JP5603552B2 - タービンブレード先端シュラウド - Google Patents
タービンブレード先端シュラウド Download PDFInfo
- Publication number
- JP5603552B2 JP5603552B2 JP2009001219A JP2009001219A JP5603552B2 JP 5603552 B2 JP5603552 B2 JP 5603552B2 JP 2009001219 A JP2009001219 A JP 2009001219A JP 2009001219 A JP2009001219 A JP 2009001219A JP 5603552 B2 JP5603552 B2 JP 5603552B2
- Authority
- JP
- Japan
- Prior art keywords
- cooling cavity
- cooling
- tip shroud
- ribs
- discrete
- 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.)
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- 238000001816 cooling Methods 0.000 claims description 202
- 238000005192 partition Methods 0.000 claims description 103
- 239000002826 coolant Substances 0.000 claims description 73
- 238000004891 communication Methods 0.000 description 7
- 239000012530 fluid Substances 0.000 description 7
- 239000002184 metal Substances 0.000 description 7
- 230000035882 stress Effects 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 238000000638 solvent extraction Methods 0.000 description 4
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 3
- 235000020637 scallop Nutrition 0.000 description 3
- 241000237509 Patinopecten sp. Species 0.000 description 2
- 230000002411 adverse Effects 0.000 description 2
- 238000005495 investment casting Methods 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 241000237503 Pectinidae Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011796 hollow space material Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Images
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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
-
- 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
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Description
先端シュラウドが、何らのスカラップも有しないか又はできるだけ小さなスカラップしか有しない状態で、タービンの高温度環境においてより良好に作動することを可能にする。さらに、そのようなシステムが先端シュラウドを冷却すると同時に先端シュラウドの重量も軽減することができる場合には、更なる効率改善を実現することができる。
本発明の現時点での好ましい例示的な実施形態についての以下の一層詳細な説明を注意深く検討することによって一層完全に理解されかつ認識されるであろう。
12 翼形部
14 根元
16 シャンク
18 ダブテール
20 先端シュラウド
22、24 当接面
26 シールレール
28 空気吐出孔
130 冷却空洞
132 正圧側冷却空洞
134 負圧側冷却空洞
136 後縁
112 翼形部
138 冷却媒体チャンバ
140 冷却媒体チャンバ開口
142 (切頭)リブ
144 (仕切り)リブ
145 外向きに延びる仕切りリブ
146 内向きに延びる仕切りリブ
147 出口開口
152 内部中央壁
154 入口開口
194 自由端
202 離散仕切りリブ
206 離散切頭リブ
208 離散コラム
212 円形出口開口
214 非円形出口開口
Claims (9)
- 先端シュラウド(20)と、
前記先端シュラウド(20)内に形成された単一の冷却空洞(130)と、
前記冷却空洞(130)内に形成された少なくとも1つの離散構造要素(202、206、208)と、
を含み、
前記離散構造要素(202、206、208)が、前記冷却空洞(130)の床を該冷却空洞(130)の天井に構造的に連結するが、該冷却空洞(130)の内部壁又は前記先端シュラウド(20)の外縁部から始まることなく、そこで終端することなく、或いはそこに連結することがない要素を含む、
タービンブレード(10)。 - 前記冷却空洞(130)の内部壁が、冷却媒体チャンバ(138)を形成した壁、該冷却空洞(130)の外側壁、及び内部中央壁(152)の1つを含む、請求項1に記載のタービンブレード(10)。
- 前記離散構造要素(202、206、208)が、該構造要素と前記冷却空洞(130)の床及び天井との連結部を除けば、該冷却空洞(130)の中空区域によって囲まれた構造要素を含む、請求項1に記載のタービンブレード(10)。
- 前記離散構造要素(202、206、208)が、離散仕切りリブ(202)を含み、
前記離散仕切りリブ(202)が、前記冷却空洞(130)を横断する距離の少なくとも大部分にわたって延びるリブを含む、
請求項3に記載のタービンブレード(10)。 - 前記冷却空洞を横断する距離の大部分が、該冷却空洞を横断する距離の少なくとも75%を含む、請求項4に記載のタービンブレード(10)。
- 前記離散仕切りリブ(202)が、該離散仕切りリブ(202)が前記冷却空洞(130)の略中央部において始まりかつ該冷却空洞(130)の2つの対向する外側壁に向って外向きに延びるように形成され、
