JP6431718B2 - Airfoil for turbine system - Google Patents
Airfoil for turbine system Download PDFInfo
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- JP6431718B2 JP6431718B2 JP2014159963A JP2014159963A JP6431718B2 JP 6431718 B2 JP6431718 B2 JP 6431718B2 JP 2014159963 A JP2014159963 A JP 2014159963A JP 2014159963 A JP2014159963 A JP 2014159963A JP 6431718 B2 JP6431718 B2 JP 6431718B2
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- 239000000463 material Substances 0.000 claims description 46
- 238000001816 cooling Methods 0.000 claims description 31
- 229910045601 alloy Inorganic materials 0.000 claims description 26
- 239000000956 alloy Substances 0.000 claims description 26
- 239000000758 substrate Substances 0.000 claims description 25
- 238000000034 method Methods 0.000 claims description 16
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 8
- 238000002485 combustion reaction Methods 0.000 claims description 8
- 239000012530 fluid Substances 0.000 claims description 8
- 229910000601 superalloy Inorganic materials 0.000 claims description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 5
- 238000005304 joining Methods 0.000 claims description 5
- 239000010941 cobalt Substances 0.000 claims description 4
- 229910017052 cobalt Inorganic materials 0.000 claims description 4
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 229910052759 nickel Inorganic materials 0.000 claims description 4
- 239000000446 fuel Substances 0.000 claims description 3
- 229910052742 iron Inorganic materials 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 239000002245 particle Substances 0.000 description 6
- 238000002844 melting Methods 0.000 description 5
- 230000008018 melting Effects 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- 238000005219 brazing Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000009760 electrical discharge machining Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000005245 sintering Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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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
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F01D5/005—Repairing methods or devices
-
- 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
- F01D5/186—Film cooling
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/22—Manufacture essentially without removing material by sintering
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49318—Repairing or disassembling
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
本明細書に開示される主題はエアフォイルに関し、より詳細にはエアフォイル、特にタービンシステム内のエアフォイルの後縁補助構造に関する。 The subject matter disclosed herein relates to airfoils, and more particularly to airfoils, and more particularly to airfoil trailing edge assist structures in turbine systems.
様々なタービンシステムで用いられるエアフォイルは、バケット及びノズルとして形成される。通常、熱ガス又は蒸気などの作動流体は、エアフォイルを横断するように送り込まれ、バケットがタービンシステムの回転子に結合する。バケットにかかる作動流体の力によって、バケットと、従って回転子との結合体が回転する。このように、エアフォイルの空気力学的配列が、タービンシステムのシステム性能全体に影響を及ぼす。鋳造など様々な製造工程を用いてエアフォイルを形成することが可能であるが、こうした工程はある側面で制限があり、一つの制限が、製造後のエアフォイルの空気力学的特性に関する。 Airfoil used in various turbine systems is formed as buckets and nozzles. Typically, a working fluid such as hot gas or steam is pumped across the airfoil and the bucket is coupled to the rotor of the turbine system. Due to the force of the working fluid acting on the bucket, the combination of the bucket and thus the rotor is rotated. Thus, the aerodynamic arrangement of the airfoil affects the overall system performance of the turbine system. Although various manufacturing processes such as casting can be used to form the airfoil, such processes are limited in certain aspects, and one limitation relates to the aerodynamic properties of the manufactured airfoil.
