EP0825332B1 - Kühlbare Schaufel - Google Patents

Kühlbare Schaufel Download PDF

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Publication number
EP0825332B1
EP0825332B1 EP97810493A EP97810493A EP0825332B1 EP 0825332 B1 EP0825332 B1 EP 0825332B1 EP 97810493 A EP97810493 A EP 97810493A EP 97810493 A EP97810493 A EP 97810493A EP 0825332 B1 EP0825332 B1 EP 0825332B1
Authority
EP
European Patent Office
Prior art keywords
rib
height
local
ribs
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.)
Expired - Lifetime
Application number
EP97810493A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0825332A1 (de
Inventor
Kenneth Hall
Bruce Dr. Johnson
Bernhard Dr. Weigand
Shey Dr. Wu
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.)
General Electric Switzerland GmbH
Original Assignee
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0825332A1 publication Critical patent/EP0825332A1/de
Application granted granted Critical
Publication of EP0825332B1 publication Critical patent/EP0825332B1/de
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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Definitions

  • the invention relates to a coolable blade according to the preamble of the first Claim.
  • Such coolable blades are known for example from DE 32 48 162.
  • a coolable shovel that has a leading edge area Has cooling fluid passage. Extend across the width of the cooling fluid passage ribs for triggering and promoting turbulence, which are at an acute angle, about 30 °, to the inside of the leading edge wall obliquely against the Cooling fluid flow direction are arranged in the cooling fluid passage. Ribs are aligned so that the cooling air is directed to the front edge of the blade becomes.
  • the rib height is between 10 to 33% of the height of the Cooling fluid passage.
  • the rib height is constant across the width of the cooling fluid passage and the cooling arrangement is only for the nasal channel Area of the front edge applicable.
  • the invention has for its object in a coolable blade type mentioned to improve the cooling of the blade and the Increase bucket life.
  • the essence of the invention is therefore that at least one rib which Rib is designed so that it has a tip and two legs which thighs of the rib at an acute angle compared to a straight line running parallel to the main flow direction are angled, the ratio of the local rib height to the local one Cavity height is essentially the same at all points on the rib.
  • the advantages of the invention include the fact that the blade through the design of the ribs with a tip and two legs evenly is cooled and the cooling fluid consumption can be reduced. This takes place in essentially by avoiding dead water areas in the area of Front and rear edge of the cooling channel of the blade.
  • By cooling the Shovel smoothes the surface temperature and the thermal Tensions in the blade are reduced, which increases the lifespan of the Bucket is raised. Due to the reduced cooling fluid consumption, the Turbine efficiency can be increased.
  • the blade can adjust the rib geometry in the cooling fluid passage and thus achieve a uniform surface temperature of the blade. shovel with ribs arranged in the cavity are also simple in terms of casting technology manufacture.
  • an embodiment of the invention is based on a schematic representation of a blade of a turbomachine.
  • the Airfoil 1 shows an airfoil 1 of a turbomachine with a cavity 2 shown in cross section, the cavity serving as a cooling fluid passage.
  • the Airfoil 1 has a leading edge area 3, a trailing edge area 4, a suction side wall 5 and a pressure side wall 6, the suction side and the pressure-side wall in the area of the front edge 3 and the rear edge 4 are interconnected. This essentially creates a double triangular shaped cooling duct with acute angled triangle tips in the area of the Front 3 and rear edge 4 of the blade.
  • On the pressure side wall 6 is a V-shaped rib 7 with a tip 9 and legs 14, 15 is arranged.
  • the V-shaped rib 7 can be designed isosceles, depending on the arrangement the rib tip 9 in the cavity, however, are also rib configurations unequal legs possible.
