EP0887515B1 - Aubage refroidi par rampe hélicoidale, par impact en cascade et par système à pontets dans une double peau - Google Patents

Aubage refroidi par rampe hélicoidale, par impact en cascade et par système à pontets dans une double peau Download PDF

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Publication number
EP0887515B1
EP0887515B1 EP98401558A EP98401558A EP0887515B1 EP 0887515 B1 EP0887515 B1 EP 0887515B1 EP 98401558 A EP98401558 A EP 98401558A EP 98401558 A EP98401558 A EP 98401558A EP 0887515 B1 EP0887515 B1 EP 0887515B1
Authority
EP
European Patent Office
Prior art keywords
blade
cavity
air
upstream
cooling
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 - Lifetime
Application number
EP98401558A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0887515A1 (fr
Inventor
Yves Maurice Bailly
Xavier Gérard André Coudray
Mischael François Louis Derrien
Jean-Michel Roger Fougeres
Philippe Christian Pellier
Jean-Claude Christian Taillant
Thierry Henri Marcel Tassin
Christophe Bernard Texier
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 Moteurs SA
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 Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP0887515A1 publication Critical patent/EP0887515A1/fr
Application granted granted Critical
Publication of EP0887515B1 publication Critical patent/EP0887515B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/14—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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical

Definitions

  • the invention relates to the blades of high pressure turbines turbomachinery.
  • the fixed and moving blades of high pressure turbines are subject to the high temperatures of the combustion gases of the combustion chamber. Also the blades of these blades are equipped with cooling devices supplied with air cooling taken from the high pressure compressor. This cooling air passes through circuits provided inside from dawn, then is discharged into the vein of hot gases flowing between the blades.
  • the cooling air enters the blades by the blade root, but in the fixed blades, the air of cooling can be introduced by a fixed vane base, either at the foot of dawn is at the head of dawn, the foot of dawn being the end of the blade closest to the axis of rotation of the turbine.
  • US-A-4 992 026 discloses a turbine blade comprising a hollow aerodynamic wall which extends radially between a foot blade and a blade head and which has a leading edge and an edge leakage, separated from each other and connected by a concave side wall or lower surface and a convex or upper side wall and comprising in addition to a cooling device provided inside said blade, supplied with cooling air from the blade root and intended for direct the cooling air against the interior surfaces of said side walls.
  • this blade comprises two radial partitions which connect said concave and convex side walls and which separate the interior of said blade into an upstream cavity located near the leading edge, a middle cavity located between said radial partitions and a downstream cavity located on the trailing edge side, the upstream cavity and the middle cavity are supplied with air by an inlet provided at the root of the blade, this air then being evacuated from said cavities by orifices provided at the head of the blade, while the downstream cavity is supplied with air by a separate inlet provided at the foot of the blade, this air then being evacuated by a plurality of slots formed in the trailing edge.
  • the internal wall of the upstream cavity comprises disruptors.
  • These disruptors can consist of ribs, spikes or bridges connecting the inner wall of the blade to the soul of the helical ramp.
  • the jacket of the middle cavity advantageously comprises a plurality of juxtaposed compartments which are powered successively by the same air flow.
  • the first compartment is supplied with air by the blade root, and the following compartments are supplied by the air flow coming from the previous compartment and having impacted the side walls of the dawn, by slots provided in the jacket walls under the protruding elements, the latter being made up of transverse ribs.
  • the helical ramp makes it possible to increase very significantly the internal exchange coefficient for cooling the blade in the leading edge area.
  • the cascade impact system placed in the cavity middle, allows to use the full potential of the cooling air before it is reintroduced into the vein.
  • the combination of these cooling technologies allows optimize the ventilation of the turbine blades by using at maximum the potential of the cooling air and having a thermal design leading to a mechanical service life optimal.
  • the design of the blade according to the invention makes it possible to reduce the ventilation flow and therefore increase the efficiency of the motor.
  • the drawing shows a moving blade 1 of a high turbine pressure which has a hollow aerodynamic wall 2, also referred to as a blade which extends radially between a blade root 3 and a blade head 4.
