JPS5847103A - Gas turbine blade - Google Patents
Gas turbine bladeInfo
- Publication number
- JPS5847103A JPS5847103A JP14228681A JP14228681A JPS5847103A JP S5847103 A JPS5847103 A JP S5847103A JP 14228681 A JP14228681 A JP 14228681A JP 14228681 A JP14228681 A JP 14228681A JP S5847103 A JPS5847103 A JP S5847103A
- Authority
- JP
- Japan
- Prior art keywords
- hollow main
- blade body
- heat
- gas turbine
- main 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
Links
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
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
本発明は、例えば、火力発電プラントにおけるガスター
ビンに組込まれるガスタービン翼に係ル。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a gas turbine blade installed in a gas turbine in a thermal power plant, for example.
特に、このガスタービン翼における静翼及び動翼上して
使用される冷却翼の構造に関する。In particular, the present invention relates to the structure of cooling blades used on stator blades and rotor blades in this gas turbine blade.
一般に、ガスタービン発電ブラントにおけるガータービ
ンは、第１図及び第２図に示されるように、彎曲面を形
成した内部ケーシングムの内がわに冷却翼を構成する第
１段動翼１ｍ、第２段靜興１ｂ。In general, a gar turbine in a gas turbine power generation brand has a 1 m first stage rotor blade, which constitutes a cooling blade inside an inner casing having a curved surface, and a 1 m rotor blade, as shown in FIGS. 1 and 2. 2nd Dan Seiki 1b.
第３段静翼１ｃ ・・・第Ｎ段靜Ｘｌｎの顯に一定の間
隙を存して設け、他方、上記内部ケーシングＡ内ド設け
られた軸受（図示されず）に圧縮用羽根車上一体のロー
タｂを回転自在に軸装し、こｏＩ２−＋ｌＫ冷却翼を＃
＊する第１段動翼１ｍ、第２段動Ｊｉ！Ｉｂ、第３段動
翼１ｅ・・・第１段動翼１１ｎを上記間隙に位置するよ
うにして設け、上記第１段靜翼Ｉ＆の位置する上記内部
ケーシングＪｋＣ）開口部に燃焼機（図示されず）から
の燃焼ガスを上記ローターへ導入する鐘熱ケーシンダｅ
を設は丸ものである。3rd stage stator vane 1c... is provided with a certain gap between the sides of the Nth stage vane b is rotatably mounted on the shaft, and the oI2-+lK cooling blade is #
*1st stage moving blade 1m, 2nd stage moving blade Ji! Ib, third stage rotor blades 1e...first stage rotor blades 11n are provided so as to be located in the above-mentioned gap, and a combustor (not shown) is installed in the opening of the internal casing JkC) where the first stage silent blades I& are located. ) into the rotor.
The set is round.
従って、上記燃焼機からＯ高圧・高温１ｔＯ燃焼ガス（
以下、高温ガスという）拡、上記ｍｓケーシング−から
第１段靜翼１ａ、Ｊｌ１段動ｊｌｌａの願に流出す為こ
とによ〉、上記各動員１ｍ 、 １ｂ・・・Ｉｎと一体
の四−タｂを囲板し、こＯａ−夕１と一体の空気圧縮用
羽根及び発電機を駆動し得るようになっている。Therefore, from the above combustor, the O high pressure and high temperature 1 t O combustion gas (
(hereinafter referred to as high-temperature gas) expands and flows out from the above MS casing to the first stage silent wing 1a, Jl1 stage moving jlla], and the four-taper b integrated with each of the above-mentioned mobilization 1m, 1b...In. It is designed so that it can drive air compression vanes and a generator that are integrated with this Oa-1.
一方、従来、この種のガスタービン翼嬬、精書鋳造翼を
採用してお）、特に、＃Ｉ２図に示される第１段静翼１
ｍ及び第１Ｒ１ｂ翼１ｍは、超耐熱合金にて構成し、し
かも断面を魚影をなす中空冷却翼を潜威している。On the other hand, conventionally, this type of gas turbine blade has been adopted (previously cast blade), especially the first stage stationary blade 1 shown in Figure #I2.
m and the first R1b blade 1m are made of a super heat-resistant alloy and have a hollow cooling blade with a fish-shaped cross section.
