JP4856644B2 - タービンステータのための保護装置 - Google Patents
タービンステータのための保護装置 Download PDFInfo
- Publication number
- JP4856644B2 JP4856644B2 JP2007531695A JP2007531695A JP4856644B2 JP 4856644 B2 JP4856644 B2 JP 4856644B2 JP 2007531695 A JP2007531695 A JP 2007531695A JP 2007531695 A JP2007531695 A JP 2007531695A JP 4856644 B2 JP4856644 B2 JP 4856644B2
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- JP
- Japan
- Prior art keywords
- radius
- axial
- turbine
- cavity
- protection device
- 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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Links
- 230000001681 protective effect Effects 0.000 title claims description 6
- 230000004323 axial length Effects 0.000 claims description 5
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 238000002485 combustion reaction Methods 0.000 description 10
- 238000001816 cooling Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 241000446313 Lamella Species 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 229910000601 superalloy Inorganic materials 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- 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
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gears, Cams (AREA)
Description
たとえ有効な冷却が行われたとしても、温度勾配及びタービンの作動温度に起因する変形を受け、この変形により、室温での形状とは異なる、すなわちタービンが作動していない停止形状に対して異なる変形した形状を生じる。
14 キャビティ
15 底面
16 強化リブ
20 薄板
21 貫通孔
60 円周方向曲率半径
70 軸方向曲率半径
Claims (7)
- 継手手段によって結合することができる一連の環状のセクタ(12)を含み、各セクタ(12)が、底面(15)を備えた少なくとも1つのキャビティ(14)を有する第1の側面を含む、タービンのステータのための保護装置であって、
前記少なくとも1つのキャビティ(14)の各底面(15)が円周方向及び/又は軸方向に凸状であり、
各セクタ(12)が、前記少なくとも1つのキャビティ(14)内部に配置されかつ長手方向に可変の断面を有して各セクタ(12)の剛性を調整するようになった少なくとも1つの強化リブ(16)を含み、
前記凸状の底面(15)が、軸方向断面において軸方向曲率半径(70)を有する頂点を有し、前記軸方向曲率半径(70)が、前記ロータの半径で除算したときに0.221〜0.299の範囲にある値を有し、
軸方向に沿った前記リブ(16)が、前記タービンの軸線に対して、3.162°〜4.278°の範囲にある角度(50)だけ傾斜している
ことを特徴とする、保護装置(10)。 - 前記軸方向曲率半径(70)が、前記ロータの半径で除算したときに0.260に等しい値を有することを特徴とする、請求項1記載の保護装置(10)。
- 前記半径方向断面における頂点が、円周方向曲率半径(60)を有し、前記円周方向曲率半径(60)が、前記ロータの半径で除算したときに0.365〜0.494の範囲にある値を有することを特徴とする、請求項1又は2記載の保護装置(10)。
- 前記円周方向曲率半径(60)が、前記ロータの半径で除算したときに0.429に等しい値を有することを特徴とする、請求項3記載の保護装置(10)。
- 前記軸方向断面における頂点が、前記少なくとも1つのキャビティ(14)の1つの端部からの間隔(80)を有し、前記間隔(80)が、前記少なくとも1つのキャビティ(14)の軸方向長さで除算したときに0.142〜0.192の範囲にある値を有することを特徴とする、請求項1乃至4のいずれか1項記載の保護装置(10)。
- 前記少なくとも1つのキャビティ(14)の軸方向長さで除算したときの間隔(80)が、0.167に等しい値を有することを特徴とする、請求項5記載の保護装置(10)。
- 前記角度(50)が、3.72°であることを特徴とする、請求項1記載の保護装置(10)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT001780A ITMI20041780A1 (it) | 2004-09-17 | 2004-09-17 | Dispositivo di protezione per uno statore di una turbina |
ITMI2004A001780 | 2004-09-17 | ||
PCT/EP2005/009997 WO2006029889A1 (en) | 2004-09-17 | 2005-09-14 | Protection device for a turbine stator |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2008513662A JP2008513662A (ja) | 2008-05-01 |
JP2008513662A5 JP2008513662A5 (ja) | 2008-10-30 |
JP4856644B2 true JP4856644B2 (ja) | 2012-01-18 |
Family
ID=35414962
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007531695A Active JP4856644B2 (ja) | 2004-09-17 | 2005-09-14 | タービンステータのための保護装置 |
Country Status (7)
Country | Link |
---|---|
US (1) | US7559740B2 (ja) |
EP (1) | EP1794418B1 (ja) |
JP (1) | JP4856644B2 (ja) |
KR (1) | KR101253789B1 (ja) |
CN (1) | CN1906381B (ja) |
IT (1) | ITMI20041780A1 (ja) |
WO (1) | WO2006029889A1 (ja) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ITMI20041781A1 (it) * | 2004-09-17 | 2004-12-17 | Nuovo Pignone Spa | Dispositivo di protezione per uno statore di una turbina |
FR2907841B1 (fr) * | 2006-10-30 | 2011-04-15 | Snecma | Secteur d'anneau de turbine de turbomachine |
RU2536443C2 (ru) * | 2011-07-01 | 2014-12-27 | Альстом Текнолоджи Лтд | Направляющая лопатка турбины |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS62195402A (ja) * | 1986-01-10 | 1987-08-28 | ゼネラル・エレクトリツク・カンパニイ | タ−ビンロ−タ翼の先端間隙を制御するシユラウド装置 |
JP2002349210A (ja) * | 2001-03-23 | 2002-12-04 | Siemens Ag | タービン |
Family Cites Families (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3146992A (en) * | 1962-12-10 | 1964-09-01 | Gen Electric | Turbine shroud support structure |
CH425341A (de) * | 1965-07-23 | 1966-11-30 | Bbc Brown Boveri & Cie | Gasturbine mit Kühlung der Schaufelträger |
US3346175A (en) * | 1966-04-01 | 1967-10-10 | Gen Motors Corp | Plastic coating for compressors |