エアフォイルは通常、タービン動作温度及び動作条件に対して耐性がある所望の機械的及び環境的特性を有したニッケル系、コバルト系又は鉄系超合金から形成される。タービンシステムの効率はその動作温度に依存するので、エアフォイルが、ますます上昇する温度に耐えることができることが望まれている。超合金成分の最高局所温度がその超合金の融点に近づくにつれ、強制空冷が必要となる。このため、ガスタービンのバケット及びノズルのエアフォイルではしばしば、蒸気又は空気、典型的には抽気をエアフォイル内の内部冷却経路に強制的に送り込み、その後エアフォイル面にある冷却孔を通って排気させ、成分から熱を移動させるという複雑な冷却スキームが必要となる。 The airfoil is typically formed from a nickel-based, cobalt-based or iron-based superalloy having the desired mechanical and environmental properties that are resistant to turbine operating temperatures and operating conditions. Since the efficiency of a turbine system depends on its operating temperature, it is desirable for the airfoil to be able to withstand increasing temperatures. As the maximum local temperature of the superalloy component approaches the melting point of the superalloy, forced air cooling is required. For this reason, gas turbine buckets and nozzle airfoils often force steam or air, typically bleed, into an internal cooling path in the airfoil and then exhaust through cooling holes in the airfoil surface. Complex cooling schemes are required to transfer heat from the components.
上記の通り、エアフォイル製造に用いられる工程は幾分制限があり、このことが冷却経路の位置と寸法の両方に関する精度に影響を及ぼす。 As mentioned above, the process used for airfoil manufacturing is somewhat limited, which affects the accuracy with respect to both the location and dimensions of the cooling path.
本発明の一つの態様によれば、エアフォイルは基材からなる主要部を含む。また、主要部の後縁領域を含む。更に、後縁領域に近接して、基材と動作可能に結合される少なくとも１つの予備焼結予備成形（ＰＳＰ）材料を含む後縁補助構造を含む。 According to one embodiment of the present invention, the airfoil includes a main portion made of a base material. In addition, it includes a trailing edge region of the main part. In addition, a trailing edge assist structure is included that includes at least one pre-sintered preformed (PSP) material operatively coupled to the substrate proximate the trailing edge region.
本発明の別の態様によれば、タービンシステムはエアフォイルを含む。また、前縁から後縁領域まで延び、基材からなる、エアフォイルの主要部を含む。更に、後縁領域に近接して、主要部の基材と結合される第１のＰＳＰ材料と第２のＰＳＰ材料を含む後縁補助構造を含む。また更に、後縁補助構造内に少なくとも１つの冷却経路を含む。 According to another aspect of the invention, the turbine system includes an airfoil. Further, it includes a main part of the airfoil extending from the front edge to the rear edge region and made of a base material. In addition, a trailing edge assist structure is included that includes a first PSP material and a second PSP material that are bonded to the main substrate in proximity to the trailing edge region. Still further, at least one cooling path is included in the trailing edge assist structure.
本発明の更に別の態様によれば、エアフォイルの後縁領域を修理する方法が提供される。方法は、エアフォイルの後縁領域に近接する材料を除去することを含む。方法はまた、後縁領域の基材を露出させることを含む。方法は更に、少なくとも１つのＰＳＰ材料を基材に結合させることを含む。方法はまた更に、少なくとも１つのＰＳＰ材料を基材に接合した後、後縁補助構造を形成することを含む。 According to yet another aspect of the invention, a method for repairing a trailing edge region of an airfoil is provided. The method includes removing material proximate the trailing edge region of the airfoil. The method also includes exposing the substrate in the trailing edge region. The method further includes bonding at least one PSP material to the substrate. The method still further includes forming a trailing edge assist structure after bonding the at least one PSP material to the substrate.
本発明の上記の及びその他の利点及び特徴は、以下の図面と併せてなされた説明から、より明らかになろう。 These and other advantages and features of the invention will become more apparent from the description taken in conjunction with the following drawings.