  • the aerodynamic wall 2 has four zones distinct: a rounded leading edge 5 intended to be placed opposite the flow of hot gases from the combustion chamber, an edge of tapered leak 6, distant from the leading edge and connected to the latter by a concave side wall 7, called the lower surface, and a side wall convex 8, called upper surface.
  • the side walls 7 and 8 are connected by two radial partitions 9 and 10 which separate the interior of the blade 1 into three cavities: a cavity upstream 11 located in the immediate vicinity of the leading edge 5, a cavity median 12 located between the two radial partitions 9 and 10 and a downstream cavity 13 located on the trailing edge side 6.
  • the downstream cavity 13 is the widest and occupies about two-thirds of the extent of dawn 1.
  • a third radial partition 14 further separates the downstream cavity 13 in an upstream part 15 and a downstream part 16 near the trailing edge 6.
  • a transverse partition 17 closes the lower end of the downstream cavity 13.
  • the upstream part 15 and the downstream part 16 communicate between them by an opening 18 formed at the foot of the third partition 14.
  • a plurality of slots 19 which connect the downstream part 16 of the downstream cavity 13 with the combustion gas stream which flows along the side walls 7 and 8 of the blade 1.
  • an orifice 20 is formed in the wall of the blade head 4 in line with the upstream cavity 11, and a second orifice 21, of oblong shape, is formed in the blade head 4, above the middle cavity 12.
  • two separate conduits 22 are formed. and 23 for supplying cooling air.
  • the first conduit 22 directly supplies cooling air to the ends lower of the upstream cavity 11 and the middle cavity 13, as well as this is shown in Figures 2 and 11, while the second leads 23 supplies cooling air to the upstream part 15 of the cavity downstream 13 in the vicinity of the blade head 4, this air having passed through the interior of the two side walls 6 and 7 consisting of double skins connected by at least straight bridges 24 of the upstream part 15, as shown in Figures 12 to 14.
  • the blade 1 is made at its aerodynamic wall hollow 2 into two half-blades subsequently joined by brazing, the cut between the two half-blades at the skeleton, or the dawn can be made in foundry.
  • the upstream cavity 11 located near the leading edge 5 is cooled by convection by through a helical ramp 30.
  • This ramp 30 can be obtained by foundry and be in one piece with a half-blade, or added in the upstream cavity 11 and brazed.
  • the helical ramp 30 shown in Figure 3 includes two nets 31a, 31b, however this ramp 30 may have only one single net or more than two, as needed.
  • the central body 32, or core, of the ramp 30 is not necessarily cylindrical, it can have an evolving section on the height in order to modulate the section as desired the section of cooling air passage in order to regulate the levels of exchange coefficient.
  • the cooling air circulates in a "worm" type cooling system that starts from the bottom 3 of dawn and ends at the head of dawn 5, from which the air is evacuated by orifice 20.
  • This system makes it possible to significantly increase the distance of the air flow and increase, at a fixed cooling rate, flow velocity relative to that obtained in a cavity purely radial.
  • disturbers 33 in the form inclined ribs are arranged either on the inner wall of the upstream cavity 11, ie on the helical ramp.
  • the disruptors can be made up of bridges 34 which connect the internal wall of the upstream cavity 11 to the core 32 of the helical ramp 30. These bridges 34 can be staggered.
  • the disturbers can be constituted by pins 35 arranged staggered or not on the wall internal of the upstream cavity 11.
  • the cooling device described above is implemented place in the upstream cavity 11 located in the immediate vicinity of the edge 5. This device could also be placed in other rooms. cavities.
  • the cooling air in this upstream cavity 11 circulates from centrifugal way, from the blade root 3 to the blade head 5. But the circuit can be reversed, especially in the fixed blades of turbine distributors, for example. Several helical ramps can also equip a cavity with reversal of the circuit cooling at the foot or at the head of the blade.
  • the central cavity 12 is cooled by convection using the cascade impact technology with cooling air introduced into the lower part of the cavity 12 from the conduit 22 formed in the blade root 3.
  • FIGS 2 and 8 to 11 show that a jacket 40 is introduced into the middle cavity 12.
  • This jacket 40 is produced by a mechanically welded assembly of a set of sheets beforehand drilled to make impact holes 41, and slots 42 or can be carried out directly in the foundry.
  • the shirt 40 is in the form of a chimney, of which two opposite side walls 43 and 44 bear on the walls internal of the radial partitions 9 and 10 and of which the two other walls 45 and 46, which include the impact holes 41 and the slots 42 are kept at a certain distance from the side walls 7 and 8 of dawn 1 by projecting elements 47, in the form of transverse ribs, formed on the walls 45 and 46 and regularly distributed between the blade root 3 and the blade head 4.
