EP1207269A1 - Aube de turbine à gaz - Google Patents

Aube de turbine à gaz Download PDF

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Publication number
EP1207269A1
EP1207269A1 EP00125032A EP00125032A EP1207269A1 EP 1207269 A1 EP1207269 A1 EP 1207269A1 EP 00125032 A EP00125032 A EP 00125032A EP 00125032 A EP00125032 A EP 00125032A EP 1207269 A1 EP1207269 A1 EP 1207269A1
Authority
EP
European Patent Office
Prior art keywords
cavity
gas turbine
leading edge
subspace
turbine blade
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
EP00125032A
Other languages
German (de)
English (en)
Other versions
EP1207269B1 (fr
Inventor
Peter Tiemann
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to DE50010300T priority Critical patent/DE50010300D1/de
Priority to EP00125032A priority patent/EP1207269B1/fr
Priority to CA002362020A priority patent/CA2362020A1/fr
Priority to JP2001350480A priority patent/JP4109445B2/ja
Priority to US10/004,476 priority patent/US6572329B2/en
Publication of EP1207269A1 publication Critical patent/EP1207269A1/fr
Application granted granted Critical
Publication of EP1207269B1 publication Critical patent/EP1207269B1/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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • 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
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the invention relates to a gas turbine blade with an inner Cavity for guiding a cooling fluid.
  • Such a coolable gas turbine blade shows the US 5,431,537.
  • Gas turbine blades are extremely high temperatures exposed by the hot gas flowing around them. For this Basically, they have to be cooled. Particularly high thermal Loads is the leading edge of a gas turbine blade exposed. For this reason, the leading edge be cooled particularly intensively.
  • cooling with Cooling air is the lowest possible consumption of cooling air aspired because the cooling air consumption the efficiency the gas turbine lowers.
  • turbulators are provided on the inside of the gas turbine blade, which swirl the cooling medium and thus a better one Allow heat transfer.
  • At the US gas turbine blade 5,431,537 is due to the turbulator configuration both achieved a favorable cooling of the leading edge, as well Achieved advantages for the castability of the turbine blade.
  • US 5,320,483 shows a steam-cooled gas turbine blade. Steam cooling is in terms of efficiency the gas turbine cheaper. However, it requires a closed one Cooling circuit because steam is different from air not introduced from the shovel into the hot gas duct can be. An impact cooling insert is used to cool the leading edge used, which corresponds to the contour of the leading edge Steam leads into a channel, being from that channel Impact-cooling through holes against the leading edge is directed. This construction is manufacturing technology very complex and also leads to one comparatively thick and therefore not aerodynamically optimized Leading edge.
  • the object of the invention is to provide a gas turbine blade, in which a technically simple and at the same time aerodynamically favorable cooling of the leading edge possible is.
  • this object is achieved by specifying a gas turbine blade directed along a blade axis with a profile that has a suction side, a pressure side, a Has leading edge and a trailing edge, and with a inner cavity in the profile for guiding a cooling fluid, wherein the cavity is adjacent to the leading edge Leading edge cavity and one towards the Trailing edge adjoining the leading edge cavity has the first partial cavity, the first partial cavity by moving in one direction from the leading edge to the Trailing edge extending partition into a first subspace and a second subspace is divided and wherein cooling fluid from the first sub-room via baffle cooling openings into the leading edge impact cooling in the leading edge cavity and can be introduced from there into the second subspace.
  • the path is taken for the first time connect a divided cavity upstream of the leading edge area, so that a closed in a constructively simple manner Cooling fluid guidance is possible.
  • This structure avoids a complex designed impact cooling insert in the area the leading edge and also allows the leading edge to perform in the most aerodynamically favorable way.
  • the leading edge cavity is from the first Partial cavity through a half rib connected to the profile Cut.
  • a half-rib does not extend like otherwise common for gas turbine blades from the suction side to to the pressure side, but ends in the cavity.
  • Such a half-rib can, for example, with a cast turbine blade be cast along. Cooling fluid is now from the first subspace led over the half rib into the leading edge cavity, for this purpose, baffle cooling openings are provided in the half-rib are. These impingement cooling openings are further preferred as Slots made.
  • Such a slotted half-rib is easy to manufacture and offers optimal Impingement cooling conditions.
  • a second partial cavity at the first partial cavity it preferably closes in the direction of the trailing edge a second partial cavity at the first partial cavity, the one extending from the suction side to the pressure side Rib is separated from the first partial cavity, the Cooling fluid through channels in the fin from the second subspace the second partial cavity can be introduced.
  • the cooling fluid in the first subspace parallel to the blade axis, in the second subspace transverse to the blade axis and in second partial cavity can be guided parallel to the blade axis. It This results in the constellation that the cooling fluid in the two subspaces of the first partial cavity two perpendicular has directions of flow directed towards one another.