主題は本発明とみなされるが、この主題は明細書の最後にある特許請求の範囲で特に指摘され明確に特許請求されるものである。本発明の上記及びその他の特徴並びに利点は、以下の添付の図面と併せてなされた詳細な説明から明確である。 The subject matter is considered as the invention, but this subject matter is particularly pointed out and distinctly claimed in the claims at the end of the specification. The above and other features and advantages of the present invention will be apparent from the detailed description taken in conjunction with the accompanying drawings in which:
詳細な説明では、一例として図面を参照しながら、本発明の実施形態を利点及び特徴とともに説明する。 The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
図１を参照すると、本発明の一例としての実施形態において構築されるタービンシステム１０の概略図が示されている。図示のタービンシステム１０は、ガスタービンエンジンを備えるが、本明細書に記載する実施形態を代替のシステム、例えば蒸気タービンなどにおいて用いることも可能であることを理解されたい。図示及び説明のために、ガスタービンエンジンに言及していく。 Referring to FIG. 1, a schematic diagram of a turbine system 10 constructed in an exemplary embodiment of the present invention is shown. Although the illustrated turbine system 10 comprises a gas turbine engine, it should be understood that the embodiments described herein may be used in alternative systems, such as a steam turbine. For illustration and explanation, reference will be made to a gas turbine engine.
ガスタービンエンジン１０は、圧縮部１２と、缶形環状アレイに配置された複数の燃焼器アセンブリを含み、燃焼器アセンブリの一つが参照符号１４で示され、燃焼器アセンブリ１４は燃焼部１８を含む。本発明は、燃焼系の詳細とは無関係であり、缶形環状システムに言及するのは本発明を説明するためである。燃料及び圧縮空気が燃焼部１８内に送られ、着火して、タービン部２４を駆動するのに用いられる高温高圧燃焼生成物又は蒸気が生成される。タービン部２４は、回転子３０を介して圧縮部１２に動作可能に接続された複数段２６から２８を含む。特に、複数段２６から２８は各々、ノズル３２とバケット３４を含み、バケット３４は動作可能に回転子３０に結合される。複数段２６から２８各々のノズル３２とバケット３４は、作動流体（例えば混合気）が上方を流れるエアフォイルである。３段と特定しているが、段数は３段より多くても少なくてもよいことを理解されたい。 The gas turbine engine 10 includes a compression section 12 and a plurality of combustor assemblies arranged in a can-shaped annular array, one of the combustor assemblies is indicated by reference numeral 14 and the combustor assembly 14 includes a combustion section 18. . The present invention is independent of the details of the combustion system, and reference to a can-annular system is for purposes of illustrating the present invention. Fuel and compressed air are sent into the combustion section 18 and ignited to produce high temperature and high pressure combustion products or steam used to drive the turbine section 24. The turbine section 24 includes multiple stages 26 to 28 that are operatively connected to the compression section 12 via a rotor 30. In particular, each of the plurality of stages 26 to 28 includes a nozzle 32 and a bucket 34, which is operatively coupled to the rotor 30. Each of the nozzles 32 and the buckets 34 in the plurality of stages 26 to 28 is an airfoil through which a working fluid (for example, an air-fuel mixture) flows. Although identified as three stages, it should be understood that the number of stages may be more or less than three.
次に図２を参照すると、ノズル３２又はバケット３４のいずれかを示すエアフォイル３６がより詳細に示されている。エアフォイル３６は、前縁４０から後縁領域４２まで延びる主要部３８を含む。主要部３８は基材から形成されるが、基材は特定の用途に応じて変更することができる。幾つかの実施形態において、基材は、ニッケル系、コバルト系又は鉄系超合金を含む。主要部３８は、例えばガスタービンエンジン内などで受ける高温高圧に耐性があるように等軸、方向性凝固（ＤＳ）又は単結晶（ＳＸ）鋳造として形成することができる。後縁領域４２は比較的丸く、後縁領域後部幅４４となる。 Referring now to FIG. 2, the airfoil 36 showing either the nozzle 32 or the bucket 34 is shown in more detail. The airfoil 36 includes a main portion 38 that extends from the leading edge 40 to the trailing edge region 42. The main portion 38 is formed of a base material, but the base material can be changed according to a specific application. In some embodiments, the substrate comprises a nickel-based, cobalt-based or iron-based superalloy. The main part 38 can be formed as equiaxed, directional solidification (DS) or single crystal (SX) casting so as to be resistant to the high temperature and pressure experienced, for example, in a gas turbine engine. The trailing edge region 42 is relatively round and has a trailing edge region rear width 44.
