 (ru) * 2004-11-23 2006-09-10 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") Охлаждаемая лопатка турбомашины

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR891635A (fr) * 1942-02-04 1944-03-13 Bmw Flugmotorenbau Gmbh Aube de turbine à refroidissement interne
BE685320A (de) * 1965-05-03 1967-01-16
FR2117034A5 (de) * 1970-12-11 1972-07-21 Gen Electric
FR2212485A1 (de) * 1973-01-02 1974-07-26 Gen Electric
FR2286277A1 (fr) * 1974-09-25 1976-04-23 Gen Electric Piece a inserer pour aube de turbomachine refroidie par air et aube ainsi obtenue
US4086757A (en) * 1976-10-06 1978-05-02 Caterpillar Tractor Co. Gas turbine cooling system
EP1508670A2 (de) 2003-08-12 2005-02-23 Snecma Moteurs Gekühlte Schaufel einer Gasturbine
EP1783326A1 (de) * 2005-11-07 2007-05-09 Snecma Kühlungsanordnung in einer Turbinenschaufel, Turbinenschaufel, Turbine und Flugantrieb damit ausgestattet

Also Published As

Publication number Publication date
RU2489573C2 (ru) 2013-08-10
FR2922597A1 (fr) 2009-04-24
CA2641438A1 (fr) 2009-04-19
RU2008141334A (ru) 2010-04-27
CA2641438C (fr) 2015-09-29
EP2050930B1 (de) 2011-08-31
US8162594B2 (en) 2012-04-24
JP5390163B2 (ja) 2014-01-15
JP2009103127A (ja) 2009-05-14
US20090104018A1 (en) 2009-04-23
FR2922597B1 (fr) 2012-11-16

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