即ち、中空冷却翼によるガスタービン翼は、高温ガスＯ
Ｖａ気中に長期間に亘って曝されている関係上、超耐熱
性及び耐蝕性を有する金属材で構成されると共に、冷却
流体を圧送する中空を愈す主翼体盛の外周面１４ に冷
却流体膜を廖威する多数Ｏ冷却噴流孔す、１を穿設し、
上記主翼体殖内にこれと略同法をなし、しかも、多数Ｏ
通気孔曽を有するインサート筒体良を空ＩＩＩを存して
構虜されている。That is, a gas turbine blade using hollow cooling blades is capable of handling high-temperature gas O.
Since it is exposed to Va air for a long period of time, it is made of a metal material with super heat resistance and corrosion resistance, and is cooled on the outer circumferential surface 14 of the main wing body that fills the hollow space through which the cooling fluid is pumped. A number of O cooling jet holes are drilled to create a fluid film,
Almost the same method is used in the main wing structure mentioned above, and a large number of O
The insert cylindrical body with the ventilation holes is captivated by the air III.
従って、上記第１段静翼１ｍの雰囲気中は、約１０００
℃以上の高温ガスによって長期間６ｃｍりて曝されてい
るけれども、上記インサーＦ筒体輩の側方から強制的に
供給される冷却流体が各通気孔曽及び空Ｉ１１を通して
上記各冷却噴流孔ｘｂ、Ｉかも上記高温ガス流体に対し
て冷却流体膜を形成するようＫＬ、これによル、上記主
翼体虚を遮熱し得るようになっている。Therefore, in the atmosphere of 1 m of the first stage stationary blade, approximately 1000
Although exposed for a long period of time to high-temperature gas at a temperature of 6 cm or higher, the cooling fluid forcibly supplied from the side of the inserter F cylinder body passes through each of the ventilation holes and the air I11 to each of the cooling jet holes xb. , I and KL form a cooling fluid film against the high-temperature gas fluid, thereby making it possible to insulate the main wing body from heat.
しかしながら、上述したガスタービン翼は、上糾各冷却
噴流孔ｍｌ、ｆ・°から高温ガスに対して冷却流体膜を
理論上、形成するようになっているけれども、実際には
、上記主翼体＃にお゛ける冷却温度分布は、上記各冷却
噴流孔ｍｌ、ｉの近傍のみ有効であ如、この各冷却噴流
孔１ 、 ｊ’から離れ九下流側の冷却温度分布は、高
温ガスによって急激に低下し、とれに起因して、超耐熱
合金材によるガスタービン翼としての主翼体通は、熱応
力によって変形し九シ、溶解するおそれもあり、ガスタ
ービン翼の交換を余儀なくされ、ガスタービンの運転効
率を低下するおそれがある。However, although the above-mentioned gas turbine blade is designed to theoretically form a cooling fluid film against high-temperature gas from each cooling jet hole ml, f°, in reality, the main blade body # The cooling temperature distribution in A is effective only in the vicinity of each of the cooling jet holes ml and i, and the cooling temperature distribution on the nine downstream side away from the cooling jet holes 1 and j' is rapidly affected by the high-temperature gas. Due to deterioration and cracking, the main wing body as a gas turbine blade made of super heat-resistant alloy material may be deformed and melted due to thermal stress, forcing the gas turbine blade to be replaced and causing damage to the gas turbine. There is a risk of reducing operating efficiency.