エアフォイル３６はまた、後縁領域４２の一面に近接し、主要部３８に動作可能に結合される後縁補助構造４６を含む。図示のように、後縁補助構造４６は主要部３８に対してテーパ状をなし、より細く、より鋭角な端部となっており、本明細書では後縁補助構造後部幅４８と称する寸法となる。 The airfoil 36 also includes a trailing edge assist structure 46 proximate to one side of the trailing edge region 42 and operably coupled to the main portion 38. As shown, the trailing edge assist structure 46 is tapered with respect to the main portion 38, has a narrower, sharper end, and is referred to herein as a trailing edge assist structure rear width 48. Become.
図３と図４を参照すると、主要部３８の後縁領域４２及び後縁補助構造４６がより詳細に示されている。図示の実施形態において、後縁補助構造４６は、本明細書ではＰＳＰシート５０と称する第１のＰＳＰ材料と、本明細書ではＰＳＰシート５２と称する第２のＰＳＰ材料を含み、ＰＳＰシート５０と５２は各々、予備焼結予備成形（ＰＳＰ）構造である。ＰＳＰシート、即ち第１のＰＳＰシート５０と第２のＰＳＰシート５２は各々、第１と第２の合金を含む粒子混合物を含み、第１と第２の合金は、融点より低い温度でともに焼結されて凝集体でやや多孔質の塊を形成する。粉末粒子の好適な粒径の範囲は、１５０メッシュ又は更に３２５メッシュかそれ以下で、粒子の急速焼結を促進させ、ＰＳＰシート内の多孔度を１０体積％以下に低下させるようにする。 Referring to FIGS. 3 and 4, the trailing edge region 42 and trailing edge assist structure 46 of the main portion 38 are shown in more detail. In the illustrated embodiment, the trailing edge assist structure 46 includes a first PSP material, referred to herein as a PSP sheet 50, and a second PSP material, referred to herein as a PSP sheet 52, Each 52 is a pre-sintered preform (PSP) structure. The PSP sheets, i.e., the first PSP sheet 50 and the second PSP sheet 52, each include a particle mixture including the first and second alloys, and the first and second alloys are both fired at a temperature below the melting point. Combined to form a slightly porous mass with aggregates. A suitable particle size range for the powder particles is 150 mesh or even 325 mesh or less, which promotes rapid sintering of the particles and reduces the porosity within the PSP sheet to 10 volume percent or less.
第１のＰＳＰシート５０及び第２のＰＳＰシート５２の第１の合金は、主要部３８の基材に類似する任意の組成を含み、ＰＳＰシートと主要部３８とがより共通の物性を示すようにする。例えば、幾つかの実施形態では、第１の合金と基材は共通の組成を共有する（即ち、第１の合金と基材は同種の材料である）。幾つかの実施形態において、第１の合金は、ニッケル系超合金又はコバルト系超合金を含む。幾つかの実施形態では、第１の合金の特性として、高疲労強度、低ひび割れ傾向、耐酸化性及び／又は機械加工性など、基材と化学的及び金属的融和性を有する。 The first alloy of the first PSP sheet 50 and the second PSP sheet 52 includes an arbitrary composition similar to the base material of the main part 38 so that the PSP sheet and the main part 38 exhibit more common physical properties. To. For example, in some embodiments, the first alloy and the substrate share a common composition (ie, the first alloy and the substrate are the same type of material). In some embodiments, the first alloy comprises a nickel-based superalloy or a cobalt-based superalloy. In some embodiments, the properties of the first alloy have chemical and metallic compatibility with the substrate, such as high fatigue strength, low cracking tendency, oxidation resistance and / or machinability.
