JP2015227661A - Turbine component - Google Patents
Turbine component Download PDFInfo
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- JP2015227661A JP2015227661A JP2015105952A JP2015105952A JP2015227661A JP 2015227661 A JP2015227661 A JP 2015227661A JP 2015105952 A JP2015105952 A JP 2015105952A JP 2015105952 A JP2015105952 A JP 2015105952A JP 2015227661 A JP2015227661 A JP 2015227661A
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- turbine component
- hook
- outer shroud
- shroud
- gap
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- 239000011153 ceramic matrix composite Substances 0.000 claims abstract description 13
- 239000000835 fiber Substances 0.000 claims abstract description 11
- 239000000463 material Substances 0.000 claims description 21
- 239000011248 coating agent Substances 0.000 claims description 10
- 238000000576 coating method Methods 0.000 claims description 10
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 10
- 230000004888 barrier function Effects 0.000 claims description 6
- 230000007613 environmental effect Effects 0.000 claims description 6
- 229910018540 Si C Inorganic materials 0.000 claims description 4
- 239000011159 matrix material Substances 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 6
- 238000001816 cooling Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 5
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000010248 power generation Methods 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- BPQQTUXANYXVAA-UHFFFAOYSA-N Orthosilicate Chemical compound [O-][Si]([O-])([O-])[O-] BPQQTUXANYXVAA-UHFFFAOYSA-N 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- XQWQNVHACLGSBB-UHFFFAOYSA-N [Si]([O-])([O-])([O-])O.[Yb+3] Chemical compound [Si]([O-])([O-])([O-])O.[Yb+3] XQWQNVHACLGSBB-UHFFFAOYSA-N 0.000 description 1
- WOIHABYNKOEWFG-UHFFFAOYSA-N [Sr].[Ba] Chemical compound [Sr].[Ba] WOIHABYNKOEWFG-UHFFFAOYSA-N 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 229910052863 mullite Inorganic materials 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 229910001233 yttria-stabilized zirconia Inorganic materials 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 1
Classifications
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
- F05D2300/6033—Ceramic matrix composites [CMC]
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Composite Materials (AREA)
Abstract
Description
本発明は、タービン構成要素に関する。詳細には、本発明は、内側シュラウド及び外側シュラウドを有するタービン構成要素に関する。 The present invention relates to turbine components. In particular, the present invention relates to a turbine component having an inner shroud and an outer shroud.
タービンエンジン及び発電システムのタービン構成要素の高温高圧動作によって効率改善及び新規な構成による運転が可能になる。このような高温高圧で動作可能な材料を選択することは困難である。このような材料は、桁違いに費用がかかり、生産が難しく、製作が難しい場合がある。さらに、このような種々の材料は、他の厄介な問題をもたらす冷却機構の変更を必要とする場合がある。 High temperature and high pressure operation of turbine components of turbine engines and power generation systems allows for improved efficiency and operation with new configurations. It is difficult to select a material that can operate at such high temperature and pressure. Such materials are orders of magnitude more expensive, difficult to produce, and sometimes difficult to manufacture. In addition, such various materials may require modification of the cooling mechanism that poses other complications.
一般に、より少ない材料を用いて同じ又は良好な動作を得ることが望ましい。より少ない材料を用いると重量が低減し、製造費用が安くなり、材料コストが安くなり、さらに他のいくつかの利点をもたらす。しかしながら、より少ない材料を用いることは、複雑な幾何学的要件を引き起こす場合、及び／又は応力等の従前では発生しなかった望ましくない力をもたらす場合がある。さらに、異なる材料を用いてより少ない材料を用いる場合、冷却機構に対して複雑な及び／又は費用のかかる変更が必要となる場合があり、これは他の厄介な問題をもたらす場合がある。 In general, it is desirable to obtain the same or better operation with less material. Using less material reduces weight, lowers manufacturing costs, lowers material costs, and provides several other advantages. However, using less material may cause complex geometric requirements and / or may result in undesirable forces that did not occur previously, such as stress. Furthermore, using less material with different materials may require complex and / or expensive changes to the cooling mechanism, which may lead to other complications.
従って、高温高圧に耐えること、より少ない量／重量で用いること、望ましくない力をもたらすことなく動作すること、複雑な及び／又は費用のかかる冷却機構を使用することなく動作条件で用いることができる材料を生産する継続的なニーズがある。 Thus, it can withstand high temperatures and pressures, be used in smaller amounts / weights, operate without undesired forces, and can be used in operating conditions without the use of complex and / or costly cooling mechanisms. There is an ongoing need to produce materials.
従来に比べて１つ又はそれ以上の改善点を示すタービン構成要素が望ましいであろう。 A turbine component that exhibits one or more improvements over the prior art would be desirable.
