JPS6278302U - - Google Patents
Info
- Publication number
- JPS6278302U JPS6278302U JP1986122995U JP12299586U JPS6278302U JP S6278302 U JPS6278302 U JP S6278302U JP 1986122995 U JP1986122995 U JP 1986122995U JP 12299586 U JP12299586 U JP 12299586U JP S6278302 U JPS6278302 U JP S6278302U
- Authority
- JP
- Japan
- Prior art keywords
- cavity
- wing member
- wing
- spar
- cooling air
- 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
Links
- 238000001816 cooling Methods 0.000 claims description 6
- 238000002485 combustion reaction Methods 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 239000002826 coolant Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Pulleys (AREA)
Description
第１図は本考案の一実施例による燃焼タービン
の回転子羽根又はベーンの翼の断面図、第２図は
第１図に示す翼の壁部を示す断面図、第３図は燃
焼タービン回転子羽根及びその内部の空気流パタ
ーンを示す説明図、第４図は本考案の一実施例に
よる燃焼タービン固定子ベーンの立面図、第５図
は第４図に示す固定子ベーンの変形実施例を示す
断面図、第６図は第４図に示す固定子ベーンの別
の変形実施例を示す断面図である。
１０……翼、１２……翼桁、１４……金属シエ
ル、１６……冷却材通路、１８ａ，１８ｃ……冷
却空所、１８ｃ……排出空所、３０ａ，３０ｂ，
３２ａ，３２ｂ，３４ａ……通孔、３４ｂ，３６
ａ，３６ｂ，３８ａ，３８ｂ……通孔、２４……
後縁、排出空所からの排出装置、５８……排出ポ
ート、７２……排出通孔、８２……排出通孔。
Fig. 1 is a sectional view of a rotor blade or vane blade of a combustion turbine according to an embodiment of the present invention, Fig. 2 is a sectional view showing the wall of the blade shown in Fig. 1, and Fig. 3 is a rotation of the combustion turbine. FIG. 4 is an elevational view of a combustion turbine stator vane according to an embodiment of the present invention, and FIG. 5 is a modified implementation of the stator vane shown in FIG. 4. FIG. 6 is a cross-sectional view showing another modified embodiment of the stator vane shown in FIG. 4. 10... Wing, 12... Wing spar, 14... Metal shell, 16... Coolant passage, 18a, 18c... Cooling cavity, 18c... Discharge cavity, 30a, 30b,
32a, 32b, 34a...through hole, 34b, 36
a, 36b, 38a, 38b... through hole, 24...
Trailing edge, evacuation device from the evacuation cavity, 58... evacuation port, 72... evacuation hole, 82... evacuation hole.
補正 昭６１．１２．９
実用新案登録請求の範囲を次のように補正する
。Amendment December 9, 1981 The scope of claims for utility model registration is amended as follows.
【実用新案登録請求の範囲】
前縁、後縁及び先端部を有する、燃焼タービン
の固定子又は回転子羽根の冷却式流体指向翼部材
であつて、該翼部材は、前記前縁から後縁に向か
つて順番に配列され区画化された半径方向の、供
給空所である第１空所、排出空所である第２空所
及び供給空所である第３空所を有すると共に、隔
置された凹側面及び凸側面を画定する、中空の翼
桁と、冷却空気を少なくとも前記第１及び第３空
所内に運ぶ装置と、前記翼部材の冷却に使用され
た前記冷却空気の廃気を少なくとも前記第２空所
から排出する排出装置と、前記翼桁の隔置された
凹側面及び凸側面に接合され該両側面を実質的に
包む金属シエルと、前記翼桁及び金属シエルの間
の空間内で実質的に翼弦方向に延長し、冷却空気
を前記翼部材の前記第１及び第３空所から前記第
２空所に運ぶように設けた複数の通路とを備える
冷却式流体指向翼部材。[Claims for Utility Model Registration] A cooled fluid-directing vane member for a stator or rotor blade of a combustion turbine, the vane member having a leading edge, a trailing edge, and a tip, the vane member extending from the leading edge to the trailing edge. It has a first cavity which is a supply cavity, a second cavity which is a discharge cavity, and a third cavity which is a supply cavity in the radial direction which are sequentially arranged and compartmentalized towards the a hollow wing spar defining a concave side surface and a convex side surface; a device for conveying cooling air into at least the first and third cavities; a discharge device for discharging from at least the second cavity; a metal shell joined to and substantially enclosing spaced apart concave and convex sides of the wing spar; and a metal shell between the wing spar and the metal shell. a plurality of passageways extending substantially chordwise within the space and configured to convey cooling air from the first and third cavities of the wing member to the second cavity; Wing member.
