JPH08177401A - Ceramic made turbine rotor - Google Patents
Ceramic made turbine rotorInfo
- Publication number
- JPH08177401A JPH08177401A JP32333094A JP32333094A JPH08177401A JP H08177401 A JPH08177401 A JP H08177401A JP 32333094 A JP32333094 A JP 32333094A JP 32333094 A JP32333094 A JP 32333094A JP H08177401 A JPH08177401 A JP H08177401A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- pressure surface
- turbine rotor
- thickness
- negative pressure
- 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.)
- Pending
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、セラミック製タービン
ロータの改良に関するものである。FIELD OF THE INVENTION This invention relates to improvements in ceramic turbine rotors.
【０００２】[0002]
【従来の技術】自動車用エンジンに備えられるターボチ
ャージャやガスタービンエンジンに備えられるタービン
ロータをセラミックスで形成し、タービンロータの耐熱
性を高めるとともに、軽量化がはかられているが、セラ
ミック材を用いて十分な強度を確保することが難しい。2. Description of the Related Art A turbocharger for an automobile engine and a turbine rotor for a gas turbine engine are made of ceramics to increase the heat resistance of the turbine rotor and reduce the weight. It is difficult to secure sufficient strength by using it.
【０００３】従来のターボチャージャとして、例えば図
８〜図１１に示すようなものがある(特開昭６１−１４
９５０４号公報、参照)。As a conventional turbocharger, there is, for example, one shown in FIGS. 8 to 11 (Japanese Patent Laid-Open No. 61-14).
9504 publication).
【０００４】これについて説明すると、タービンロータ
１は、その回転中心部に位置するディスク５と、このデ
ィスク５から径方向に突出する翼２がセラミックにより
一体形成されている。To explain this, in the turbine rotor 1, a disk 5 located at the center of rotation of the turbine rotor 1 and blades 2 projecting radially from the disk 5 are integrally formed of ceramic.
【０００５】翼２はその上流部１３から下流部１４にか
けて弓形に湾曲して形成される。翼２は正圧面６が凹状
に窪むように湾曲している。そして、タービンロータ１
は図８、図１１に矢印で示す方向に回転する。The blade 2 is formed in an arcuate shape from its upstream portion 13 to its downstream portion 14. The blade 2 is curved so that the positive pressure surface 6 is recessed. And the turbine rotor 1
Rotates in the direction indicated by the arrow in FIGS.
【０００６】翼２の断面形状は、翼２からディスク５に
かけて漸次肉厚が増大するように滑らか曲面をもってつ
ながり、翼２の翼厚中心線１０について正圧面６と負圧
面３が対称的に形成されている。The cross-sectional shape of the blade 2 is connected with a smooth curved surface so that the wall thickness gradually increases from the blade 2 to the disk 5, and the pressure surface 6 and the suction surface 3 are formed symmetrically with respect to the blade thickness center line 10 of the blade 2. Has been done.
【０００７】図９、図１０において、１０は、タービン
ロータ１の回転中心９から放射状に延びて、翼２を略等
分する翼厚中心線である。８は翼２の重力中心である。In FIGS. 9 and 10, reference numeral 10 denotes a blade thickness center line that extends radially from the rotation center 9 of the turbine rotor 1 and divides the blade 2 into substantially equal parts. 8 is the center of gravity of the wing 2.
【０００８】翼２の重力中心８は翼厚中心線１０上に配
置されるように、翼２の断面形状は、翼厚中心線１０に
ついて負圧面３と正圧面６が対称的に形成される。As the gravity center 8 of the blade 2 is arranged on the blade thickness center line 10, the cross-sectional shape of the blade 2 is such that the suction surface 3 and the pressure surface 6 are symmetrical with respect to the blade thickness center line 10. .