１つの実施形態において、タービン構成要素は、外側シュラウドと、外側シュラウドの第１の部分の上に広がる第１のフック領域及び外側シュラウドの第２の部分の上に広がる第２のフック領域を有する内側シュラウドとを備える。第１のフック領域及び第１の部分は第１のフック間隙を定め、第２のフック領域及び第２の部分は第２のフック間隙を定める。第１の半径方向間隙が、第１のフック間隙の反対側の第１のフック領域と、外側シュラウドとの間に広がり、第２の半径方向間隙が、第２のフック間隙の反対側の第２のフック領域と、外側シュラウドとの間に広がる。第１のフック間隙、第２のフック間隙、第１の半径方向間隙、及び第２の半径方向間隙は、熱負荷の下で内側シュラウドが外側シュラウドから偏位できるように構成及び配置される。 In one embodiment, the turbine component has an outer shroud, a first hook region extending over a first portion of the outer shroud and a second hook region extending over a second portion of the outer shroud. An inner shroud. The first hook region and the first portion define a first hook gap, and the second hook region and the second portion define a second hook gap. A first radial gap extends between the first hook region opposite the first hook gap and the outer shroud, and a second radial gap is the second opposite the second hook gap. 2 between the hook area and the outer shroud. The first hook gap, the second hook gap, the first radial gap, and the second radial gap are configured and arranged to allow the inner shroud to deviate from the outer shroud under a thermal load.
別の実施形態において、タービン構成要素は、外側シュラウドと、外側シュラウドの第１の部分の上に広がる第１のフック領域及び外側シュラウドの第２の部分の上に広がる第２のフック領域を有する内側シュラウドとを備える。内側シュラウドは、２００Ｗ／ｍ・ｋ未満で１０Ｗ／ｍ・ｋよりも大きい熱伝導率のセラミックスマトリックス複合材料繊維を含む。 In another embodiment, the turbine component has an outer shroud, a first hook region extending over a first portion of the outer shroud, and a second hook region extending over a second portion of the outer shroud. An inner shroud. The inner shroud includes ceramic matrix composite fibers with a thermal conductivity of less than 200 W / m · k and greater than 10 W / m · k.
別の実施形態において、タービン構成要素は、外側シュラウドと、外側シュラウドの第１の部分の上に広がる第１のフック領域及び外側シュラウドの第２の部分の上に広がる第２のフック領域を有する内側シュラウドとを備える。第１のフック領域及び第１の部分は第１のフック間隙を定め、第２のフック領域及び第２の部分は第２のフック間隙を定め、第１のフック間隙及び第２のフック間隙は、熱負荷の下で内側シュラウドが外側シュラウドから偏位できるように構成及び配置される。内側シュラウドは、２００Ｗ／ｍ・ｋ未満で１０Ｗ／ｍ・ｋよりも大きい熱伝導率のセラミックスマトリックス複合材料繊維を含む。 In another embodiment, the turbine component has an outer shroud, a first hook region extending over a first portion of the outer shroud, and a second hook region extending over a second portion of the outer shroud. An inner shroud. The first hook region and the first part define a first hook gap, the second hook region and the second part define a second hook gap, and the first hook gap and the second hook gap are , Constructed and arranged so that the inner shroud can be displaced from the outer shroud under heat load. The inner shroud includes ceramic matrix composite fibers with a thermal conductivity of less than 200 W / m · k and greater than 10 W / m · k.
本発明の他の特徴及び利点は、例証として本発明の原理を示す添付図面を参照しながら、以下のより詳細な説明から明らかになるであろう。 Other features and advantages of the present invention will become apparent from the following more detailed description, taken in conjunction with the accompanying drawings, illustrating by way of example the principles of the invention.
可能な限り、同じ要素を示すために図面全体を通じて同じ参照符号が使用される。 Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same elements.
タービン構成要素が提供される。本開示の実施形態は、例えば、本明細書で開示する特徴部の１つ又はそれ以上を含んでいないコンセプトに比べると、より簡単に補修又は交換ができ、高温高圧に耐えることができ、少ない量／重量で用いることができ、望ましくない力を生じることなく動作でき、複雑な及び／又は費用のかかる冷却機構を使用することなく動作条件で用いることができ、及び／又は漏れを少なくするために機械的に負荷をかけることができ、結果的にエンジン作動効率を高めるようになっている。 A turbine component is provided. Embodiments of the present disclosure can be repaired or replaced more easily, can withstand high temperatures and pressures, and are fewer than, for example, concepts that do not include one or more of the features disclosed herein To be used in volume / weight, can operate without creating undesirable forces, can be used in operating conditions without using complex and / or expensive cooling mechanisms, and / or to reduce leakage As a result, the engine operating efficiency is increased.