  • a ratio of a height h1 of the rib 7 to A local height H1 of the cavity 2 is the same size as a ratio a height h2 of the rib 7 to a local height H2 of the cavity 2.
  • Das Ratio of rib height h to cavity height H is thus at every point Rib essentially the same.
  • the rib 9 tapers to the passage the cooling fluid in these areas not to inhibit.
  • Fig. 2 shows the inside of the suction side wall 5 with cut Front edge area 3 and rear edge area 4.
  • One blade 10 one Turbomachine consists of the airfoil 1 and the Blade base 11 with which the blade 10 can be mounted. Between Blade 1 and blade root 11 is usually a platform 12 arranged, which the blade root of those flowing around the airfoil Shields fluids.
  • On the suction side wall there are also V-shaped ribs 7a arranged, here a tip 9a of the ribs on a plane 13 of the Cavity 2 is arranged and the tip 9a is downstream.
  • Level 13 runs radially to the blade and perpendicular to the inside of walls 5 and 6 the blade and is arranged at the widest point of the cavity 2. The Tip 9a is therefore at the point where the local rib height h is maximum.
  • a cooling fluid 20 is passed through the cavity 2, starting from the blade root.
  • the ribs are angled at an angle 8 to the main flow direction of the cooling fluid 20, the main flow direction running essentially parallel to the plane 13.
  • the angle 8 is 30 to 60 °, preferably 40 to 50 ° and in particular 45 °. Downstream of the V-shaped fins, vortices and recirculation zones arise, which increase the heat transfer coefficient.
  • Mean Nusselt number depending on the rib height of the V-shaped rib Ratio of rib height / cavity height [%] 0 18 31 44 Nu / Nu smooth 1 2-4 5 - 7 9-12
  • the Nusselt number Nu is defined as the ratio of the convectively dissipated to the conducted amount of heat.
  • Table 1 the average Nusselt number Nu for different rib heights is compared to the Nusselt number Nu smooth of a channel without ribs, the tips of the V-shaped ribs being arranged downstream. Table 1 clearly shows that the average Nusselt number increases sharply with increased rib height.
  • the ratio of local rib height to local cavity height should therefore be between 5 to 50%, preferably between 20 to 40%.
  • Fig. 3 shows the inside of the pressure side wall 6 with cut Front edge area 3 and rear edge area 4.
  • the on the inside of the pressure-side wall 6 arranged ribs 7b are also V-shaped, their Tip 9b is arranged on the level 13 of the cavity 2.
  • the tip 9b lies thus at the point where the local rib height h is maximum.
  • the ribs on the suction and pressure side to each other in Flow direction arranged offset.
  • the mutual arrangement of the ribs 7a and 7b can be seen from FIG.
  • the ribs are offset from one another in the direction of flow, so that the Flow successively onto a rib 7a of the suction side 5 and a rib 7b of the Print page 6 hits.
  • the ribs are advantageously in the middle arranged between the ribs of the opposite wall.
  • Fig. 5 shows the inside of the pressure side wall 6 with cut Front edge area 3 and rear edge area 4 of the blade 10, which from the Blade 1 and the blade root 11 there.
  • the ribs are also in the Angle 8 angled to the main flow direction of the cooling fluid 20.
  • FIG. 6 shows the suction-side wall with ribs 7a and indicated ribs 7c wherein the ribs 7a are arranged according to FIG. 2 on the suction side.
  • the relationship is of course local Rib height to local cavity height always less than 50%.
  • V-shaped ribs can also be in Buckets with several cooling air passages can be arranged if in the Edge zones of the cooling air diffusers have a high flow resistance.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP97810493A 1996-08-23 1997-07-15 Kühlbare Schaufel Expired - Lifetime EP0825332B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19634238A DE19634238A1 (de) 1996-08-23 1996-08-23 Kühlbare Schaufel
DE19634238 1996-08-23

Publications (2)

Publication Number Publication Date
EP0825332A1 EP0825332A1 (de) 1998-02-25
EP0825332B1 true EP0825332B1 (de) 2003-02-05

Family

ID=7803586

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810493A Expired - Lifetime EP0825332B1 (de) 1996-08-23 1997-07-15 Kühlbare Schaufel

Country Status (5)