【０００９】[0009]
【発明が解決しようとする課題】しかしながら、このよ
うな従来のセラミック製タービンロータ１にあっては、
遠心力によって翼２を弓形に強く湾曲させようとする力
によって、図７に実線で示すように、翼２が正圧面６側
へ倒れるように変形し、負圧面３側の翼付け根部４に引
張応力が集中する可能性がある。このため、十分な強度
を確保することが難しいという問題点があった。However, in such a conventional ceramic turbine rotor 1 as described above,
Due to the force that strongly bends the blade 2 into a bow shape by the centrifugal force, as shown by the solid line in FIG. 7, the blade 2 is deformed so as to fall toward the pressure surface 6 side, and the blade root portion 4 on the suction surface 3 side is deformed. The tensile stress may be concentrated. Therefore, there is a problem that it is difficult to secure sufficient strength.
【００１０】本発明は上記の問題点を解消し、セラミッ
ク製タービンロータの重量増大を抑えつつ、十分な強度
を確保することを目的とする。It is an object of the present invention to solve the above problems and to secure sufficient strength while suppressing an increase in weight of a ceramic turbine rotor.
【００１１】[0011]
【課題を解決するための手段】請求項１記載の発明は、
回転中心部に位置するディスクと、ディスクから径方向
に突出する複数の翼がセラミックにより一体形成される
セラミック製タービンロータにおいて、翼を、その上流
部から下流部にかけて、回転後方を向いた正圧面側が窪
むように湾曲して形成し、翼の重力中心を翼厚中心線に
対して、回転前方を向いた負圧面側にオフセットする。According to the first aspect of the present invention,
In a ceramic turbine rotor in which a disk located at the center of rotation and a plurality of blades protruding in the radial direction from the disk are integrally formed of ceramic, in a blade, from the upstream portion to the downstream portion, a positive pressure surface facing rearward in rotation. The blade is formed so as to be concave so that the center of gravity of the blade is offset with respect to the blade thickness center line to the suction side facing forward in the rotation.
【００１２】請求項２記載のセラミック製タービンロー
タは、請求項１記載の発明において、翼の負圧面の付け
根部の肉厚を、翼の正圧面の付け根部の肉厚より大きく
形成する。According to a second aspect of the present invention, in the ceramic turbine rotor according to the first aspect, the wall thickness of the root portion of the suction surface of the blade is made larger than the wall thickness of the root portion of the pressure surface of the blade.
【００１３】請求項３記載のセラミック製タービンロー
タは、請求項１記載の発明において、翼の負圧面の先端
部の肉厚を、翼の正圧面の先端部の肉厚より大きく形成
する。According to a third aspect of the present invention, in the ceramic turbine rotor according to the first aspect of the present invention, the thickness of the tip of the suction surface of the blade is larger than the thickness of the tip of the pressure surface of the blade.
【００１４】請求項４記載のセラミック製タービンロー
タは、請求項１から３のいずれかに記載の発明におい
て、翼の上流側に位置する部位を、翼厚中心線について
負圧面と正圧面を非対称的に形成し、翼の下流側に位置
する部位を、翼厚中心線について負圧面と正圧面を対称
的に形成する。According to a fourth aspect of the present invention, in the ceramic turbine rotor according to the first aspect of the present invention, a portion located upstream of the blade has a negative pressure surface and a positive pressure surface which are asymmetric with respect to a blade thickness center line. And a portion located downstream of the blade is formed symmetrically with respect to the center line of the blade thickness.
【００１５】[0015]
【作用】請求項１に記載のセラミック製タービンロータ
において、タービンロータは例えばレシプロエンジンの
燃焼室またはガスタービンエンジンの燃焼器等から送ら
れるガスが回転径方向から導かれることにより、ガスの
流れを回転軸方向に換えながら回転力を取出し、高速回
転する。In the ceramic turbine rotor according to the first aspect of the present invention, the turbine rotor is configured so that a gas sent from, for example, a combustion chamber of a reciprocating engine or a combustor of a gas turbine engine is guided in the radial direction of rotation, thereby allowing the gas flow to flow. Rotate at high speed by extracting the rotational force while changing the direction of the rotation axis.