前記離散仕切りリブ(202)が、該離散仕切りリブ(202)の第1の端部と前記冷却空洞(130)の対向する外側壁の一方との間に第1のギャップが形成されまた該離散仕切りリブ(202)の第2の端部と前記冷却空洞(130)の対向する外側壁の他方との間に第2のギャップが形成されるような長さのものである、
請求項4に記載のタービンブレード(10)。 - 前記第1のギャップ及び第2のギャップが各々、2.54〜19.05mmの横断方向距離を含む、請求項6に記載のタービンブレード(10)。
- 前記第1のギャップ及び第2のギャップが各々、少なくとも2.54mmの横断方向距離を含む、請求項6に記載のタービンブレード(10)。
- 前記離散構造要素(202、206、208)が、離散切頭リブ(206)を含み、
前記離散切頭リブ(206)が、前記冷却空洞(130)を横断する距離よりも短い長さのリブを含む、
請求項3に記載のタービンブレード(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/971,982 US8348612B2 (en) | 2008-01-10 | 2008-01-10 | Turbine blade tip shroud |
US11/971,982 | 2008-01-10 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2009168017A JP2009168017A (ja) | 2009-07-30 |
JP5603552B2 true JP5603552B2 (ja) | 2014-10-08 |
Family
ID=40758650
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2009001219A Active JP5603552B2 (ja) | 2008-01-10 | 2009-01-07 | タービンブレード先端シュラウド |
Country Status (5)
Country | Link |
---|---|
US (1) | US8348612B2 (ja) |
JP (1) | JP5603552B2 (ja) |
CN (1) | CN101482031B (ja) |
CH (1) | CH698339B1 (ja) |
DE (1) | DE102009003318B4 (ja) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11959392B2 (en) | 2020-10-06 | 2024-04-16 | Mitsubishi Heavy Industries, Ltd. | Rotor blade |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102128055A (zh) * | 2011-04-21 | 2011-07-20 | 西北工业大学 | 一种带冠的燃气涡轮冷却叶片 |
US9163519B2 (en) | 2011-07-28 | 2015-10-20 | General Electric Company | Cap for ceramic blade tip shroud |
US8956104B2 (en) * | 2011-10-12 | 2015-02-17 | General Electric Company | Bucket assembly for turbine system |
CN102943694B (zh) * | 2012-12-05 | 2015-02-18 | 沈阳航空航天大学 | 动叶叶顶隔板式迷宫结构 |
US9404511B2 (en) * | 2013-03-13 | 2016-08-02 | Robert Bosch Gmbh | Free-tipped axial fan assembly with a thicker blade tip |
FR3037974B1 (fr) | 2015-06-29 | 2017-07-21 | Snecma | Procede de fabrication d'une aube comportant une baignoire integrant un muret |
US10508554B2 (en) | 2015-10-27 | 2019-12-17 | General Electric Company | Turbine bucket having outlet path in shroud |
US10156145B2 (en) | 2015-10-27 | 2018-12-18 | General Electric Company | Turbine bucket having cooling passageway |
US9885243B2 (en) | 2015-10-27 | 2018-02-06 | General Electric Company | Turbine bucket having outlet path in shroud |
US10590786B2 (en) | 2016-05-03 | 2020-03-17 | General Electric Company | System and method for cooling components of a gas turbine engine |
US10344599B2 (en) * | 2016-05-24 | 2019-07-09 | General Electric Company | Cooling passage for gas turbine rotor blade |
US10982554B2 (en) * | 2016-10-28 | 2021-04-20 | General Electric Company | Tip shroud for a turbine engine |
US20180216474A1 (en) * | 2017-02-01 | 2018-08-02 | General Electric Company | Turbomachine Blade Cooling Cavity |
US10472974B2 (en) * | 2017-02-14 | 2019-11-12 | General Electric Company | Turbomachine rotor blade |
US10502069B2 (en) * | 2017-06-07 | 2019-12-10 | General Electric Company | Turbomachine rotor blade |
US10301943B2 (en) * | 2017-06-30 | 2019-05-28 | General Electric Company | Turbomachine rotor blade |
US10577945B2 (en) * | 2017-06-30 | 2020-03-03 | General Electric Company | Turbomachine rotor blade |