図１は、タービン構成要素１００の実施形態を示し、例えば、発電システム、タービンエンジン、又はその両方に使用することができる。タービン構成要素１００は、外側シュラウド１０１と、外側シュラウド１０１の第１の部分１０９に広がる第１のフック領域１０５及び外側シュラウド１０１の第２の部分１１１に広がる第２のフック領域１０７とを有する内側シュラウド１０３を有する。第１のフック領域１０５及び第１の部分１０９は、第１のフック間隙１１３を定め、第２のフック領域１０７及び第２の部分１１１は、第２のフック間隙１１５を定める。第１の半径方向間隙１１４は、第１のフック間隙１１３の反対側の第１のフック領域１０５と外側シュラウド１０１との間に延び、第２の半径方向間隙１１６は、第２のフック間隙１１５の反対側の第２のフック領域１０７と外側シュラウド１０１との間に延びる。 FIG. 1 illustrates an embodiment of a turbine component 100 that can be used, for example, in a power generation system, a turbine engine, or both. Turbine component 100 has an inner shroud 101 and an inner first hook region 105 that extends to a first portion 109 of outer shroud 101 and a second hook region 107 that extends to a second portion 111 of outer shroud 101. It has a shroud 103. The first hook region 105 and the first portion 109 define a first hook gap 113, and the second hook region 107 and the second portion 111 define a second hook gap 115. The first radial gap 114 extends between the first hook region 105 opposite the first hook gap 113 and the outer shroud 101 and the second radial gap 116 is the second hook gap 115. Extending between the second hook region 107 and the outer shroud 101 on the opposite side.
第１のフック間隙１１３、第２のフック間隙１１５、第１の半径方向間隙１１４、及び第２の半径方向間隙１１６は、熱負荷の下で内側シュラウド１０３が外側シュラウド１０１から偏位することができるように構成されて配置されている。 The first hook gap 113, the second hook gap 115, the first radial gap 114, and the second radial gap 116 may cause the inner shroud 103 to deviate from the outer shroud 101 under a thermal load. It is configured and arranged so that it can.
第１のフック間隙１１３、第２のフック間隙１１５、第１の半径方向間隙１１４、及び第２の半径方向間隙１１６は、タービン構成要素１００の運用時の応力を低減又はなくすように偏位可能な任意の幾何学的形状である。例えば、１つの実施形態において、適切な幾何学的形状は、内側シュラウド１０３の上に広がる立方形状の溝である。用語「フック」が用いられており、図１は、第１の湾曲部１０２、該第１の湾曲部１０２に隣接した第１の平面部１０４、該第１の平面部１０４に隣接した第２の湾曲部１０６、及び該第２の湾曲部１０６に隣接した第２の平面部１０８を示し、第２の平面部１０８は内側シュラウド及び高温ガス経路１１９に対して実質的に平行であるが、角度、アーチ形、カール形、曲線形、及び少なくとも３つの別の平面に広がる他の構成は、用語「フック」の範囲にあると見なされることを理解されたい。他の適切な幾何学的形状としては、限定されるものではないが、直方体、スロット、円筒の一部（例えば、半円筒）、平坦な又は略平坦な境界接続端部（ｂｏｒｄｅｒ ｃｏｎｎｅｃｔｉｎｇ ｅｎｄｓ）を備えたアーチ形、又は偏位を可能にする任意の他の幾何学的形状を挙げることができる。 First hook gap 113, second hook gap 115, first radial gap 114, and second radial gap 116 can be offset to reduce or eliminate stress during operation of turbine component 100. Any geometric shape. For example, in one embodiment, a suitable geometric shape is a cubic groove extending over the inner shroud 103. The term “hook” is used, and FIG. 1 illustrates a first curved portion 102, a first planar portion 104 adjacent to the first curved portion 102, and a second adjacent to the first planar portion 104. , And a second plane 108 adjacent to the second curve 106, the second plane 108 being substantially parallel to the inner shroud and hot gas path 119, It should be understood that angles, arches, curls, curves, and other configurations extending in at least three other planes are considered within the scope of the term “hook”. Other suitable geometric shapes include, but are not limited to, a rectangular parallelepiped, a slot, a portion of a cylinder (eg, a semi-cylinder), a flat or substantially flat border connecting ends. Mention may be made of an arched shape, or any other geometric shape that allows for deflection.