本発明は、上述し′＃−難点を解消するために、複数の
噴流孔を備えた中空主翼体の頭部嵌合部に耐熱セラミッ
ク材による魚ｌＩＩ萬体を着脱自在に設け、上記中空主
具体ｌ内面に耐熱セフイック層を附設し、これによ〕、
耐熱性及び耐腐蝕性Ｏ向上を図〉、併せて、ガスタービ
ンの運転効率を上げ為ようにし九ことを目的とするガス
タービン翼を提供するにＴｏゐ。In order to solve the above-mentioned problems, the present invention provides a removable body made of heat-resistant ceramic material in the head fitting part of the hollow main wing body having a plurality of jet holes, and Specifically, a heat-resistant safe layer is attached to the inner surface, and this allows
It is an object of the present invention to provide a gas turbine blade that aims to improve heat resistance and corrosion resistance, and also to increase the operating efficiency of a gas turbine.
以下、本発明を、ガスタービンにおける静ＪＩＩｌｃよ
る冷却翼に適用し九図示の一実施例にりいて説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention is applied to a static JIIlc cooling blade in a gas turbine and will be described below with reference to one embodiment shown in the drawings.
第３ｗＡ及び第４図において、符号ｌはガスタービンに
おける内部ケーシングに着脱自在に設けら−４れゐ耐熱
含金による中空主翼体であって、この中空主翼体ｌの上
・下部には嵌合部２，３が形成されてお９．この両嵌會
部２，３は上記内部ケーシングに壷金して取付けられる
ようになっている。In Fig. 3wA and Fig. 4, reference numeral 1 denotes a hollow main wing body made of heat-resistant metal, which is removably attached to the internal casing of the gas turbine. 9. Parts 2 and 3 are formed. Both fitting portions 2 and 3 are attached to the inner casing by means of a pot.
又、上記中空主翼体ｌの嵌合部２には冷却流体の流入口
４が形成されており、この流入口４には上記内部ケーシ
ンダ内を通りて圧送される冷却流体が上記中空主具体ｌ
内に供給されるようになっていゐ。さらに、上記中空主
翼体１０表ｇ１ｍ及び尾部１ｂには複数の噴流孔５及び
６が穿設されておシ、この各噴流孔５は上記中空主翼体
ＩＣ）１１面１ｍに冷却流体ｊｌ（薄膜層□流）を形成
されるよう２、ｋなっている。Further, a cooling fluid inlet 4 is formed in the fitting portion 2 of the hollow main wing body l, and the cooling fluid pumped through the inner casing is fed to the inlet 4 into the hollow main wing body l.
It is now supplied internally. Furthermore, a plurality of jet holes 5 and 6 are bored in the surface g1m of the hollow main wing body 10 and the tail part 1b, and each jet hole 5 is provided with a cooling fluid jl (thin film) on the surface 1m of the hollow main wing body IC) 11. 2,k so that a layer □ flow) is formed.
一方、上記中空主属体１の頭部１ｃ Ｋは頭部嵌合部７
が形成されておシ、とめ頭部嵌合部７には“複数（図で
は６個）に分割された耐熱セラミック材による亀頭翼体
８が着脱自在に関Ｗａ９を存して設けられている。なお
、この魚頭翼体８は、例えば、炭化珪素、窒化珪素など
による耐熱セラミック材で魚頭形に構成されることが望
ましい。又。On the other hand, the head 1c K of the hollow main body 1 is the head fitting part 7.
is formed, and the pawl head fitting portion 7 is provided with a glans wing body 8 made of a heat-resistant ceramic material that is divided into a plurality (six pieces in the figure) of a heat-resistant ceramic material and is removably attached thereto. It is preferable that the fishhead wing body 8 is made of a heat-resistant ceramic material such as silicon carbide or silicon nitride and is shaped like a fishhead.
