EP1644615B1 - Circuits de refroidissement pour anneau fixe de turbine a gaz - Google Patents

Circuits de refroidissement pour anneau fixe de turbine a gaz Download PDF

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Publication number
EP1644615B1
EP1644615B1 EP04767617.6A EP04767617A EP1644615B1 EP 1644615 B1 EP1644615 B1 EP 1644615B1 EP 04767617 A EP04767617 A EP 04767617A EP 1644615 B1 EP1644615 B1 EP 1644615B1
Authority
EP
European Patent Office
Prior art keywords
cavity
ring
ring segment
cooling circuit
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.)
Active
Application number
EP04767617.6A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1644615A1 (fr
Inventor
Stéphane CAMUS
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
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1644615A1 publication Critical patent/EP1644615A1/fr
Application granted granted Critical
Publication of EP1644615B1 publication Critical patent/EP1644615B1/fr
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
    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to fixed rings surrounding gas turbine gas passages, and more particularly to the cooling of gas turbine fixed rings.
  • a gas turbine in particular a turbomachine high-pressure turbine, typically comprises a plurality of stationary vanes arranged alternately with a plurality of blades in the passage of hot gases from the combustion chamber of the turbomachine.
  • the turbine blades are surrounded circumferentially by a fixed ring which is generally formed of a plurality of ring segments. These ring segments partially define the passage for the flow of hot gases through the blades of the turbine.
  • the ring segments of the turbine are thus subjected to the high temperatures of the hot gases from the combustion chamber of the turbomachine. For the mechanical and thermal resistance of the turbine ring, it is therefore necessary to provide the ring segments with cooling devices.
  • One of the known methods of cooling is to supply cooling air with an impact plate mounted on the body of the ring segments.
  • the plate is provided with a plurality of orifices for the passage of the air which comes, under the pressure difference on either side of the plate, to cool the ring segment by impact.
  • the cooling air is then discharged into the passage of the hot gases through holes made through the ring segment.
  • Such a method does not make it possible to obtain efficient and homogeneous cooling of the ring segments, in particular at the upstream end of the ring segment, which is a zone particularly exposed to hot gases. The life of the ring segments is thus affected.
  • this technology requires excessive sampling of cooling air, which reduces the performance of the turbine.
  • the present invention therefore aims at overcoming such drawbacks by proposing a stationary gas turbine ring, each ring segment of which is provided with internal cooling circuits requiring a low air flow and making it possible to effectively cool the ring segment by convection. thermal.
  • the upper and lower internal cooling circuits benefit from high heat exchange coefficients in order to ensure efficient and homogeneous cooling of each ring segment. These circuits make it possible in particular to cool the areas of the ring segment which are most exposed to hot gases. It is thus possible to reduce the air flow necessary for the cooling of the ring segments, even under severe thermodynamic operating conditions of the turbine.
  • the upper cooling circuit makes it possible, in particular, to cool the upstream side of the ring segment and to improve the efficiency of the lower cooling circuit.
  • the lower cooling circuit is used to cool the inner surface of the ring segment and possibly the adjacent ring segments.
  • the internal circuits of upper and lower cooling are independent of one another, which has the advantages of being able to dissociate the cooling provided by each cooling circuit and to adapt the flow of air supplying each circuit. For example, a high flow rate for the upper circuit can be used to effectively cool the upstream side of the ring segment (which is the hottest zone) and a lower flow rate for the lower circuit.
  • the independence between the cooling circuits also makes it possible to optimize cooling independently.
  • FIG. 1 schematically represents a portion of a high-pressure turbine 1 of a turbomachine.
  • the high-pressure turbine 1 comprises in particular a fixed annular housing 2 forming a casing of the turbomachine.
  • a fixed turbine ring 4 is fixed to this housing 2 and surrounds a plurality of blades 6 of the turbine. These blades 6 are arranged upstream of blades 8 with respect to the flow direction 10 of hot gases from a combustion chamber 12 of the turbomachine and passing through the turbine.
  • the turbine ring 4 surrounds a flow passage 14 for the hot gases.
  • the turbine ring 4 is composed of a plurality of ring segments arranged circumferentially around the axis of the turbine (not shown) so as to form a circular and continuous surface.
  • the turbine ring is composed of only one continuous piece. The present invention applies equally to a single turbine ring and a turbine ring segment.
  • each ring segment 16 forming the fixed ring has an inner annular surface 18 and an outer annular surface 20 radially offset from the inner surface 18.
  • the inner surface 18 faces the flow passage 14 hot gases.
  • Each ring segment 16 furthermore has, at its upstream transverse wall 16a, an upstream hook 22 and, at its downstream transverse wall 16b, a downstream hook 24.
  • the upstream and downstream hooks 24 allow the fixing of the ring segment 16 on the fixed annular housing 2 of the turbine.
  • the fixed annular housing 2 and the turbine ring formed by the ring segments 16 define between them an annular cooling chamber 26 which is supplied with cooling air via at least one orifice 28 passing through the annular housing. 2.
  • the cooling air supplying this cooling chamber 26 typically comes from a portion of the outside air passing through a fan and bypasses the combustion chamber of the turbomachine.
  • each ring segment 16 is provided with an upper internal cooling circuit A and a lower internal cooling circuit B, B ', the lower cooling circuit B, B' being independent of the cooling circuit.
  • the upper cooling circuit A is intended to cool the outer annular surface 20 and the upstream side of the ring segment 16 which is the side of the ring segment most exposed to hot gases.
  • the lower cooling circuit B, B ' is used to cool the inner annular surface 18 of the ring segment 16 which is the surface most exposed to the flow of hot gases.
  • the upper cooling circuit A also improves the cooling efficiency achieved by the lower circuit B, B '.
  • the upper cooling circuit A comprises at least a first internal cavity 32 which extends angularly between longitudinal walls 16c, 16d of the ring segment 16. This first cavity 32 also extends axially on only a part the width of the ring segment 16 defined between its upstream transverse walls 16a and downstream 16b.
  • the upper cooling circuit A also comprises at least one second internal cavity 34 extending angularly between the longitudinal walls 16c, 16d of the ring segment 16.
  • This second cavity 34 is disposed axially upstream of the first cavity 32, that is between an upstream transverse wall of the first cavity 32 and the upstream transverse wall 16a of the ring segment 16.
  • the width of the second cavity 34 (that is to say the distance between its transverse walls) is substantially less than that of the first cavity 32.