第１のフック領域１０５、第１の半径方向間隙１１４、及び第１の部分１０９は、後縁１２９に比べると前縁１２７に近接する。第２のフック領域１０７、第２の半径方向間隙１１６、及び第２の部分１１１は、前縁１２７に比べると後縁１２９に近接する。第１のフック領域１０５及び第２のフック領域１０７は、内側シュラウド１０３を外側シュラウド１０１に調整可能に固定する。１つの実施形態において、内側シュラウド１０３及び外側シュラウド１０１は、ボルト締めではなく、外側シュラウド１０１の第１の部分１０９に広がる第１のフック領域１０５及び外側シュラウド１０１の第２の部分１１１に広がる第２のフック領域１０７を利用して一緒に固定することができる。外側シュラウド１０１及び内側シュラウド１０３、並びに実施形態における複数の内側シュラウド１０３を備えた追加の内側シュラウドをさらにしっかり固定するために、任意の他の適切な力−付与機構を利用することができる。 The first hook region 105, the first radial gap 114, and the first portion 109 are closer to the leading edge 127 compared to the trailing edge 129. The second hook region 107, the second radial gap 116, and the second portion 111 are closer to the trailing edge 129 than the leading edge 127. The first hook area 105 and the second hook area 107 fixably adjust the inner shroud 103 to the outer shroud 101. In one embodiment, the inner shroud 103 and the outer shroud 101 are not bolted, but a first hook region 105 that extends to the first portion 109 of the outer shroud 101 and a second portion 111 that extends to the second portion 111 of the outer shroud 101. The two hook regions 107 can be used to fix together. Any other suitable force-applying mechanism can be utilized to further secure the outer shroud 101 and inner shroud 103, and additional inner shrouds with multiple inner shrouds 103 in embodiments.
１つの実施形態において、選択材料と併せて、外側シュラウド１０１及び内側シュラウド１０３の構成は、内側シュラウド１０３を外側シュラウド１０１から選択的に取り外すこと、補修すること、及び／又は交換することを可能にする。例えば、１つの実施形態において、内側シュラウド１０３及び外側シュラウド１０１は、タービン構成要素１００の適切な動作条件下では結合しない。本明細書で用いる場合、用語「結合（ｂｉｎｄ）」は、例えば、第２の平面部１０８の上での外側シュラウド１０１の局所的な降伏又は変形を呼ぶ。適切な動作条件は、限定されるものではないが、約１２００°Ｆから３２００°Ｆ以上（約６５０°Ｃから１７６０°Ｃ以上）である。 In one embodiment, the configuration of the outer shroud 101 and the inner shroud 103, in conjunction with the selected material, allows the inner shroud 103 to be selectively removed from the outer shroud 101, repaired, and / or replaced. To do. For example, in one embodiment, inner shroud 103 and outer shroud 101 do not couple under the proper operating conditions of turbine component 100. As used herein, the term “bind” refers to, for example, local yielding or deformation of the outer shroud 101 on the second planar portion 108. Suitable operating conditions include, but are not limited to, about 1200 ° F. to 3200 ° F. or more (about 650 ° C. to 1760 ° C. or more).
内側シュラウド１０３及び外側シュラウド１０１は、発電システム、タービンエンジン、又はタービン構成要素１００を利用する任意の他のシステムの動作条件で使用することができる任意の材料を含むことができる。１つの実施形態において、外側シュラウド１０１はニッケルベース合金、又はステンレス鋼等の金属又は金属材料を含む。１つの実施形態において、内側シュラウド１０３は、セラミックスマトリックス複合材料を含む。本明細書で用いる場合、用語「セラミックスマトリックス複合材料」は、限定されるものではないが、炭素繊維強化炭素（Ｃ／Ｃ）、炭素繊維強化炭化ケイ素（Ｃ／ＳｉＣ）、炭化ケイ素繊維強化炭化ケイ素（ＳｉＣ／ＳｉＣ）、及び炭化ケイ素繊維強化酸化物マトリックス複合材料を含む。１つの実施形態において、セラミックスマトリックス複合材料は、モノリシックセラミック構造に比べて、高い伸び率、破壊靱性、熱衝撃、動荷重性能、及び異方特性を有する。１つの適切なセラミックスマトリックス複合材料は、Ｓｉ−Ｃ繊維及びＳｉＣ−マトリックスを含み、例えば、セラミックスマトリックス複合材料のＳｉ−Ｃ繊維の体積濃度は、少なくとも約２０％、例えば、少なくとも約２３％、少なくとも約２８％、少なくとも約３０％、約２３％から約３２％の間、又は任意の適切な組み合わせ、部分的組み合わせ、範囲、又はその中の部分的範囲である。 Inner shroud 103 and outer shroud 101 can include any material that can be used in the operating conditions of a power generation system, turbine engine, or any other system that utilizes turbine component 100. In one embodiment, the outer shroud 101 comprises a nickel-based alloy or a metal or metal material such as stainless steel. In one embodiment, the inner shroud 103 comprises a ceramic matrix composite material. As used herein, the term “ceramic matrix composite” includes, but is not limited to, carbon fiber reinforced carbon (C / C), carbon fiber reinforced silicon carbide (C / SiC), silicon carbide fiber reinforced carbonized. Includes silicon (SiC / SiC) and silicon carbide fiber reinforced oxide matrix composites. In one embodiment, the ceramic matrix composite has higher elongation, fracture toughness, thermal shock, dynamic load performance, and anisotropic properties compared to a monolithic ceramic structure. One suitable ceramic matrix composite includes Si-C fibers and SiC-matrix, for example, the volume concentration of Si-C fibers in the ceramic matrix composite is at least about 20%, such as at least about 23%, at least About 28%, at least about 30%, between about 23% and about 32%, or any suitable combination, subcombination, range, or subrange therein.