上記亀頭翼体８の一端部８ａに位置する上記嵌合部２に
は盲蓋体１０が上記魚頭翼体８を高温ガスによる熱応力
によって抜出さないようにして設妙られておシ、上記分
割された上記各魚頭翼体８との・間には冷却流体の流出
口１１が形成されている。さらに、上記頭部嵌合部７に
は３個の通気孔１２１゜１２ｂ、１２ｅが穿設されてお
夛、この通気孔１２１の流体は上記間隙９を通して上記
流出口Ｕ及び噴流孔５へ流出して冷却流体膜を形成する
ようになっている。又、上記他Ｏ過気孔１２ｂ 、 １
２＠Ｏ流体紘上記各噴流孔５へ流出するようＫなって％
／ｈる。A blind cover 10 is installed in the fitting part 2 located at one end 8a of the glans wing body 8 to prevent the fishhead wing body 8 from being pulled out due to thermal stress caused by high temperature gas. A cooling fluid outlet 11 is formed between each of the divided fishhead wing bodies 8. Further, three ventilation holes 121, 12b and 12e are formed in the head fitting part 7, and the fluid in the ventilation holes 121 flows out through the gap 9 to the outlet U and the jet hole 5. to form a cooling fluid film. In addition to the above, O permeation holes 12b, 1
2@O fluid flow out to each jet hole 5 above so that K becomes %.
/hr.
他方、上記中空主翼体ｌの空胴円にはヒＯ中空主属体ｌ
の略同形をなすインサート筒体Ｕが空隙１４を存して嵌
装されておシ、このイン紫−ト筒体１３０周面には多数
の通気孔巧が上記１！１１１４を介して上記会噴流孔５
へ連通するようになっている。On the other hand, in the cavity circle of the hollow main wing body l, there is a hollow main wing body l.
An insert cylindrical body U having approximately the same shape as the above is fitted with a gap 14 in between, and a large number of ventilation holes are provided on the circumferential surface of the insert cylindrical body 130 to connect the above-mentioned holes through the above-mentioned holes 1!1114. Jet hole 5
It is designed to communicate with.
又、上記各噴流孔ＳＯ２設されていない上記中空主翼体
ｌの表面１ｍには帯状の浅い凹窩部１６が形成されてお
り、各凹窩部１６には耐熱セラ建ツク層１７が附設され
ている。In addition, a belt-shaped shallow recess 16 is formed on the surface 1m of the hollow main wing body l where the jet holes SO2 are not provided, and a heat-resistant ceramic construction layer 17 is attached to each recess 16. ing.
なお、上記各噴流孔Ｓの傾斜角度αはｌぎ〜６σ１１Ｊ
ｉｉ！に設けることが望ましい。Incidentally, the inclination angle α of each jet hole S is l~6σ11J.
ii! It is desirable to provide a
従って、ガスタービンの運転時、静翼による冷却具の雰
囲気中は、約１０００℃以上の高温ガスによって長期間
に亘りて曝されてお）、シかも、上記高温ガスは、第３
図及び１ｓ４図の鎖線Ｏ８矢方向から耐熱セラ６り材に
よる上記、魚頭翼体８及び中空主翼体１０曲面に沿って
流れを正整しながら尾端部へ流れる。一方、上記中空主
翼体１の＝部に穿設された流入口４からの冷却流体は上
記インサート筒体１３の各通気孔巧がら空１１１１４を
介して各噴流孔５．６へ噴出されゐ。しかして、との各
噴流孔５．６からの冷却流体は上記１魚顧興体８及び中
空主属体ｉを内がわから冷却すると共に、上記高温１ｊ
ｌＣＲ体に対して冷却流体膜を生成して上記中空主属体
１を總熱し得ゐようになっていゐ。Therefore, during operation of a gas turbine, the atmosphere of the cooling device using the stationary blades is exposed to high-temperature gas of approximately 1000°C or higher for a long period of time).
The flow flows from the arrow direction of the dashed line O8 in the figures and 1s4 to the tail end while straightening the flow along the curved surfaces of the fishhead wing body 8 and the hollow main wing body 10, which are made of heat-resistant ceramic material. On the other hand, the cooling fluid from the inlet 4 bored in the = section of the hollow main wing body 1 is ejected through the air holes 11114 of the insert cylinder 13 to the jet holes 5.6. Therefore, the cooling fluid from each jet hole 5.6 cools the above-mentioned 1-fish-guoxing body 8 and the hollow main body i, and also cools the above-mentioned high-temperature body 1j.