【００１６】翼を弓形に強く湾曲させようとする力が、
負圧面側の翼付け根部へ引張応力として作用する。この
引張応力に対して、翼の重力中心を負圧面側にオフセッ
トしているために発生する遠心力が、負圧面側の翼付け
根部へ圧縮応力として作用して相殺するため、負圧面側
の翼付け根部に生じる最大応力を低減することができ
る。The force that strongly bends the wing into a bow shape is
It acts as a tensile stress on the root of the blade on the suction side. With respect to this tensile stress, the centrifugal force generated because the center of gravity of the blade is offset to the suction surface side acts as a compressive stress on the blade root portion on the suction surface side and cancels it out. It is possible to reduce the maximum stress generated at the root portion of the blade.
【００１７】脆性材料であるセラミックを用いたタービ
ンロータでは、金属材料のように過度な応力下で塑性変
形ができないため、材料強度以上の応力が発生すると直
ちに破壊に至るため、セラミック製タービンロータの最
大応力を低下させることにより破壊に至ることを回避で
きる。A turbine rotor using a brittle material such as ceramic cannot be plastically deformed under an excessive stress like a metal material. Therefore, when a stress higher than the material strength is generated, the turbine rotor is immediately destroyed. Reducing the maximum stress can prevent destruction.
【００１８】請求項２に記載のセラミック製タービンロ
ータにおいて、翼の付け根部に余肉を形成する構造によ
り、タービンロータの鋳造時に用いられる翼型の製作お
よび型抜きが容易に行え、生産性を高められる。In the ceramic turbine rotor according to the second aspect of the present invention, due to the structure in which the excess thickness is formed at the root portion of the blade, the blade shape used for casting the turbine rotor can be easily manufactured and demolded, and the productivity is improved. To be enhanced.
【００１９】請求項３に記載のセラミック製タービンロ
ータにおいて、翼の先端部に余肉を形成する構造によ
り、翼の付け根部の断面形状が非対称的に形成される構
造に比べて、翼に加えられる余肉が少なくて済み、翼の
重量増加を抑えて慣性モーメントの増加を抑えられる。In the ceramic turbine rotor according to claim 3, in addition to the structure in which the cross-sectional shape of the root portion of the blade is formed asymmetrically due to the structure in which excess thickness is formed at the tip of the blade, The surplus thickness is small, and the increase in the moment of inertia is suppressed by suppressing the increase in the weight of the blade.
【００２０】請求項４に記載のセラミック製タービンロ
ータにおいて、翼が回転中心軸に対して弓形に湾曲して
いるために発生する遠心応力は、翼の下流部より上流部
で大きくなるが、上流部に限定して翼を翼厚中心線につ
いて非対称的に形成し、下流部を翼厚中心線について対
称的に形成する構造により、翼に加えられる余肉が少な
くて済み、タービンロータの重量増大を抑えつつ、十分
な強度を確保することができる。In the ceramic turbine rotor according to a fourth aspect of the present invention, the centrifugal stress generated because the blade is curved in an arc shape with respect to the center axis of rotation is greater in the upstream portion than in the downstream portion of the blade, but is upstream. Due to the structure in which the blade is formed asymmetrically with respect to the blade thickness centerline only in the section, and the downstream portion is formed symmetrically with respect to the blade thickness centerline, less surplus is added to the blade and the weight of the turbine rotor is increased. It is possible to secure sufficient strength while suppressing the above.
【００２１】[0021]
【実施例】以下、本発明の実施例を添付図面に基づいて
説明する。Embodiments of the present invention will be described below with reference to the accompanying drawings.
【００２２】図２に示すように、タービンロータ１は、
その回転中心部に位置するディスク５と、このディスク
５から径方向に突出する複数の翼２がセラミックにより
一体形成されている。As shown in FIG. 2, the turbine rotor 1 is
A disk 5 located at the center of rotation and a plurality of blades 2 projecting radially from the disk 5 are integrally formed of ceramic.