内側シュラウド１０３の材料は、タービン構成要素１００に関する熱伝導率の選択範囲を可能にするように選択される。１つの実施形態において、内側シュラウド１０３及び／又は内側シュラウド１０３の材料の熱伝導率は、２００Ｗ／ｍ・ｋ未満、１５０Ｗ／ｍ・ｋ未満、１４０Ｗ／ｍ・ｋ未満、１３０Ｗ／ｍ・ｋ未満、又は任意の適切な組み合わせ、部分的組み合わせ、範囲、又はその中の部分的範囲である。追加的に又は代替的に、１つの実施形態において、内側シュラウド１０３及び／又は内側シュラウド１０３の材料の熱伝導率は、１０Ｗ／ｍ・ｋより大きく５０Ｗ／ｍ・ｋ未満、１００Ｗ／ｍ・ｋより大きく１１０Ｗ／ｍ・ｋ未満、又は任意の適切な組み合わせ、部分的組み合わせ、範囲、又はその中の部分的範囲である。１つの実施形態において、熱伝導率は１２０Ｗ／ｍ・ｋである。 The material of the inner shroud 103 is selected to allow a select range of thermal conductivity for the turbine component 100. In one embodiment, the thermal conductivity of the inner shroud 103 and / or the material of the inner shroud 103 is less than 200 W / m · k, less than 150 W / m · k, less than 140 W / m · k, less than 130 W / m · k. Or any suitable combination, subcombination, range, or subrange therein. Additionally or alternatively, in one embodiment, the thermal conductivity of the inner shroud 103 and / or the material of the inner shroud 103 is greater than 10 W / m · k and less than 50 W / m · k, 100 W / m · k. Greater than 110 W / m · k, or any suitable combination, subcombination, range, or subrange therein. In one embodiment, the thermal conductivity is 120 W / m · k.
内側シュラウド１０３及び／又は外側シュラウド１０１は、熱負荷の下で偏位に悪影響を与えない任意の他の適切な特徴部を含む。例えば、１つの実施形態において、外側シュラウド１０１は、流体（例えば、空気又は圧縮空気）が流れることが可能な内部空洞１１７を有する。内部空洞１１７は、例えば、タービン構成要素１００の円周面上のスプラインシール、並びに前縁１２７及び／又は後縁１２９上のコンプライアントシールによってシールすることができる。１つの実施形態において、内部空洞１１７は、例えば、動作圧力及び／又は外側シュラウド１０１に対する内側シュラウド１０３の遠位部の端から端までを横切る高温ガス経路１１９の圧力まで、又はその圧力以上に加圧される。１つの実施形態において、横方向間隙１２１は、内側シュラウド１０３と外側シュラウド１０１との間を第１のフック領域１０５から第２のフック領域１０７まで平行に、実質的に平行に、又は接線方向に延び、内側シュラウド１０３から外側シュラウド１０１への熱伝達を可能にする。別の実施形態において、インピンジメントプレート１２３は、内側シュラウド１０３と外側シュラウド１０１との間に配置される。インピンジメントプレート１２３は、内側シュラウド１０３と同一の、類似の、又はこれとは異なる材料を含み、熱を内部空洞１１７に伝達することで冷却機能をもたらす。 Inner shroud 103 and / or outer shroud 101 include any other suitable feature that does not adversely affect excursion under thermal load. For example, in one embodiment, the outer shroud 101 has an internal cavity 117 through which fluid (eg, air or compressed air) can flow. The internal cavity 117 can be sealed by, for example, a spline seal on the circumferential surface of the turbine component 100 and a compliant seal on the leading edge 127 and / or the trailing edge 129. In one embodiment, the internal cavity 117 can be applied, for example, to operating pressure and / or to the pressure of the hot gas path 119 across the distal portion of the inner shroud 103 relative to the outer shroud 101, or higher. Pressed. In one embodiment, the lateral gap 121 is parallel, substantially parallel, or tangentially from the first hook region 105 to the second hook region 107 between the inner shroud 103 and the outer shroud 101. Extending to allow heat transfer from the inner shroud 103 to the outer shroud 101. In another embodiment, the impingement plate 123 is disposed between the inner shroud 103 and the outer shroud 101. The impingement plate 123 includes the same, similar, or different material as the inner shroud 103 and provides heat to the internal cavity 117 to provide a cooling function.