Country Link
US (1) US5919031A (zh)
EP (1) EP0825332B1 (zh)
JP (1) JP4017708B2 (zh)
CN (1) CN1105227C (zh)
DE (2) DE19634238A1 (zh)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0945595A3 (en) * 1998-03-26 2001-10-10 Mitsubishi Heavy Industries, Ltd. Gas turbine cooled blade
SE512384C2 (sv) * 1998-05-25 2000-03-06 Abb Ab Komponent för en gasturbin
DE19846332A1 (de) 1998-10-08 2000-04-13 Asea Brown Boveri Kühlkanal eines thermisch hochbelasteten Bauteils
DE19856458B4 (de) * 1998-12-03 2017-08-10 General Electric Technology Gmbh Kühlvorrichtung zur gezielten Beaufschlagung einer zu kühlenden Oberfläche mit einem gasförmigen Kühlmedium sowie Verfahren hierzu
DE50002464D1 (de) * 1999-06-28 2003-07-10 Siemens Ag Heissgasbeaufschlagbares bauteil, insbesondere turbinenschaufel
JP4610836B2 (ja) * 2000-03-22 2011-01-12 シーメンス アクチエンゲゼルシヤフト 構造と冷却を強化したタービン翼
EP1136651A1 (de) * 2000-03-22 2001-09-26 Siemens Aktiengesellschaft Kühlsystem für eine Turbinenschaufel
US6695582B2 (en) * 2002-06-06 2004-02-24 General Electric Company Turbine blade wall cooling apparatus and method of fabrication
GB0222352D0 (en) * 2002-09-26 2002-11-06 Dorling Kevin Turbine blade turbulator cooling design
SE526847C2 (sv) * 2004-02-27 2005-11-08 Demag Delaval Ind Turbomachine En komponent som innefattar en ledskena eller ett rotorblad för en gasturbin
EP1921269A1 (de) * 2006-11-09 2008-05-14 Siemens Aktiengesellschaft Turbinenschaufel
CN103089335A (zh) * 2013-01-21 2013-05-08 上海交通大学 适用于涡轮叶片后部冷却腔的w形肋通道冷却结构
JP6036424B2 (ja) * 2013-03-14 2016-11-30 株式会社Ihi 冷却促進構造
KR101501444B1 (ko) * 2014-04-30 2015-03-12 연세대학교 산학협력단 냉각 성능 향상을 위한 내부유로 구조를 포함하는 가스터빈 블레이드
CN106481366B (zh) * 2015-08-28 2019-03-26 中国航发商用航空发动机有限责任公司 冷却叶片和燃气涡轮
CN106555617B (zh) * 2017-01-05 2018-07-10 西北工业大学 一种有斜下吹式气膜冷却孔的涡轮叶片
JP6906332B2 (ja) * 2017-03-10 2021-07-21 川崎重工業株式会社 タービン翼の冷却構造
US10590778B2 (en) * 2017-08-03 2020-03-17 General Electric Company Engine component with non-uniform chevron pins
US10787932B2 (en) * 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
CN110748384B (zh) * 2019-11-29 2021-11-05 大连理工大学 一种涡轮叶片尾缘折线式排气劈缝结构
CN112746871B (zh) * 2021-01-12 2022-06-10 南京航空航天大学 具有梯形横截面的连续波浪肋冷却结构
CN114673687B (zh) * 2022-05-30 2022-08-19 长城汽车股份有限公司 扇叶总成、风扇及车辆

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3171631A (en) * 1962-12-05 1965-03-02 Gen Motors Corp Turbine blade
GB1361256A (en) * 1971-08-25 1974-07-24 Rolls Royce Gas turbine engine blades
GB1410014A (en) * 1971-12-14 1975-10-15 Rolls Royce Gas turbine engine blade
US4775296A (en) 1981-12-28 1988-10-04 United Technologies Corporation Coolable airfoil for a rotary machine
US5052889A (en) * 1990-05-17 1991-10-01 Pratt & Whintey Canada Offset ribs for heat transfer surface
US5403157A (en) * 1993-12-08 1995-04-04 United Technologies Corporation Heat exchange means for obtaining temperature gradient balance
US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
DE19526917A1 (de) * 1995-07-22 1997-01-23 Fiebig Martin Prof Dr Ing Längswirbelerzeugende Rauhigkeitselemente

Also Published As

Publication number Publication date
US5919031A (en) 1999-07-06
CN1186150A (zh) 1998-07-01
EP0825332A1 (de) 1998-02-25
JP4017708B2 (ja) 2007-12-05
CN1105227C (zh) 2003-04-09
JPH1089006A (ja) 1998-04-07
DE59709255D1 (de) 2003-03-13
DE19634238A1 (de) 1998-02-26

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