【００２３】図１において、タービンロータ１は図中矢
印で示すように回転し、翼２は回転前方向に向いた負圧
面３と、回転後方向を向いた正圧面６を有する。In FIG. 1, the turbine rotor 1 rotates as indicated by the arrow in the figure, and the blades 2 have a suction surface 3 facing the front direction of rotation and a pressure surface 6 facing the rear direction of rotation.
【００２４】図３に示すように、翼２はその上流部１３
から下流部１４にかけて弓形に湾曲して形成される。翼
２は正圧面６が凹状に窪むように湾曲している。As shown in FIG. 3, the blade 2 has an upstream portion 13 thereof.
To the downstream portion 14 are curved in an arc shape. The blade 2 is curved so that the positive pressure surface 6 is recessed.
【００２５】負圧面３と正圧面６の各付け根部４，７は
その翼端部からディスク５にかけて漸次肉厚が増大する
ように円弧状に湾曲する曲面をもってつながっている。
また、各付け根部はその翼端部からディスク５にかけて
楕円弧状に湾曲する曲面をもってつながるように形成し
てもよい。The root portions 4 and 7 of the negative pressure surface 3 and the positive pressure surface 6 are connected by a curved surface curved in an arc shape so that the wall thickness gradually increases from the blade end portion to the disk 5.
Further, each root may be formed so as to be connected to each other with a curved surface curved in an elliptic arc shape from the blade end to the disk 5.
【００２６】図１において、１０は、タービンロータ１
の回転中心軸９から放射状に延びて、翼２を略等分する
翼厚中心線である。８は翼２の重力中心である。In FIG. 1, 10 is a turbine rotor 1.
Is a blade thickness center line that extends radially from the rotation center axis 9 and divides the blade 2 substantially equally. 8 is the center of gravity of the wing 2.
【００２７】本発明の要旨とするところであるが、翼２
の重力中心８は翼厚中心線１０に対して翼２の負圧面３
側にオフセットされるように、翼２の断面形状は、翼厚
中心線１０について負圧面３と正圧面６が非対称的に形
成される。As the gist of the present invention, the wing 2
The center of gravity 8 of the blade is the suction surface 3 of the blade 2 with respect to the blade thickness center line 10.
The cross-sectional shape of the blade 2 is formed so that the suction surface 3 and the pressure surface 6 are asymmetrical with respect to the blade thickness center line 10 so as to be offset to the side.
【００２８】翼厚中心線１０に対する翼２の重力中心８
の位置は、翼２が弓形に湾曲する度合い、翼２の外径、
翼２の厚さ等に応じて決定される。Center of gravity 8 of blade 2 with respect to blade thickness center line 10
The position of is the degree to which the wing 2 bends in an arc, the outer diameter of the wing 2,
It is determined according to the thickness of the blade 2 and the like.
【００２９】この実施例では、翼２の付け根部分の断面
形状が非対称的に形成されている。すなわち、負圧面３
の付け根部４の肉厚が、正圧面６の付け根部７の肉厚よ
り大きくなるように形成される。図１において、破線は
負圧面３の付け根部４を正圧面６の付け根部７について
翼厚中心線１０に対して対称的に形成した場合の表面を
表しており、負圧面３の付け根部４は、正圧面６の付け
根部７の肉厚に対して、翼２とディスク５のつくる隅部
を埋めるように分布している。In this embodiment, the cross-sectional shape of the root portion of the blade 2 is formed asymmetrically. That is, the suction surface 3
The root portion 4 is formed to have a thickness larger than that of the root portion 7 of the positive pressure surface 6. In FIG. 1, the broken line represents the surface when the root portion 4 of the suction surface 3 is formed symmetrically with respect to the root portion 7 of the pressure surface 6 with respect to the blade thickness center line 10, and the root portion 4 of the suction surface 3 is shown. Are distributed so as to fill the corners formed by the blade 2 and the disk 5 with respect to the wall thickness of the root portion 7 of the positive pressure surface 6.