第２の合金もまた、主要部３８の基材と類似する組成を有してもよいが、第１の合金と第２の合金の粒子の焼結を促進させ、基材の融点より低い温度でＰＳＰシートを主要部３８の後縁領域４２に接合できるように、融点降下性を更に含有する。 The second alloy may also have a composition similar to the substrate of the main portion 38, but promotes sintering of the particles of the first alloy and the second alloy and is at a temperature below the melting point of the substrate. In order to bond the PSP sheet to the trailing edge region 42 of the main portion 38, the melting point lowering property is further contained.
ＰＳＰシートは、第１の合金と第２の合金の粒子が互いに対して、またエアフォイル３６の主要部３８の後縁領域４２に対して確実に濡れ及び接合（例えば拡散／ろう付け接合）するのに十分な融点降下性をもたらすのに十分な任意の相対量の第１の合金と第２の合金を含む。例えば、幾つかの実施形態において、第２の合金は、第１のＰＳＰシート５０と第２のＰＳＰシート５２各々において少なくとも約１０重量パーセント含有される。一つの実施形態において、第２の合金は、ＰＳＰシート各々において約７０重量パーセント含有され、第１の合金はＰＳＰシート各々において約３０重量パーセント含有され、これによって、第１の合金と第２の合金の重量混合比は約３０：７０となる。別の実施形態では、第１の合金と第２の合金の重量混合比は約４０：６０となる。 The PSP sheet ensures that the particles of the first alloy and the second alloy wet and bond (eg, diffusion / brazing) to each other and to the trailing edge region 42 of the main portion 38 of the airfoil 36. Any relative amount of the first alloy and the second alloy sufficient to provide sufficient melting point depression. For example, in some embodiments, the second alloy is included at least about 10 weight percent in each of the first PSP sheet 50 and the second PSP sheet 52. In one embodiment, the second alloy is included in each PSP sheet at about 70 weight percent, and the first alloy is included in each PSP sheet at about 30 weight percent, whereby the first alloy and the second alloy The weight mixing ratio of the alloy is about 30:70. In another embodiment, the weight mixing ratio of the first alloy and the second alloy is about 40:60.
上記実施形態では、後縁補助構造４６は２つのＰＳＰシートを有するとして例示し、説明している。しかしながら、単一のＰＳＰシートを使用して、主要部３８の後縁領域４２に動作可能に結合してもよいことを理解されたい。更に、ＰＳＰシートを３つ以上使用して、後縁補助構造４６を形成してもよい。 In the above embodiment, the trailing edge auxiliary structure 46 is illustrated and described as having two PSP sheets. However, it should be understood that a single PSP sheet may be used to operably couple to the trailing edge region 42 of the main portion 38. Further, the trailing edge auxiliary structure 46 may be formed by using three or more PSP sheets.
使用されるＰＳＰシートの正確な数に関係なく、シートは主要部３８の後縁領域４２に動作可能に結合される。一つの実施形態において、ＰＳＰシートは後縁領域４２にろう付けされる。ＰＳＰシートは、ろう付け用ペーストを必要とせずに後縁領域４２にろう付けされるよう構成された材料からなる。このように、第１のＰＳＰシート５０と第２のＰＳＰシート５２などのＰＳＰシートが、炉内で、後縁領域４２に当接するような所望の場所に位置付けられ、ＰＳＰシートの主要部３８へのろう付けが容易になるのに必要な温度まで加熱される。ろう付けだけでなく、溶接、拡散接合又は機械的締結を含む、ただしこれに限定されない、代替の結合技術を用いてもよいものとしている。 Regardless of the exact number of PSP sheets used, the sheets are operably coupled to the trailing edge region 42 of the main portion 38. In one embodiment, the PSP sheet is brazed to the trailing edge region 42. The PSP sheet is made of a material configured to be brazed to the trailing edge region 42 without the need for brazing paste. In this way, the PSP sheets such as the first PSP sheet 50 and the second PSP sheet 52 are positioned at desired locations in the furnace so as to contact the trailing edge region 42, and to the main part 38 of the PSP sheet. It is heated to the temperature necessary to facilitate brazing. Alternative joining techniques may be used, including but not limited to welding, diffusion bonding or mechanical fastening, as well as brazing.