  • At least one cooling air supply port 36 opens into the cooling chamber 26 and opens into the first cavity 32 to supply the upper circuit A with cooling air. More precisely, this supply orifice 36 opens into the cooling chamber 26 and opens on the downstream side of the first cavity 32.
  • a plurality of emission holes 38 opening in the first cavity 32 and opening into the second cavity 34 are also provided. These emission holes 38 make it possible to cool the second cavity 34 by air impact.
  • the upper cooling circuit A further comprises a plurality of outlet holes 40a, 40b opening in the second cavity 34 and opening into the passage 14 of the hot gases, on the upstream side of the ring segment 16. The cooling air circulating in the upper circuit A is thus discharged through these outlet holes 40a, 40b.
  • a first series of exit holes 40a which open into the passage 14 of the hot, at the inner annular surface 18 of the ring segment 16 and a second series of outlet holes 40b which open into the passage 14 of the hot gases at the upstream transverse wall 16a of the ring segment.
  • the outlet holes 40a of the first series may be inclined with respect to the direction of flow of the hot gases, while the outlet holes 40b of the second series may be substantially parallel to this direction of flow.
  • the upper cooling circuit A has other series of outlet holes opening into the passage of the hot gases, on the upstream side of the ring segment 16.
  • the exit holes 40a and 40b are substantially aligned in an axial direction relative to the emission holes 38 opening in the first cavity 32 and opening into the second cavity 34. Such an arrangement thus makes it possible to reduce the pressure losses. . However, it is also conceivable that the exit holes 40a and 40b are not aligned with the emission holes 38.
  • the lower internal cooling circuit B is provided with at least three internal cavities 42, 44 and 46 which extend angularly between the longitudinal walls 16c, 16d of the ring segment 16.
  • These three cavities 42, 44 and 46 are furthermore offset radially with respect to the first cavity 32 of the upper cooling circuit A, ie they are arranged between the first cavity 32 of the upper circuit A and the annular surface. internal 18 of the ring segment 16.
  • At least one first internal cavity 42 is disposed on the downstream side of the ring segment 16. At least one second internal cavity 44 is disposed axially upstream of the first cavity 42. Likewise, at least one third cavity internal 46 is disposed axially upstream of the second cavity 44.
  • the lower cooling circuit B is supplied with cooling air by at least one air supply opening 48 opening in the cooling chamber 26 and opening into the first cavity 42.
  • the lower cooling circuit B also comprises at least a first passage 50 communicating the first cavity 42 with the second cavity 42 and at least a second passage 52 communicating the second cavity 44 with the third cavity 46.
  • a plurality of outlet holes 54 open in the third cavity 46 and open into the passage 14 of the hot gases, the upstream side of the ring segment 16 to cool it.
  • the outlet holes 54 open on the upstream side of the ring segment, at the inner annular surface 18. They are, for example, inclined with respect to the flow direction of the hot gases. The cooling air circulating in the lower circuit B is thus discharged through these outlet holes 54.
  • the second cavity 44 of this lower cooling circuit B is provided with disturbers 56 so as to increase heat transfer.
  • these disrupters 56 may be ribs extending longitudinally perpendicular to the direction of flow of air in the second cavity 44.
  • the disrupters may also take the form of pins or bridges for example.
  • the air supply port 48 and the second passage 52 of the lower circuit B are arranged on the side of one of the longitudinal walls 16c (or 16d) of the ring segment 16, while the first passage 50 of the lower circuit B is disposed on the side of the other longitudinal wall 16d (or 16c) of the ring segment.
  • Such an arrangement increases the flow path of the cooling air in the lower circuit B to increase heat transfer.
  • FIGS. Figures 5 and 6 Another embodiment of the ring segment according to the invention will now be described with reference to FIGS. Figures 5 and 6 .
  • the upper cooling circuit A of the ring segment is identical to that described above.
  • the lower cooling circuit B ' is different.
  • This lower cooling circuit B comprises at least four internal cavities 58, 60, 62 and 64 which extend axially between the upstream transverse walls 16a and downstream 16b of the ring segment 16.
  • These four cavities 58, 60, 62 and 64 are further radially offset relative to the first cavity 32 of the upper cooling circuit A, ie they are arranged between the first cavity 32 of the upper circuit A and the inner annular surface 18 of the ring segment 16.
  • the first cavity 58 of this lower cooling circuit B ' is disposed on the side of one of the longitudinal walls 16c (or 16d) of the ring segment 16.
  • the second cavity 60 is angularly offset relative to the first cavity 58
  • the third cavity 62 is angularly offset relative to the second
  • the fourth cavity 64 is angularly shifted relative to the third.
  • These cavities are arranged so that the fourth cavity 64 is disposed on the side of the longitudinal wall 16d (or 16c) opposite that of the first cavity 58.
  • At least a first 66 and a second 68 cooling air supply ports open into the cooling chamber 26 and open respectively into the second 60 and third cavities 62 to supply them with cooling air.
  • the lower cooling circuit B ' also comprises at least a first passage 70 communicating the second cavity 60 with the first cavity 58. Similarly, at least one second passage 72 communicates the third cavity 62 with the fourth cavity 64.
  • the lower cooling circuit B ' is provided with at least a plurality of first outlet holes 74 opening in the first cavity 58 and opening into the passage 14 of the hot gases, at the longitudinal wall 16c of the segment ring 16 on the side of which is arranged the first cavity 58.
  • these subcircuits may be substantially symmetrical with respect to a median longitudinal axis of the ring segment.
  • These lower sub-circuits are independently supplied by the supply ports 66, 68 and have independent outlet holes 74, 76 which enable the ring segments adjacent to the ring segment concerned to be cooled.
  • the second 60 and third 62 cavities of the lower cooling circuit B 'each comprise disruptors 78 so as to increase the heat transfer.
  • These disrupters 78 may take the form of ribs (as on the Figures 5 and 6 ), pimples or bridges.
  • first 66 and a second 68 supply ports of the lower circuit B ' are advantageously made on the side of one of the transverse walls 16a, 16b of the ring segment 16 (on the figure 6 , on the side of the downstream wall 16b) and the first 70 and second 72 passages of the lower circuit B 'are formed on the side of the other transverse wall 16b, 16a of the ring segment 16 (on the figure 6 on the side of the upstream wall 16a).
  • Such an arrangement makes it possible to increase the circulation path of the cooling air in the second lower circuit B 'in order to increase the heat transfer.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04767617.6A 2003-07-10 2004-07-08 Circuits de refroidissement pour anneau fixe de turbine a gaz Active EP1644615B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0308483A FR2857406B1 (fr) 2003-07-10 2003-07-10 Refroidissement des anneaux de turbine
PCT/FR2004/001785 WO2005008033A1 (fr) 2003-07-10 2004-07-08 Circuits de refroidissement pour anneau fixe de turbine a gaz