【００３０】図４に示すように、翼２の中心軸９方向に
ついて中間部より上流側に位置する上流部１３は、翼厚
中心線１０について負圧面３と正圧面６が非対称的に形
成される。図５に示すように、翼２の中心軸９方向につ
いて中間部より下流側に位置する下流部１４は、翼厚中
心線１０について負圧面３と正圧面６が対称的に形成さ
れる。As shown in FIG. 4, in the upstream portion 13 located upstream of the intermediate portion in the direction of the central axis 9 of the blade 2, the suction surface 3 and the pressure surface 6 are formed asymmetrically with respect to the blade thickness center line 10. It As shown in FIG. 5, in the downstream portion 14 located downstream of the intermediate portion in the direction of the central axis 9 of the blade 2, the suction surface 3 and the pressure surface 6 are formed symmetrically with respect to the blade thickness center line 10.
【００３１】以上のように構成され、次に作用について
説明する。With the above construction, the operation will be described below.
【００３２】タービンロータ１はレシプロエンジンの燃
焼室またはガスタービンエンジンの燃焼器等から送られ
るガスが回転径方向から導かれることにより、ガスの流
れを回転軸９方向に換えながら回転力を取出し、高速回
転する。The turbine rotor 1 extracts the rotational force while changing the gas flow in the direction of the rotation axis 9 by introducing the gas sent from the combustion chamber of the reciprocating engine or the combustor of the gas turbine engine from the radial direction of rotation. Rotate at high speed.
【００３３】図６は本実施例における翼２について、解
析計算による応力分布と、翼２の変形図とを示してい
る。解析は、ヤング率３１０ＧＰａ、翼２の周速度を７
００ｍ／ｓｅｃとした時の遠心応力を表している。FIG. 6 shows the stress distribution by the analytical calculation and the deformation diagram of the blade 2 in the present embodiment. The analysis was performed with a Young's modulus of 310 GPa and a peripheral velocity of the blade 2 of 7
It represents the centrifugal stress when the pressure is set to 00 m / sec.
【００３４】この場合、翼２を弓形に強く湾曲させよう
とする力が、負圧面３側の翼付け根部４へ引張応力とし
て作用するのに対して、翼２の重力中心８を負圧面３側
にオフセットしているために発生する遠心力が、負圧面
３側の翼付け根部４へ圧縮応力として作用して相殺する
ため、負圧面３側の翼付け根部４に生じる最大応力を２
９３ＭＰａとすることができる。In this case, the force that strongly bends the blade 2 into an arcuate shape acts as a tensile stress on the blade root portion 4 on the suction surface 3 side, whereas the gravity center 8 of the blade 2 moves toward the suction surface 3. Since the centrifugal force generated due to the offset to the side acts as a compressive stress on the blade root 4 on the suction surface 3 side to cancel it, the maximum stress generated on the blade root 4 on the suction surface 3 side is 2
It can be 93 MPa.
【００３５】図７は翼２の重力中心８を翼厚中心線１０
に配置した従来例について、解析計算による応力分布
と、翼２の変形図とを示している。FIG. 7 shows the center of gravity 8 of the blade 2 as the center line 10 of the blade thickness.
The stress distribution by the analytical calculation and the deformation diagram of the blade 2 are shown for the conventional example arranged in FIG.
【００３６】この場合、翼２を弓形に強く湾曲させよう
とする遠心力が、負圧面３側の翼付け根部４へ引張とし
て作用するため、最大応力は３４６ＭＰａとなる。In this case, the centrifugal force tending to strongly bend the blade 2 into an arc acts as a tensile force on the blade root 4 on the suction surface 3 side, and the maximum stress is 346 MPa.
【００３７】すなわち本発明は、翼２の重力中心８を翼
厚中心線１０について負圧面３側へオフセットすること
により、翼２に発生する最大応力を１５％程度低減する
ことができる。That is, in the present invention, the maximum stress generated in the blade 2 can be reduced by about 15% by offsetting the gravity center 8 of the blade 2 with respect to the blade thickness center line 10 toward the suction surface 3 side.