  • the partition is preferably a sheet metal. This is what offers a further manufacturing technology for cast gas turbine blades Simplification, since no partition wall is cast got to.
  • the partition is in the finished cast scoop simply used.
  • the partition wall is preferred jammed in recesses between cast turbulators and / or on a particular cast on a rib Offset added.
  • the partition also separates the second subspace from the leading edge cavity, the Partition openings for introducing the cooling fluid from the leading edge cavity has in the second subspace.
  • This Execution is particularly preferred in connection with the Leading edge cavity to the first sub-space separating half-rib. Through the half rib on the one hand and the inserted as sheet metal Partition on the other hand thus becomes the leading edge cavity separated from the first partial cavity.
  • the sheet is preferably supported on the first half rib.
  • the gas turbine blade is preferably a guide blade executed.
  • the cooling fluid is preferably steam.
  • Steam cooling offers the advantage of saving cooling air and thus leads to an improvement in efficiency and increased performance for the gas turbine.
  • a steam supply can be used well because the guide vanes are connected to the housing through which the cooling steam can be supplied.
  • Figure 1 shows a side view of a gas turbine blade 1.
  • the gas turbine blade 1 is designed as a guide blade. It is directed along a blade axis 3.
  • the gas turbine blade 1 has a profile 5.
  • the profile 5 points a suction side 7 and a pressure side 9. Furthermore points the profile 5 has an entry edge 11 and a trailing edge 13 on.
  • the profile 5 is between a housing-side platform 15 and a rotor-side platform 17.
  • the Profile 5 has an inner cavity 19 for guiding a Cooling fluid on. The construction of the internal cooling structure of the profile 5 is explained in more detail with reference to the following figures.
  • Figure 2 shows a cross section through the gas turbine blade 1 from Figure 1.
  • the inner cavity 19 is constructed from a leading edge cavity lying in the region of the leading edge 11 21, one in the direction of the trailing edge 13 the first partial cavity adjoining the leading edge cavity 21 23, one adjoining the first partial cavity 23 second partial cavity 25 and one to the second partial cavity 25 adjoining partial cavity 27.
  • the first partial cavity 23 is divided into a first subspace 31 and a second subspace 33. These two subspaces 31, 33 are formed by a partition 37 which in first partial cavity 23 extends and extends in the direction of the leading edge extends to the trailing edge, so that the two subspaces 31, 33 side by side in the axial direction lie.
  • the partition 37 also borders the second subspace 33 from the leading edge cavity 21.
  • the leading edge cavity 21 is from the first subspace 31 through a half rib 35 separated from the pressure side 9 in the inner Cavity 19 extends approximately to half the distance to the opposite suction side 7
  • Half rib 35 pressing the partition 37 and through the half rib 35 is thus the leading edge cavity 21 from the first partial cavity 23 separated.
  • In the half rib 35 are slit-like Impingement cooling openings 55 arranged, see Figure 3.
  • Page openings 61 are provided.
  • the first partial cavity 23 is separated from the second partial cavity 25 by a the pressure side 9 to the suction side 7 extending rib 39 separated. About half the width of the rib 39 has one Paragraph 41, which extends along the blade axis 3.
  • first partial cavity 23 In the first partial cavity 23 are on the inside of the profile 5 extending across the blade axis 3 turbulators 45 arranged.
  • Turbulators 43 In the leading edge cavity 21 are Turbulators 43 extending transversely to the blade axis 3 arranged on the inside of the profile 5. Between Turbulators 43 and the turbulators 45 run approximately parallel a recess 44 to the blade axis 3.
  • the partition 37 is designed as a sheet metal, which at one end in the Recess 44 is held and at the other end on the paragraph 41 of the rib 39 rests. In addition, the partition 37 is against the half rib 35 stretched. This structure enables one particularly simple insertion 37, especially in an otherwise Cast gas turbine blade 1.
  • cooling fluid 51 in particular steam, in the first subspace 31 of the first Partial cavity 23 initiated. Arrives from the first subspace 31 the cooling fluid 51 via the impingement cooling openings 55 in the Half rib 35 in the leading edge cavity 21 that the Leading edge 11 is impact-cooled from the inside. The cooling fluid 51 then passes through openings 61 in partition 37 (see Figure 4) in the second subspace 33 where it is vertical flows to the blade axis 3. In contrast, it will Cooling fluid 51 in the first subspace 31 parallel to the blade axis 3 led. This occurs from the second subspace 33 Cooling fluid 51 via channels 63 in the rib 39 in the second Partial cavity 25, where it in turn is parallel to the blade axis 3 guided and derived from the gas turbine guide vane becomes.
EP00125032A 2000-11-16 2000-11-16 Aube de turbine à gaz Expired - Lifetime EP1207269B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
DE50010300T DE50010300D1 (de) 2000-11-16 2000-11-16 Gasturbinenschaufel
EP00125032A EP1207269B1 (fr) 2000-11-16 2000-11-16 Aube de turbine à gaz
CA002362020A CA2362020A1 (fr) 2000-11-16 2001-11-14 Aube de turbine a gaz
JP2001350480A JP4109445B2 (ja) 2000-11-16 2001-11-15 ガスタービン翼
US10/004,476 US6572329B2 (en) 2000-11-16 2001-11-16 Gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00125032A EP1207269B1 (fr) 2000-11-16 2000-11-16 Aube de turbine à gaz