Publications (2)

Publication Number Publication Date
EP1644615A1 EP1644615A1 (fr) 2006-04-12
EP1644615B1 true EP1644615B1 (fr) 2015-04-01

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP04767617.6A Active EP1644615B1 (fr) 2003-07-10 2004-07-08 Circuits de refroidissement pour anneau fixe de turbine a gaz

Country Status (8)

Country Link
US (1) US7517189B2 (ja)
EP (1) EP1644615B1 (ja)
JP (1) JP4536723B2 (ja)
CA (1) CA2531519C (ja)
FR (1) FR2857406B1 (ja)
RU (1) RU2348817C2 (ja)
UA (1) UA83835C2 (ja)
WO (1) WO2005008033A1 (ja)

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Also Published As

Publication number Publication date
EP1644615A1 (fr) 2006-04-12
RU2348817C2 (ru) 2009-03-10
US7517189B2 (en) 2009-04-14
UA83835C2 (ru) 2008-08-26
WO2005008033A1 (fr) 2005-01-27
JP4536723B2 (ja) 2010-09-01
CA2531519C (fr) 2011-08-30
CA2531519A1 (fr) 2005-01-27
JP2007516375A (ja) 2007-06-21
FR2857406A1 (fr) 2005-01-14
US20070041827A1 (en) 2007-02-22
FR2857406B1 (fr) 2005-09-30
RU2005141577A (ru) 2006-06-27

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