【００３８】また、正圧面６と負圧面３とでの応力を平
均化し、かつ高応力が占める部位を減らすため、脆性材
料であるセラミック製ロータの破壊確率を１／１０4か
ら１／１０6へと改善して、信頼性を高められる。Further, in order to average the stresses on the positive pressure surface 6 and the negative pressure surface 3 and reduce the portion occupied by high stress, the fracture probability of the brittle ceramic rotor is 1/10 4 to 1/10 6. To improve reliability.
【００３９】翼２が回転中心軸９に対して弓形に湾曲し
ているために発生する遠心応力は、翼２の下流部１４よ
り上流部１３で大きくなるが、上流部１３に限定して翼
２を翼厚中心線１０について非対称的に形成し、下流部
１４を翼厚中心線１０について対称的に形成する構造に
より、翼２に加えられる余肉が少なくて済み、タービン
ロータ１の重量増大を抑えつつ、十分な強度を確保する
ことができる。The centrifugal stress generated because the blade 2 is curved in an arc shape with respect to the rotation center axis 9 is larger in the upstream portion 13 than in the downstream portion 14 of the blade 2, but is limited to the upstream portion 13. Due to the structure in which 2 is formed asymmetrically with respect to the blade thickness centerline 10 and the downstream portion 14 is formed symmetrically with respect to the blade thickness centerline 10, less surplus is added to the blade 2 and the weight of the turbine rotor 1 is increased. It is possible to secure sufficient strength while suppressing the above.
【００４０】他の実施例として、翼２の先端部の断面形
状を非対称的に形成してもよい。すなわち、翼２の高さ
（回転中心軸９に対する半径方向の距離）が中間部より
高い位置において、負圧面３の肉厚が、正圧面６の肉厚
より大きくなるように形成される。As another example, the cross-sectional shape of the tip of the blade 2 may be formed asymmetrically. That is, the wall thickness of the suction surface 3 is formed to be larger than the wall thickness of the positive pressure surface 6 at a position where the height of the blade 2 (distance in the radial direction with respect to the rotation center axis 9) is higher than the middle portion.
【００４１】この場合、翼２の付け根部分の断面形状が
非対称的に形成される前記実施例に比べて、翼２に加え
られる余肉が少なくて済み、翼２の重量増加を抑えて慣
性モーメントの増加を抑えられる。In this case, as compared with the above-described embodiment in which the cross-sectional shape of the root portion of the blade 2 is formed asymmetrically, the extra thickness added to the blade 2 is small, the weight increase of the blade 2 is suppressed, and the moment of inertia is reduced. Can be suppressed.
【００４２】また、前記実施例の場合、翼２の付け根部
に余肉を形成する構造により、ロータ１の鋳造時に用い
られる翼型の製作および型抜きが容易に行え、生産性を
高められる。Further, in the case of the above-mentioned embodiment, due to the structure in which the excess thickness is formed at the root portion of the blade 2, the blade shape used during the casting of the rotor 1 can be easily manufactured and demolded, and the productivity can be improved.
【００４３】[0043]
【発明の効果】以上説明したように請求項１記載の発明
は、回転中心部に位置するディスクと、ディスクから径
方向に突出する複数の翼がセラミックにより一体形成さ
れるセラミック製タービンロータにおいて、翼を、その
上流部から下流部にかけて、回転後方を向い正負圧面側
が窪むように湾曲して形成し、翼の重力中心を翼厚中心
線に対して、回転前方を向いた負圧面側にオフセットし
たため、負圧面側の翼付け根部に生じる最大応力を低減
し、翼の質量増加を抑えてタービンロータの強度を十分
に確保して、信頼性を高めることができる。As described above, the invention according to claim 1 is a ceramic turbine rotor in which a disk located at the center of rotation and a plurality of blades projecting radially from the disk are integrally formed of ceramic. The blade was formed from the upstream part to the downstream part so as to be curved so that the positive and negative pressure surface side was concave toward the rear of the rotation, and the gravity center of the blade was offset to the negative pressure surface side facing the front of rotation with respect to the blade thickness center line. It is possible to reduce the maximum stress generated at the blade root portion on the suction surface side, suppress the increase in the blade mass, sufficiently secure the strength of the turbine rotor, and improve the reliability.