A cooling fluid film is generated on the ICR body to heat the hollow main body 1.
一方、上記魚頭翼体８及び中空主翼体１の外表１ 次に、第５図及び第６図に示される実施例は。On the other hand, the outer surface 1 of the fishhead wing body 8 and the hollow main wing body 1 Next, the embodiment shown in FIGS. 5 and 6 is as follows.
本発ＶＳＯ他の実施例でありて、これは上記中空主翼体
ｌの尾部ｌｂに複１ｋＫ分割され九尾部嵌金部１８を設
け、ζＯ尾部嵌金部１８に耐熱上２イック材による尾翼
体１９を着脱自在に設け、さらに、との尾翼体１９〇一
端部１９−に位置する前記嵌合部２に盲蓋体加を高温ガ
スによる熱応力によって抜出さないようにして設けたも
のであシ、上述し九臭体例と同一内容をなすものである
。なお、上記尾翼体Ｗの位置する上記ＩＩＩ流孔５の傾
斜角ｌは２σ〜９σＩ１ｍＫ設けることが望壜しい。This is another embodiment of the VSO of the present invention, in which the tail part lb of the hollow main wing body l is divided into multiple 1kK parts and provided with nine tail part fitting parts 18, and the tail part part 18 is made of a heat-resistant two-piece material. 19 is provided in a detachable manner, and a blind cover member is provided on the fitting portion 2 located at one end 19- of the tail body 190 to prevent it from being pulled out due to thermal stress caused by high-temperature gas. This is the same content as the nine odor body examples mentioned above. Note that it is desirable that the inclination angle l of the III flow hole 5 in which the tail body W is located is set to 2σ to 9σI1 mK.
又一方、第７ａｌｌ及び１ｌｌｉ８ＥＩＩＣ示されるＩ
Ａ施例紘、本発ＩＩＯ他の実施例であって、これは、上
記魚頭＾体８内に冷却多孔筒体４を空１１２２を存して
設け、ζ０！！１１２２を上記噴流孔５に連通す為よう
にすると共に、上記魚＠具体Ｓの一端部ｌｅｍ”に位置
する上記嵌合部２に給気孔１０ｍを有すゐ蓋体１Ｇを外
方へ抜は出さないようにして設は九もＯ′ｃ番〉、上述
し九実施例と同じ内容をなすもＯで参ゐ。On the other hand, 7all and 1lli8EIIC indicated I
Example A is another example of Hiro, Honsha IIO and others, in which a cooling porous cylinder 4 is provided within the fish head body 8 with an air gap 1122, and ζ0! ! 1122 to communicate with the jet hole 5, and the lid body 1G, which has an air supply hole 10m in the fitting part 2 located at one end lem'' of the fish@tai S, is pulled outward. The number 9 is also set to O'c so as not to appear, and the number 9 is also O'c, which has the same content as the embodiment 9 described above.
以上達べ九ように本発明によれば、複数の噴流孔！Ｓ、
６を備え丸中空主翼体１１０１１１部金部部７に耐熱セ
ツミック材による魚頭翼体８を着脱自在に設け、上記中
空主翼体１０表１ｉＫ耐熱セラ々ツク層１７を陰線しで
あるＯで、各噴流孔５．６から冷−動流体の流れが充分
に冷却流体膜を生成しなくても、耐熱性及び耐腐蝕性Ｏ
向上を図ることができるばかｐでな（、ガスタービンの
運転効率を上げることがで龜る。According to the present invention, there are multiple jet holes! S,
6, a fishhead wing body 8 made of heat-resistant ceramic material is removably attached to the metal part 7 of the round hollow main wing body 110111, and the hollow main wing body 10 is provided with a heat-resistant ceramic layer 17 as a hidden line O, Heat resistant and corrosion resistant O
It is difficult to improve the operating efficiency of gas turbines.