Publications (2)

Publication Number Publication Date
EP1207269A1 true EP1207269A1 (fr) 2002-05-22
EP1207269B1 EP1207269B1 (fr) 2005-05-11

Family

ID=8170399

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00125032A Expired - Lifetime EP1207269B1 (fr) 2000-11-16 2000-11-16 Aube de turbine à gaz

Country Status (5)

Country Link
US (1) US6572329B2 (fr)
EP (1) EP1207269B1 (fr)
JP (1) JP4109445B2 (fr)
CA (1) CA2362020A1 (fr)
DE (1) DE50010300D1 (fr)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE50108466D1 (de) * 2001-08-09 2006-01-26 Siemens Ag Kühlung einer Turbinenschaufel
US6742991B2 (en) * 2002-07-11 2004-06-01 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine
US7137779B2 (en) * 2004-05-27 2006-11-21 Siemens Power Generation, Inc. Gas turbine airfoil leading edge cooling
GB2441771B (en) * 2006-09-13 2009-07-08 Rolls Royce Plc Cooling arrangement for a component of a gas turbine engine
US7762784B2 (en) * 2007-01-11 2010-07-27 United Technologies Corporation Insertable impingement rib
WO2010131385A1 (fr) 2009-05-11 2010-11-18 三菱重工業株式会社 Ailette de stator de turbine et turbine à gaz
US9127561B2 (en) * 2012-03-01 2015-09-08 General Electric Company Turbine bucket with contoured internal rib
CA2954785A1 (fr) * 2016-01-25 2017-07-25 Rolls-Royce Corporation Aube a serpentin a ecoulement avant
US20180210734A1 (en) * 2017-01-26 2018-07-26 Alibaba Group Holding Limited Methods and apparatus for processing self-modifying codes
CN108979734B (zh) * 2018-07-18 2021-05-28 上海交通大学 一种带有旋流的涡轮叶片多通道冷却结构和装置
CN111764967B (zh) * 2020-07-06 2022-10-14 中国航发湖南动力机械研究所 涡轮叶片尾缘冷却结构