US11156102B2 (en) | 2018-03-19 | 2021-10-26 | General Electric Company | Blade having a tip cooling cavity and method of making same |
US10808552B2 (en) * | 2018-06-18 | 2020-10-20 | Raytheon Technologies Corporation | Trip strip configuration for gaspath component in a gas turbine engine |
CN114109516A (zh) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | 一种涡轮叶片端壁冷却结构 |
FR3137124A1 (fr) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Ensemble de turbomachine comportant des aubes portant des léchettes dont les extrémités se recouvrent mutuellement selon la direction circonférentielle |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3017159A (en) | 1956-11-23 | 1962-01-16 | Curtiss Wright Corp | Hollow blade construction |
JPH03194101A (ja) * | 1989-12-21 | 1991-08-23 | Toshiba Corp | ガスタービン冷却動翼 |
US6761534B1 (en) * | 1999-04-05 | 2004-07-13 | General Electric Company | Cooling circuit for a gas turbine bucket and tip shroud |
EP1136651A1 (de) * | 2000-03-22 | 2001-09-26 | Siemens Aktiengesellschaft | Kühlsystem für eine Turbinenschaufel |
US6471480B1 (en) * | 2001-04-16 | 2002-10-29 | United Technologies Corporation | Thin walled cooled hollow tip shroud |
US6506022B2 (en) | 2001-04-27 | 2003-01-14 | General Electric Company | Turbine blade having a cooled tip shroud |
US6511293B2 (en) * | 2001-05-29 | 2003-01-28 | Siemens Westinghouse Power Corporation | Closed loop steam cooled airfoil |
US6742991B2 (en) * | 2002-07-11 | 2004-06-01 | Mitsubishi Heavy Industries, Ltd. | Turbine blade and gas turbine |
JP4191578B2 (ja) * | 2003-11-21 | 2008-12-03 | 三菱重工業株式会社 | ガスタービンエンジンのタービン冷却翼 |
SE527932C2 (sv) * | 2004-02-27 | 2006-07-11 | Demag Delaval Ind Turbomachine | Ett rotorblad eller en ledskena för en rotormaskin, såsom en gasturbin |
AU2005284134B2 (en) * | 2004-09-16 | 2008-10-09 | General Electric Technology Gmbh | Turbine engine vane with fluid cooled shroud |
US7686581B2 (en) * | 2006-06-07 | 2010-03-30 | General Electric Company | Serpentine cooling circuit and method for cooling tip shroud |
US7568882B2 (en) * | 2007-01-12 | 2009-08-04 | General Electric Company | Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method |
-
2008
- 2008-01-10 US US11/971,982 patent/US8348612B2/en active Active
-
2009
- 2009-01-06 CH CH00009/09A patent/CH698339B1/de not_active IP Right Cessation
- 2009-01-06 CN CN200910003507.1A patent/CN101482031B/zh active Active
- 2009-01-07 DE DE102009003318.1A patent/DE102009003318B4/de active Active
- 2009-01-07 JP JP2009001219A patent/JP5603552B2/ja active Active
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11959392B2 (en) | 2020-10-06 | 2024-04-16 | Mitsubishi Heavy Industries, Ltd. | Rotor blade |
Also Published As
Publication number | Publication date |
---|---|
US20090180896A1 (en) | 2009-07-16 |
US8348612B2 (en) | 2013-01-08 |
CN101482031A (zh) | 2009-07-15 |
CN101482031B (zh) | 2014-01-08 |
JP2009168017A (ja) | 2009-07-30 |
CH698339A2 (de) | 2009-07-15 |
CH698339B1 (de) | 2015-03-13 |
DE102009003318A1 (de) | 2009-07-16 |
DE102009003318B4 (de) | 2024-01-11 |
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