  • the internal cavity of the shirt 40 is divided into a certain number of compartments, referenced C1 to C7 in Figure 11, at by means of transverse partitions 48 arranged respectively, in starting from the blade root 3, under a couple of projecting elements 47 and separated from these projecting elements 47 by two facing slots 42 walls 7 and 8 of the blade 1.
  • the upper partition 48a is separated from the wall forming the blade head 4, so that the cooling air evacuated from the cavity C7 can be evacuated through the orifice 21.
  • the cooling circuit in the middle cavity 12 is carried out as follows
  • the air is brought through line 22 into compartment C1 of the jacket 40, then is evacuated from compartment C1 through the orifices impact 41, in order to strike the internal walls of the lower surface 7 and the upper surface 8 of the blade 1 in the vicinity of the blade root 3.
  • air is introduced into the second compartment C2 through the first slots 42, then discharged through the impact orifices 21 of the compartment C2 to be then reintroduced into the third compartment C3.
  • the air flows in this way to the upper compartment C7, from where it impacts the internal walls of the lower surface 7 and the upper surface 8 neighborhood of the blade head 4, then is evacuated out of the blade L by orifice 21.
  • the number of compartments can be different from 7, and the number of impact orifices 41 may be different from compartment to the other.
  • the shirt 40 described above could also be mounted in a cavity near the leading edge or the trailing edge. She can be adapted to both fixed and mobile blades. For fixed blades, the feed can be done by the blade head 4, and compartments C1 to C7 can be arranged radially, as in the example described above, or be arranged axially from the leading edge 5 to the trailing edge 6 or vice versa. This device can be applied as well for distributed impact (several rows of orifices) only for concentrated impact (a single row of holes 41).
  • the lower surface 7 and the upper surface 8 comprise at the level of the upstream part 15 of the cavity downstream 13 of the double skins 7a, 7b and 8a, 8b, connected by bridges 24.
  • the internal skins 7b, 8b are connected in the vicinity of the blade root 3 by the transverse partition 17. These two internal skins 7b, 8b extend to the vicinity of the partition forming the blade head 4, while reserving passages 50a, 50b near the blade head 4 by which, the air introduced through the orifice 23 of the blade root 3, and having circulated centrifugally between the skins 7a, 7b of the lower surface 7 and the skins 8a, 8b of the upper surface 8, is evacuated in the upstream part 15 of the downstream cavity.
  • This cooling air circulates centripetally in this upstream part 15, then enters the downstream part 16 by the opening 18. The air finally rises centrifugally in the downstream part 16 and is discharged into the stream of hot gases through the slots 19 formed in the trailing edge 6.
  • the cooling air introduced by orifice 23 is divided into two flows B1 and B2 by the partition transverse 17. These two flows B1 and B2 circulate so centrifugal through the multitude of bridges 24. These bridges 24 are obtained in foundry during casting. These bridges 24 can be staggered (see Figure 13) or arranged in a row (see figure 14).
  • the shape of the bridges can be any, of section cylindrical, square, oblong .... This device can also be used for cooling areas extending to the edge attack.
  • the constitution of the internal cooling circuits is realizes by assembling the added parts, helical ramp 30 and 40 welded shirt, in one of the half-blades, then in bringing the other half-dawn over the previous one and then brazing all the parts.
  • the cooling circuits can also be carried out entirely or partially directly in foundry.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP98401558A 1997-06-26 1998-06-25 Aubage refroidi par rampe hélicoidale, par impact en cascade et par système à pontets dans une double peau Expired - Lifetime EP0887515B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9707988 1997-06-26
FR9707988A FR2765265B1 (fr) 1997-06-26 1997-06-26 Aubage refroidi par rampe helicoidale, par impact en cascade et par systeme a pontets dans une double peau

Publications (2)

Publication Number Publication Date
EP0887515A1 EP0887515A1 (fr) 1998-12-30
EP0887515B1 true EP0887515B1 (fr) 2003-08-13

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EP98401558A Expired - Lifetime EP0887515B1 (fr) 1997-06-26 1998-06-25 Aubage refroidi par rampe hélicoidale, par impact en cascade et par système à pontets dans une double peau

Country Status (6)

Country Link
US (1) US5993156A (ru)
EP (1) EP0887515B1 (ru)
JP (1) JP3735201B2 (ru)
DE (1) DE69817094T2 (ru)
FR (1) FR2765265B1 (ru)
RU (1) RU2146766C1 (ru)

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EP0887515A1 (fr) 1998-12-30
JP3735201B2 (ja) 2006-01-18
US5993156A (en) 1999-11-30
DE69817094D1 (de) 2003-09-18
FR2765265A1 (fr) 1998-12-31
FR2765265B1 (fr) 1999-08-20
JPH1172003A (ja) 1999-03-16
RU2146766C1 (ru) 2000-03-20
DE69817094T2 (de) 2004-06-17

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