Claims (1)
の固定子又は回転子羽根の冷却式流体指向翼部材
であつて、該翼部材は、供給空所及び排出空所か
らなる少なくとも二つのスパン方向及び半径方向
の空所を有すると共に、隔置された凹側面及び凸
側面を画定する、中空の翼桁と、冷却空気を少な
くとも前記供給空所内に運ぶ装置と、前記翼部材
の冷却に使用された前記冷却空気の廃気を少なく
とも前記排出空所から排出する排出装置と、前記
翼桁の隔置された凹側面及び凸側面に接合され該
両側面を実質的に含む金属シエルと、前記翼桁及
びシエルの間に空間内で実質的に翼弦方向に延長
し、冷記空気を前記翼部材の前記供給空所から排
出空所に運ぶように設けた複数の通路とを備える
冷却式流体指向翼部材。 A cooled, fluid-directing wing member of a stator or rotor blade of a combustion turbine having a leading edge, a trailing edge, and a tip, the wing member having at least two spanwise directions comprising a supply cavity and a discharge cavity. and a hollow wing spar having a radial cavity and defining spaced apart concave and convex sides, a device for conveying cooling air into at least the supply cavity, and a device used for cooling the wing member. a metal shell joined to and substantially including spaced apart concave and convex sides of the wing spar; a plurality of passageways extending substantially chordwise in the space between the spar and the shell for conveying cooling air from the supply cavity to the discharge cavity of the wing member; Directional wing member.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US32888481A | 1981-12-09 | 1981-12-09 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS6278302U true JPS6278302U (en) | 1987-05-19 |
| JPH0110401Y2 JPH0110401Y2 (en) | 1989-03-24 |
Family
ID=23282872
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57214732A Pending JPS58106102A (en) | 1981-12-09 | 1982-12-09 | Convection cooling wing of rotor blade or stator vane of combustion turbine |
| JP1986122995U Expired JPH0110401Y2 (en) | 1981-12-09 | 1986-08-12 |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57214732A Pending JPS58106102A (en) | 1981-12-09 | 1982-12-09 | Convection cooling wing of rotor blade or stator vane of combustion turbine |
Country Status (6)
| Country | Link |
|---|---|
| JP (2) | JPS58106102A (en) |
| AR (1) | AR228927A1 (en) |
| BE (1) | BE895285A (en) |
| GB (1) | GB2111604A (en) |
| IT (1) | IT1153370B (en) |
| MX (1) | MX157531A (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2550978B1 (en) * | 1983-05-26 | 1989-10-13 | Rolls Royce | METHOD FOR APPLYING SURFACE COATINGS ON ARTICLES |
| JP4170400B2 (en) * | 1997-04-07 | 2008-10-22 | シーメンス アクチエンゲゼルシヤフト | Turbine blade, its use and cooling method of turbine blade |
| DE19939179B4 (en) * | 1999-08-20 | 2007-08-02 | Alstom | Coolable blade for a gas turbine |
| EP1457641A1 (en) * | 2003-03-11 | 2004-09-15 | Siemens Aktiengesellschaft | Method for cooling a hot gas guiding component and component to be cooled |
| US8727727B2 (en) * | 2010-12-10 | 2014-05-20 | General Electric Company | Components with cooling channels and methods of manufacture |
| US9115590B2 (en) * | 2012-09-26 | 2015-08-25 | United Technologies Corporation | Gas turbine engine airfoil cooling circuit |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5672201A (en) * | 1979-11-14 | 1981-06-16 | Hitachi Ltd | Cooling structure of gas turbine blade |
-
1982
- 1982-12-06 IT IT24620/82A patent/IT1153370B/en active
- 1982-12-07 GB GB08234832A patent/GB2111604A/en not_active Withdrawn
- 1982-12-08 MX MX195506A patent/MX157531A/en unknown
- 1982-12-08 BE BE0/209682A patent/BE895285A/en not_active IP Right Cessation
- 1982-12-09 JP JP57214732A patent/JPS58106102A/en active Pending
- 1982-12-09 AR AR291543A patent/AR228927A1/en active
-
1986
- 1986-08-12 JP JP1986122995U patent/JPH0110401Y2/ja not_active Expired
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5672201A (en) * | 1979-11-14 | 1981-06-16 | Hitachi Ltd | Cooling structure of gas turbine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| BE895285A (en) | 1983-06-08 |
| GB2111604A (en) | 1983-07-06 |
| IT8224620A1 (en) | 1984-06-06 |
| AR228927A1 (en) | 1983-04-29 |
| JPH0110401Y2 (en) | 1989-03-24 |
| JPS58106102A (en) | 1983-06-24 |
| IT8224620A0 (en) | 1982-12-06 |
| IT1153370B (en) | 1987-01-14 |
| MX157531A (en) | 1988-11-28 |
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