【００４４】請求項２記載のセラミック製タービンロー
タは、請求項１記載の発明において、翼の負圧面の付け
根部の肉厚を、翼の正圧面の付け根部の肉厚より大きく
形成したため、タービンロータの鋳造時に用いられる翼
型の製作および型抜きが容易に行え、生産性を高められ
る。。According to a second aspect of the invention, in the ceramic turbine rotor according to the first aspect of the invention, the thickness of the root portion of the suction surface of the blade is made larger than the thickness of the root portion of the pressure surface of the blade. The blade shape used for casting the rotor can be easily manufactured and die-cut, and the productivity can be improved. .
【００４５】請求項３記載のセラミック製タービンロー
タは、請求項１記載の発明において、翼の負圧面の先端
部の肉厚を、翼の正圧面の先端部の肉厚より大きく形成
したため、翼に加えられる余肉が少なくて済み、翼の重
量増加を抑えて慣性モーメントの増加を抑えられる。According to a third aspect of the present invention, in the ceramic turbine rotor according to the first aspect of the invention, the wall thickness of the tip of the suction surface of the blade is made larger than the wall thickness of the tip of the pressure surface of the blade. The amount of surplus added to the is small, and the increase in the moment of inertia can be suppressed by suppressing the increase in the weight of the wing.
【００４６】請求項４記載のセラミック製タービンロー
タは、請求項１から３のいずれかに記載の発明におい
て、翼の上流側に位置する部位を、翼厚中心線について
負圧面と正圧面を非対称的に形成し、翼の下流側に位置
する部位を、翼厚中心線について負圧面と正圧面を対称
的に形成したため、翼に加えられる余肉が少なくて済
み、タービンロータの重量増大を抑えつつ、十分な強度
を確保して、信頼性を高めることができる。According to a fourth aspect of the present invention, in the ceramic turbine rotor according to the first aspect of the present invention, a portion located upstream of the blade has a negative pressure surface and a positive pressure surface with respect to a blade thickness center line. The suction surface and the pressure surface are formed symmetrically with respect to the blade thickness center line in the portion located downstream of the blade, so that the surplus wall added to the blade is small and the increase in the weight of the turbine rotor is suppressed. At the same time, sufficient strength can be secured and reliability can be improved.
【図１】本発明の実施例を示し、タービンロータを図２
の矢印Ｚ方向から見た図。FIG. 1 shows an embodiment of the present invention, and FIG.
The figure seen from the arrow Z direction.
【図２】同じくタービンロータの断面図。FIG. 2 is a sectional view of the same turbine rotor.
【図３】同じく翼の断面図。FIG. 3 is a sectional view of the same wing.
【図４】同じく図２のＣ−Ｃ線に沿う断面図。FIG. 4 is a sectional view taken along line CC of FIG.
【図５】同じく図２のＤ−Ｄ線に沿う断面図。FIG. 5 is a sectional view taken along line D-D of FIG.
【図６】同じく翼の応力分布を示す図。FIG. 6 is a diagram showing a stress distribution of the blade.
【図７】比較例の翼の応力分布を示す図。FIG. 7 is a diagram showing a stress distribution of a blade of a comparative example.
【図８】従来例を示す翼の断面図。FIG. 8 is a sectional view of a blade showing a conventional example.
【図９】同じく図８のＡ−Ａ線に沿う断面図。9 is a sectional view taken along line AA of FIG.
【図１０】同じく図８のＢ−Ｂ線に沿う断面図。FIG. 10 is a sectional view taken along line BB of FIG.
【図１１】同じくタービンロータの正面図。FIG. 11 is a front view of the turbine rotor of the same.