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2956773A (en) * 1956-05-15 1960-10-18 Napier & Son Ltd Cooled hollow turbine blades
US3574481A (en) * 1968-05-09 1971-04-13 James A Pyne Jr Variable area cooled airfoil construction for gas turbines
FR2221020A5 (fr) * 1973-03-09 1974-10-04 Gen Electric
GB1467483A (en) * 1974-02-19 1977-03-16 Rolls Royce Cooled vane for a gas turbine engine
US4025226A (en) * 1975-10-03 1977-05-24 United Technologies Corporation Air cooled turbine vane
US4135855A (en) * 1973-10-13 1979-01-23 Rolls-Royce Limited Hollow cooled blade or vane for a gas turbine engine
US4252501A (en) * 1973-11-15 1981-02-24 Rolls-Royce Limited Hollow cooled vane for a gas turbine engine
US5320483A (en) 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
US5431537A (en) 1994-04-19 1995-07-11 United Technologies Corporation Cooled gas turbine blade
US5464322A (en) * 1994-08-23 1995-11-07 General Electric Company Cooling circuit for turbine stator vane trailing edge
US6036441A (en) * 1998-11-16 2000-03-14 General Electric Company Series impingement cooled airfoil

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4063851A (en) * 1975-12-22 1977-12-20 United Technologies Corporation Coolable turbine airfoil
US5667359A (en) * 1988-08-24 1997-09-16 United Technologies Corp. Clearance control for the turbine of a gas turbine engine
US5762471A (en) * 1997-04-04 1998-06-09 General Electric Company turbine stator vane segments having leading edge impingement cooling circuits

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2956773A (en) * 1956-05-15 1960-10-18 Napier & Son Ltd Cooled hollow turbine blades
US3574481A (en) * 1968-05-09 1971-04-13 James A Pyne Jr Variable area cooled airfoil construction for gas turbines
FR2221020A5 (fr) * 1973-03-09 1974-10-04 Gen Electric
US4135855A (en) * 1973-10-13 1979-01-23 Rolls-Royce Limited Hollow cooled blade or vane for a gas turbine engine
US4252501A (en) * 1973-11-15 1981-02-24 Rolls-Royce Limited Hollow cooled vane for a gas turbine engine
GB1467483A (en) * 1974-02-19 1977-03-16 Rolls Royce Cooled vane for a gas turbine engine
US4025226A (en) * 1975-10-03 1977-05-24 United Technologies Corporation Air cooled turbine vane
US5320483A (en) 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
US5431537A (en) 1994-04-19 1995-07-11 United Technologies Corporation Cooled gas turbine blade
US5464322A (en) * 1994-08-23 1995-11-07 General Electric Company Cooling circuit for turbine stator vane trailing edge
US6036441A (en) * 1998-11-16 2000-03-14 General Electric Company Series impingement cooled airfoil

Also Published As

Publication number Publication date
EP1207269B1 (fr) 2005-05-11
US20020085908A1 (en) 2002-07-04
JP2002161705A (ja) 2002-06-07
DE50010300D1 (de) 2005-06-16
CA2362020A1 (fr) 2002-05-16
US6572329B2 (en) 2003-06-03
JP4109445B2 (ja) 2008-07-02

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