内側シュラウド１０３は、高温ガス経路１１９の内部の高温ガスに接触するように配置されることでもたらされる温度及び圧力等の動作パラメータに対応する任意の適切な特徴部を含む。例えば、１つの実施形態において、内側シュラウド１０３は、高温ガス経路１１９の高温ガスと接触するように配置された内側シュラウド１０３の一部又は全ての表面上に設けられた環境障壁コーティング１２５を含む。環境障壁コーティング１２５は、高温ガス経路１１９で動作可能な任意の適切なコーティングである。１つの実施形態において、翼端間隙に対応するために、高温ガス経路１１９の中の内側シュラウド１０３上には摩耗性摩擦コーティング（図示せず）が設けられている。環境障壁コーティング１２５及び／又は摩耗性摩擦コーティングの材料としては、限定されるものではないが、バリウムストロンチウムアルミナ珪酸塩、ムライト、イットリア安定化ジルコニア、イットリアモノシリケート及びジシリケート、イッテルビウムモノシリケート及びジシリケート、及びこれらを組み合わせたものを挙げることができる。 Inner shroud 103 includes any suitable features corresponding to operating parameters such as temperature and pressure resulting from being placed in contact with the hot gas inside hot gas path 119. For example, in one embodiment, the inner shroud 103 includes an environmental barrier coating 125 provided on some or all surfaces of the inner shroud 103 that are arranged to contact the hot gas in the hot gas path 119. Environmental barrier coating 125 is any suitable coating operable in hot gas path 119. In one embodiment, an abrasive friction coating (not shown) is provided on the inner shroud 103 in the hot gas path 119 to accommodate the tip clearance. Materials for the environmental barrier coating 125 and / or the abrasive friction coating include, but are not limited to, barium strontium alumina silicate, mullite, yttria stabilized zirconia, yttria monosilicate and disilicate, ytterbium monosilicate and disilicate, and A combination of these can be mentioned.
本発明は、１つ又はそれ以上の実施形態を参照して説明されているが、当業者であれば、本発明の範囲から逸脱することなく種々の変形を行うこと及びその要素の均等物を提起できることを理解できるはずである。さらに、本発明の本質的な範囲から逸脱することなく、特定の状況又は物的事項を本発明の教示に適合するように多くの修正を行うことができる。従って、本発明は、本発明を実施するために企図される最良の形態として開示した特定の実施形態に限定されるものではなく、また本発明は、添付の特許請求の範囲の技術的範囲内に属する全ての実施形態を包含することを意図している。 Although the invention has been described with reference to one or more embodiments, those skilled in the art will recognize that various modifications and equivalents of the elements can be made without departing from the scope of the invention. You should understand what you can raise. In addition, many modifications may be made to adapt a particular situation or material matter to the teachings of the invention without departing from the essential scope thereof. Accordingly, the invention is not limited to the specific embodiments disclosed as the best mode contemplated for carrying out the invention, and the invention is within the scope of the appended claims. It is intended to encompass all embodiments belonging to.
１００ タービン構成要素
１０１ 外側シュラウド
１０２ 第１の湾曲部
１０３ 内側シュラウド
１０４ 第１の平面部
１０５ 第１のフック領域
１０６ 第２の湾曲部
１０７ 第２のフック領域
１０８ 第２の平面部
１０９ 第１の部分
１１１ 第２の部分
１１３ 第１のフック間隙
１１４ 第１の半径方向間隙
１１５ 第２のフック間隙
１１６ 第２の半径方向間隙
１１７ 内部空洞
１１９ 高温ガス経路
１２１ 横方向間隙
１２３ インピンジメントプレート
１２５ 環境障壁コーティング
１２７ 前縁
１２９ 後縁
100 turbine component 101 outer shroud 102 first curved portion 103 inner shroud 104 first flat portion 105 first hook region 106 second curved portion 107 second hook region 108 second flat portion 109 first Portion 111 second portion 113 first hook gap 114 first radial gap 115 second hook gap 116 second radial gap 117 internal cavity 119 hot gas path 121 lateral gap 123 impingement plate 125 environmental barrier Coating 127 Leading edge 129 Trailing edge
Claims (20)
前記外側シュラウド（１０１）の第１の部分（１０９）の上に広がる第１のフック領域（１０５）及び前記外側シュラウド（１０１）の第２の部分（１１１）の上に広がる第２のフック領域（１０７）を有する内側シュラウド（１０３）と、