１ タービンロータ ２ 翼 ３ 負圧面 ４ 負圧面付け根部 ５ ディスク ６ 正圧面 ７ 正圧面付け根部 ８ 重力中心 ９ 回転中心軸 １０ 翼厚中心線 １３ 上流部 １４ 下流部 1 Turbine Rotor 2 Blade 3 Negative Pressure Surface 4 Negative Pressure Surface Root 5 Disk 6 Positive Pressure Surface 7 Positive Pressure Root 8 Center of Gravity 9 Rotation Center Axis 10 Blade Thickness Centerline 13 Upstream 14 Downstream
Claims (4)
より一体形成されるセラミック製タービンロータにおい
て、 翼を、その上流部から下流部にかけて、回転後方を向い
た正圧面側が窪むように湾曲して形成し、 翼の重力中心を翼厚中心線に対して、回転前方を向いた
負圧面側にオフセットしたことを特徴とするセラミック
製タービンロータ。1. A ceramic turbine rotor in which a disk located at the center of rotation and a plurality of blades projecting in the radial direction from the disk are integrally formed of ceramics. The blade is rotated backward from the upstream portion to the downstream portion. A ceramic turbine rotor characterized in that it is formed so as to be curved so that the pressure surface side that faces toward is concave, and the gravity center of the blade is offset to the suction surface side that faces forward in the rotation with respect to the blade thickness center line.
面の付け根部の肉厚より大きく形成したことを特徴とす
る請求項１に記載のセラミック製タービンロータ。2. The ceramic turbine rotor according to claim 1, wherein the thickness of the root portion of the suction surface of the blade is larger than the thickness of the root portion of the pressure surface of the blade.
の先端部の肉厚より大きく形成したことを特徴とする請
求項１に記載のセラミック製タービンロータ。3. The ceramic turbine rotor according to claim 1, wherein the wall thickness of the tip of the suction surface of the blade is larger than the wall thickness of the tip of the pressure surface of the blade.
について負圧面と正圧面を非対称的に形成し、 翼の下流側に位置する部位を、翼厚中心線について負圧
面と正圧面を対称的に形成したことを特徴とする請求項
１から３のいずれかに記載のセラミック製タービンロー
タ。4. A portion located upstream of the blade has a suction surface and a pressure surface asymmetrical with respect to the blade thickness centerline, and a portion located downstream of the blade has a suction surface about the blade thickness centerline. The ceramic turbine rotor according to claim 1, wherein the positive pressure surface is formed symmetrically.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32333094A JPH08177401A (en) | 1994-12-26 | 1994-12-26 | Ceramic made turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP32333094A JPH08177401A (en) | 1994-12-26 | 1994-12-26 | Ceramic made turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH08177401A true JPH08177401A (en) | 1996-07-09 |
Family
ID=18153595
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP32333094A Pending JPH08177401A (en) | 1994-12-26 | 1994-12-26 | Ceramic made turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH08177401A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998057042A1 (en) * | 1997-06-12 | 1998-12-17 | Mitsubishi Heavy Industries, Ltd. | Cooled moving blade for gas turbines |
| DE19941134C1 (en) * | 1999-08-30 | 2000-12-28 | Mtu Muenchen Gmbh | Blade crown ring for gas turbine aircraft engine has each blade provided with transition region between blade surface and blade platform having successively decreasing curvature radii |
-
1994
- 1994-12-26 JP JP32333094A patent/JPH08177401A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998057042A1 (en) * | 1997-06-12 | 1998-12-17 | Mitsubishi Heavy Industries, Ltd. | Cooled moving blade for gas turbines |
| US6190128B1 (en) | 1997-06-12 | 2001-02-20 | Mitsubishi Heavy Industries, Ltd. | Cooled moving blade for gas turbine |
| DE19941134C1 (en) * | 1999-08-30 | 2000-12-28 | Mtu Muenchen Gmbh | Blade crown ring for gas turbine aircraft engine has each blade provided with transition region between blade surface and blade platform having successively decreasing curvature radii |
| FR2797906A1 (en) | 1999-08-30 | 2001-03-02 | Mtu Muenchen Gmbh | GAS TURBINE BLADE CROWN |
| US6478539B1 (en) | 1999-08-30 | 2002-11-12 | Mtu Aero Engines Gmbh | Blade structure for a gas turbine engine |
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