US3730640A (en) * | 1971-06-28 | 1973-05-01 | United Aircraft Corp | Seal ring for gas turbine |
US3860358A (en) * | 1974-04-18 | 1975-01-14 | United Aircraft Corp | Turbine blade tip seal |
US4032253A (en) * | 1975-09-11 | 1977-06-28 | Carrier Corporation | Compensating ring for a rotary machine |
US4135851A (en) * | 1977-05-27 | 1979-01-23 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Composite seal for turbomachinery |
US4177004A (en) * | 1977-10-31 | 1979-12-04 | General Electric Company | Combined turbine shroud and vane support structure |
FR2416345A1 (fr) * | 1978-01-31 | 1979-08-31 | Snecma | Dispositif de refroidissement par impact des segments d'etancheite de turbine d'un turboreacteur |
FR2438165A1 (fr) * | 1978-10-06 | 1980-04-30 | Snecma | Dispositif de regulation de temperature pour turbines a gaz |
HU189210B (en) * | 1982-12-28 | 1986-06-30 | Richter Gedeon Vegyeszeti Gyar Rt,Hu | Process for the production of new carbamates of antilipaemic effect, as well as therapeutic preparations containing them |
CN1004016B (zh) * | 1985-04-01 | 1989-04-26 | 苏舍兄弟有限公司 | 涡轮机的筒形外壳 |
JPS62153504A (ja) * | 1985-12-26 | 1987-07-08 | Toshiba Corp | シユラウドセグメント |
US4868963A (en) * | 1988-01-11 | 1989-09-26 | General Electric Company | Stator vane mounting method and assembly |
US5071313A (en) * | 1990-01-16 | 1991-12-10 | General Electric Company | Rotor blade shroud segment |
US5127793A (en) * | 1990-05-31 | 1992-07-07 | General Electric Company | Turbine shroud clearance control assembly |
US5993150A (en) * | 1998-01-16 | 1999-11-30 | General Electric Company | Dual cooled shroud |
DE19915049A1 (de) * | 1999-04-01 | 2000-10-05 | Abb Alstom Power Ch Ag | Hitzeschild für eine Gasturbine |
US6340286B1 (en) * | 1999-12-27 | 2002-01-22 | General Electric Company | Rotary machine having a seal assembly |
US6508623B1 (en) * | 2000-03-07 | 2003-01-21 | Mitsubishi Heavy Industries, Ltd. | Gas turbine segmental ring |
US6390769B1 (en) * | 2000-05-08 | 2002-05-21 | General Electric Company | Closed circuit steam cooled turbine shroud and method for steam cooling turbine shroud |
US6340285B1 (en) * | 2000-06-08 | 2002-01-22 | General Electric Company | End rail cooling for combined high and low pressure turbine shroud |
US6761034B2 (en) * | 2000-12-08 | 2004-07-13 | General Electroc Company | Structural cover for gas turbine engine bolted flanges |
JP4698847B2 (ja) * | 2001-01-19 | 2011-06-08 | 三菱重工業株式会社 | ガスタービン分割環 |
GB2374123B (en) * | 2001-04-05 | 2004-09-08 | Rolls Royce Plc | Gas turbine engine system |
US6672833B2 (en) * | 2001-12-18 | 2004-01-06 | General Electric Company | Gas turbine engine frame flowpath liner support |
JP2004036443A (ja) * | 2002-07-02 | 2004-02-05 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンシュラウド構造 |
GB2404953A (en) * | 2003-08-15 | 2005-02-16 | Rolls Royce Plc | Blade tip clearance system |
FR2871513B1 (fr) * | 2004-06-15 | 2006-09-22 | Snecma Moteurs Sa | Systeme et procede de controle d'un flux d'air dans une turbine a gaz |
-
2004
- 2004-09-17 IT IT001780A patent/ITMI20041780A1/it unknown
-
2005
- 2005-09-14 US US10/595,855 patent/US7559740B2/en active Active
- 2005-09-14 EP EP05783917.7A patent/EP1794418B1/en active Active
- 2005-09-14 KR KR1020067011052A patent/KR101253789B1/ko active IP Right Grant
- 2005-09-14 JP JP2007531695A patent/JP4856644B2/ja active Active
- 2005-09-14 CN CN2005800016032A patent/CN1906381B/zh active Active
- 2005-09-14 WO PCT/EP2005/009997 patent/WO2006029889A1/en active Application Filing
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS62195402A (ja) * | 1986-01-10 | 1987-08-28 | ゼネラル・エレクトリツク・カンパニイ | タ−ビンロ−タ翼の先端間隙を制御するシユラウド装置 |
JP2002349210A (ja) * | 2001-03-23 | 2002-12-04 | Siemens Ag | タービン |
Also Published As
Publication number | Publication date |
---|---|
CN1906381A (zh) | 2007-01-31 |
ITMI20041780A1 (it) | 2004-12-17 |
WO2006029889A1 (en) | 2006-03-23 |
US7559740B2 (en) | 2009-07-14 |
US20070147994A1 (en) | 2007-06-28 |
CN1906381B (zh) | 2010-06-16 |
EP1794418B1 (en) | 2013-12-04 |
KR101253789B1 (ko) | 2013-04-12 |
KR20070052688A (ko) | 2007-05-22 |
JP2008513662A (ja) | 2008-05-01 |
EP1794418A1 (en) | 2007-06-13 |
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