を備えるタービン構成要素（１００）であって、
前記第１のフック領域（１０５）及び前記第１の部分（１０９）は第１のフック間隙（１１３）を定め、前記第２のフック領域（１０７）及び前記第２の部分（１１１）は第２のフック間隙（１１５）を定め、
第１の半径方向間隙（１１４）が、前記第１のフック間隙（１１３）の反対側の前記第１のフック領域（１０５）と、前記外側シュラウド（１０１）との間に広がり、第２の半径方向間隙（１１６）が、前記第２のフック間隙（１１５）の反対側の前記第２のフック領域（１０７）と、前記外側シュラウド（１０１）との間に広がり、
前記第１のフック間隙（１１３）、前記第２のフック間隙（１１５）、前記第１の半径方向間隙（１１４）、及び前記第２の半径方向間隙（１１６）は、熱負荷の下で前記内側シュラウド（１０３）が前記外側シュラウド（１０１）から偏位できるように構成及び配置される、タービン構成要素。 An outer shroud (101);
A first hook region (105) extending over a first portion (109) of the outer shroud (101) and a second hook region extending over a second portion (111) of the outer shroud (101) An inner shroud (103) having (107);
A turbine component (100) comprising:
The first hook region (105) and the first portion (109) define a first hook gap (113), and the second hook region (107) and the second portion (111) are first Two hook gaps (115)
A first radial gap (114) extends between the first hook region (105) opposite the first hook gap (113) and the outer shroud (101), and a second A radial gap (116) extends between the second hook region (107) opposite the second hook gap (115) and the outer shroud (101);
The first hook gap (113), the second hook gap (115), the first radial gap (114) and the second radial gap (116) are A turbine component configured and arranged such that an inner shroud (103) can be offset from said outer shroud (101).
前記外側シュラウド（１０１）の第１の部分（１０９）の上に広がる第１のフック領域（１０５）及び前記外側シュラウド（１０１）の第２の部分（１１１）の上に広がる第２のフック領域（１０７）を有する内側シュラウド（１０３）と、
を備えるタービン構成要素（１００）であって、
前記内側シュラウド（１０３）は、２００Ｗ／ｍ・ｋ未満で１０Ｗ／ｍ・ｋよりも大きい熱伝導率のセラミックスマトリックス複合材料繊維を含む、タービン構成要素。 An outer shroud (101);
A first hook region (105) extending over a first portion (109) of the outer shroud (101) and a second hook region extending over a second portion (111) of the outer shroud (101) An inner shroud (103) having (107);
A turbine component (100) comprising:
The inner shroud (103) comprises a turbine component comprising ceramic matrix composite fibers having a thermal conductivity of less than 200 W / m · k and greater than 10 W / m · k.
前記外側シュラウド（１０１）の第１の部分（１０９）の上に広がる第１のフック領域（１０５）及び前記外側シュラウド（１０１）の第２の部分（１１１）の上に広がる第２のフック領域（１０７）を有する内側シュラウド（１０３）と、
を備えるタービン構成要素（１００）であって、
前記第１のフック領域（１０５）及び前記第１の部分（１０９）は第１のフック間隙（１１３）を定め、前記第２のフック領域（１０７）及び前記第２の部分（１１１）は第２のフック間隙（１１５）を定め、前記第１のフック間隙（１１３）及び前記第２のフック間隙（１１５）は、熱負荷の下で前記内側シュラウド（１０３）が前記外側シュラウド（１０１）から偏位できるように構成及び配置され、
前記内側シュラウド（１０３）は、２００Ｗ／ｍ・ｋ未満で１０Ｗ／ｍ・ｋよりも大きい熱伝導率のセラミックスマトリックス複合材料繊維を含む、タービン構成要素。
An outer shroud (101);
A first hook region (105) extending over a first portion (109) of the outer shroud (101) and a second hook region extending over a second portion (111) of the outer shroud (101) An inner shroud (103) having (107);
A turbine component (100) comprising:
The first hook region (105) and the first portion (109) define a first hook gap (113), and the second hook region (107) and the second portion (111) are first Two hook gaps (115), and the first hook gap (113) and the second hook gap (115) are arranged so that the inner shroud (103) is separated from the outer shroud (101) under a heat load. Constructed and arranged so that it can be displaced,
The inner shroud (103) comprises a turbine component comprising ceramic matrix composite fibers having a thermal conductivity of less than 200 W / m · k and greater than 10 W / m · k.