因に、上達した実施例紘ガスタービンＯ靜興に−ビンの
動翼に適用し得るように設計変更することは自由である
。Incidentally, it is free to modify the design of the improved example gas turbine so that it can be applied to the rotor blades of the gas turbine.
第１図は従来のガスタービン翼を組込んだガスタービン
Ｏ１！部のみを示す断７ｒＪｒＩＪ、第２図は第１図中
の鎖線ムー人に沿う拡大断面図、第３図は本発ＦＩＲＫ
よるガスタービン翼を示す平面図、第４図は第３図中の
鎖線Ｂ−ＢＫ沿う拡大断面図、第５図乃Ｉ第８図は本発
明の他の実施例を示す図で多゛−４、ａ・・・噴流孔、
７・・・頭部嵌合部、８・・・魚頭翼体。
１０・・・盲蓋体、１１・・・流出口、 １２ｍ 、
１２ｂ 、 １２ｅ・・・通気孔、１３・・・インサー
ト部材、１４・・・空隙、ｂ・・・通気孔、１７・・・
上２９２１層、１９・・・尾翼体。Figure 1 shows a gas turbine O1 incorporating conventional gas turbine blades! Section 7rJrIJ showing only the part, Figure 2 is an enlarged cross-sectional view along the chain line Mu in Figure 1, Figure 3 is the original FIRK.
FIG. 4 is an enlarged sectional view taken along the chain line B-BK in FIG. 3, and FIGS. 5 to 8 are views showing other embodiments of the present invention. 4, a... jet hole,
7... Head fitting part, 8... Fish head wing body. 10... Blind lid body, 11... Outlet, 12m,
12b, 12e...Vent hole, 13...Insert member, 14...Gap, b...Vent hole, 17...
Upper 2921st layer, 19...tail body.
Claims (1)
脱−＊Ｋｔけられた耐熱上２ζツク材による魚頭翼体と
、上記中空主属体０１１ｍＫｊｔ設され九耐熱セツ々ツ
ク層とを臭備したことを譬黴とするガスタービン翼。 ２、中空主翼体の尾部嵌脅部に耐熱−にツ叱ツク材によ
る尾翼体を着脱自在に設けたことを特徴とする特許請求
の範鴎第１項記載のガスタービン翼。 落 魚屓翼体内に冷却多孔筒体を！！−を存して設けた
ことを特徴とする特許鎖車ｏｗｎｓ第１項及び第２項記
載のガスタービン翼。[Scope of Claims] 1. A fish head wing body made of heat-resistant 2ζ material that is attached to and detached from the fitting part of the hollow main wing body with a plurality of jet holes, and the above-mentioned hollow main body 011mKjt. A gas turbine blade is accused of having a moldy odor with a heat-resistant adhesive layer installed therein. 2. A gas turbine blade according to claim 1, wherein a tail body made of a heat-resistant hardening material is detachably provided in the tail portion of the hollow main wing body. Cooling porous cylinder inside the wing body! ! - The gas turbine blade according to paragraphs 1 and 2 of the patent chain wheel owns.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14228681A JPS5925086B2 (en) | 1981-09-11 | 1981-09-11 | gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14228681A JPS5925086B2 (en) | 1981-09-11 | 1981-09-11 | gas turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5847103A true JPS5847103A (en) | 1983-03-18 |
| JPS5925086B2 JPS5925086B2 (en) | 1984-06-14 |
Family
ID=15311834
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14228681A Expired JPS5925086B2 (en) | 1981-09-11 | 1981-09-11 | gas turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5925086B2 (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59152176U (en) * | 1983-03-31 | 1984-10-12 | 三菱自動車工業株式会社 | fuel injection nozzle |
| JPS59155640U (en) * | 1983-03-31 | 1984-10-19 | カシオ計算機株式会社 | Wiring board device for small electronic equipment |
| JPS59174021U (en) * | 1983-05-11 | 1984-11-20 | 株式会社 バンビ | Connection structure between watch band and conical screw mounting bracket |
| JPS59174475U (en) * | 1983-05-11 | 1984-11-21 | 株式会社大林組 | Piping support fittings |
| JPS645932U (en) * | 1987-06-23 | 1989-01-13 | ||