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| JPH10331602A (en) * | 1997-05-29 | 1998-12-15 | Toshiba Corp | Gas turbine |
| US20030133790A1 (en) * | 2002-01-16 | 2003-07-17 | Darkins Toby George | Turbine shroud segment and shroud assembly |
| US20040047726A1 (en) * | 2002-09-09 | 2004-03-11 | Siemens Westinghouse Power Corporation | Ceramic matrix composite component for a gas turbine engine |
| US20050232752A1 (en) * | 2004-04-15 | 2005-10-20 | David Meisels | Turbine shroud cooling system |
| US20100074745A1 (en) * | 2008-09-19 | 2010-03-25 | Daniel Vern Jones | Dual stage turbine shroud |
| US20120076927A1 (en) * | 2010-02-01 | 2012-03-29 | United States Government As Represented By The Secretary Of The Army | Method of improving the thermo-mechanical properties of fiber-reinforced silicon carbide matrix composites |
| JP2012077743A (en) * | 2010-09-30 | 2012-04-19 | General Electric Co <Ge> | Low-ductility open channel turbine shroud |
| JP2013504003A (en) * | 2009-09-04 | 2013-02-04 | ターボメカ | Devices supporting turbine rings, turbines having such devices, and turbine engines having such turbines |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10204860A1 (en) * | 2002-02-06 | 2003-08-14 | Man Technologie Gmbh | Fiber composite ceramic material, used e.g. for heat engine, heat exchanger, hot gas pipe or nozzle or plasma containing vessel, has heat-conducting three-dimensional fabric with silicon carbide matrix produced in three stages |
| US7090459B2 (en) * | 2004-03-31 | 2006-08-15 | General Electric Company | Hybrid seal and system and method incorporating the same |
-
2014
- 2014-06-02 US US14/292,985 patent/US20150345308A1/en not_active Abandoned
-
2015
- 2015-05-19 DE DE102015107848.1A patent/DE102015107848A1/en active Pending
- 2015-05-26 JP JP2015105952A patent/JP6979751B2/en active Active
- 2015-05-27 CH CH00753/15A patent/CH709761B1/en unknown
- 2015-06-02 CN CN201510294617.3A patent/CN105275513B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10331602A (en) * | 1997-05-29 | 1998-12-15 | Toshiba Corp | Gas turbine |
| US20030133790A1 (en) * | 2002-01-16 | 2003-07-17 | Darkins Toby George | Turbine shroud segment and shroud assembly |
| US20040047726A1 (en) * | 2002-09-09 | 2004-03-11 | Siemens Westinghouse Power Corporation | Ceramic matrix composite component for a gas turbine engine |
| US20050232752A1 (en) * | 2004-04-15 | 2005-10-20 | David Meisels | Turbine shroud cooling system |
| US20100074745A1 (en) * | 2008-09-19 | 2010-03-25 | Daniel Vern Jones | Dual stage turbine shroud |
| JP2013504003A (en) * | 2009-09-04 | 2013-02-04 | ターボメカ | Devices supporting turbine rings, turbines having such devices, and turbine engines having such turbines |
| US20120076927A1 (en) * | 2010-02-01 | 2012-03-29 | United States Government As Represented By The Secretary Of The Army | Method of improving the thermo-mechanical properties of fiber-reinforced silicon carbide matrix composites |
| JP2012077743A (en) * | 2010-09-30 | 2012-04-19 | General Electric Co <Ge> | Low-ductility open channel turbine shroud |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2017172584A (en) * | 2016-03-24 | 2017-09-28 | ゼネラル・エレクトリック・カンパニイ | Apparatus and method for forming apparatus |
| JP7102101B2 (en) | 2016-03-24 | 2022-07-19 | ゼネラル・エレクトリック・カンパニイ | Equipment and device formation method |
| KR20180136896A (en) | 2017-06-15 | 2018-12-26 | 제네럴 일렉트릭 컴퍼니 | Turbine shroud assembly |
| JP2019002403A (en) * | 2017-06-15 | 2019-01-10 | ゼネラル・エレクトリック・カンパニイ | Turbine shroud assembly |
| JP7195772B2 (en) | 2017-06-15 | 2022-12-26 | ゼネラル・エレクトリック・カンパニイ | turbine shroud assembly |
| KR102644723B1 (en) * | 2017-06-15 | 2024-03-06 | 제네럴 일렉트릭 컴퍼니 | Turbine shroud assembly |
| WO2019215913A1 (en) | 2018-05-11 | 2019-11-14 | 川崎重工業株式会社 | Shroud assembly for gas turbine |
| US11236629B2 (en) | 2018-05-11 | 2022-02-01 | Kawasaki Jukogyo Kabushiki Kaisha | Shroud assembly of gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CH709761B1 (en) | 2019-07-15 |
| DE102015107848A1 (en) | 2015-12-03 |
| CN105275513A (en) | 2016-01-27 |
| CN105275513B (en) | 2018-07-24 |
| US20150345308A1 (en) | 2015-12-03 |
| JP6979751B2 (en) | 2021-12-15 |
| CH709761A2 (en) | 2015-12-15 |
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