| US4859147A (en) * | 1988-01-25 | 1989-08-22 | United Technologies Corporation | Cooled gas turbine blade |
| US5352091A (en) * | 1994-01-05 | 1994-10-04 | United Technologies Corporation | Gas turbine airfoil |
| US5690473A (en) * | 1992-08-25 | 1997-11-25 | General Electric Company | Turbine blade having transpiration strip cooling and method of manufacture |
| US5827045A (en) * | 1996-05-02 | 1998-10-27 | Asea Brown Boveri Ag | Thermally loaded blade for a turbomachine |
| WO2008105866A2 (en) * | 2007-02-27 | 2008-09-04 | Siemens Energy, Inc. | Cmc airfoil with thin trailing edge |
| US20110116912A1 (en) * | 2009-11-13 | 2011-05-19 | Mccall Thomas | Zoned discontinuous coating for high pressure turbine component |
| US8241001B2 (en) | 2008-09-04 | 2012-08-14 | Siemens Energy, Inc. | Stationary turbine component with laminated skin |
| EP3144479A1 (en) * | 2015-09-18 | 2017-03-22 | General Electric Company | Stator component cooling |
-
1981
- 1981-09-11 JP JP14228681A patent/JPS5925086B2/en not_active Expired
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59152176U (en) * | 1983-03-31 | 1984-10-12 | 三菱自動車工業株式会社 | fuel injection nozzle |
| JPS59155640U (en) * | 1983-03-31 | 1984-10-19 | カシオ計算機株式会社 | Wiring board device for small electronic equipment |
| JPS59174021U (en) * | 1983-05-11 | 1984-11-20 | 株式会社 バンビ | Connection structure between watch band and conical screw mounting bracket |
| JPS59174475U (en) * | 1983-05-11 | 1984-11-21 | 株式会社大林組 | Piping support fittings |
| JPH032178Y2 (en) * | 1983-05-11 | 1991-01-22 | ||
| JPS645932U (en) * | 1987-06-23 | 1989-01-13 | ||
| US4859147A (en) * | 1988-01-25 | 1989-08-22 | United Technologies Corporation | Cooled gas turbine blade |
| US5690473A (en) * | 1992-08-25 | 1997-11-25 | General Electric Company | Turbine blade having transpiration strip cooling and method of manufacture |
| US5352091A (en) * | 1994-01-05 | 1994-10-04 | United Technologies Corporation | Gas turbine airfoil |
| US5827045A (en) * | 1996-05-02 | 1998-10-27 | Asea Brown Boveri Ag | Thermally loaded blade for a turbomachine |
| WO2008105866A2 (en) * | 2007-02-27 | 2008-09-04 | Siemens Energy, Inc. | Cmc airfoil with thin trailing edge |
| WO2008105866A3 (en) * | 2007-02-27 | 2008-10-30 | Siemens Power Generation Inc | Cmc airfoil with thin trailing edge |
| US7887300B2 (en) | 2007-02-27 | 2011-02-15 | Siemens Energy, Inc. | CMC airfoil with thin trailing edge |
| US8241001B2 (en) | 2008-09-04 | 2012-08-14 | Siemens Energy, Inc. | Stationary turbine component with laminated skin |
| US20110116912A1 (en) * | 2009-11-13 | 2011-05-19 | Mccall Thomas | Zoned discontinuous coating for high pressure turbine component |
| EP2325441A3 (en) * | 2009-11-13 | 2013-01-23 | United Technologies Corporation | Gas turbine engine component with discontinuous coated areas and corresponding coating method |
| EP3144479A1 (en) * | 2015-09-18 | 2017-03-22 | General Electric Company | Stator component cooling |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5925086B2 (en) | 1984-06-14 |
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