ＰＳＰシートを後縁補助構造４６として形成することにより、エアフォイル３６の後縁部をより薄くすることが可能となり、空気力学的閉塞を効果的に減少し、これによってタービンシステム全体の性能が向上する。 By forming the PSP sheet as the trailing edge auxiliary structure 46, the trailing edge of the airfoil 36 can be made thinner, effectively reducing aerodynamic blockage and thereby improving the overall performance of the turbine system. To do.
エアフォイル３６を効果的に冷却するために、主要部３８の後縁領域４２及び後縁補助構造４６全体にわたり冷却配置５４を設ける。主要部３８の後縁領域４２は、後縁補助構造４６内に配設される少なくとも１つ、ただし通常は複数の冷却経路５８と流体連通する、少なくとも１つの冷却チャネル５６を含む。複数の冷却経路５８は製造工程全体にわたり様々な方法でまた様々な時間に形成することができる。具体的には、後縁補助構造４６を主要部３８に結合する前又は結合した後に、複数の冷却経路５８を形成することができる。 In order to effectively cool the airfoil 36, a cooling arrangement 54 is provided throughout the trailing edge region 42 and the trailing edge assist structure 46 of the main portion 38. The trailing edge region 42 of the main portion 38 includes at least one cooling channel 56 disposed in the trailing edge assist structure 46, but typically in fluid communication with a plurality of cooling paths 58. Multiple cooling paths 58 can be formed in different ways and at different times throughout the manufacturing process. Specifically, a plurality of cooling paths 58 can be formed before or after the trailing edge assist structure 46 is coupled to the main portion 38.
後縁補助構造４６を主要部３８に結合する前に複数の冷却経路５８を形成することは、ＰＳＰシートそれ自体を形成中に、ＰＳＰシートがいまだに初期焼結前の柔軟なグリーン状態にあるように、ＰＳＰシートの少なくとも１つに控えめな大きさの溝、スロットなどを形成することを含む。溝、スロットなどを第１のＰＳＰシート５０と第２のＰＳＰシート５２の両方に形成して、複数の冷却経路５８を形成するために溝、スロットなどの位置合わせが必要となるようにしてもよい。また代替として、複数の冷却経路５８を、フライス加工、研削加工、ワイヤ放電加工（ＥＤＭ）、ミリングしたＥＤＭ、プランジＥＤＭ、電気化学的加工（ＥＣＭ）、ウォータージェットトレンチ加工、レーザトレンチ加工、又はこれらの組み合わせを含む、ただしこれに限定されない、任意の好適な材料除去動作によって加工（即ちＰＳＰシートからある材料を除去）してもよい。材料除去工程は、後縁補助構造４６を主要部に結合する前又は結合した後のいずれで行ってもよいものとしている。複数の冷却経路５８を形成する時間に関わらず、複数の冷却経路５８は少なくとも１つの冷却チャネル５６と流体連通する。上記の実施形態を、新規の又は様々なタービンシステムで既存のエアフォイルに組み込むことが可能であるものとしている。 Forming a plurality of cooling paths 58 before joining the trailing edge assist structure 46 to the main portion 38 is such that during the formation of the PSP sheet itself, the PSP sheet is still in a flexible green state prior to initial sintering. Forming a conservatively sized groove, slot or the like in at least one of the PSP sheets. Grooves, slots, etc. are formed in both the first PSP sheet 50 and the second PSP sheet 52, and alignment of the grooves, slots, etc. is required to form a plurality of cooling paths 58. Good. Alternatively, the cooling paths 58 may be milled, ground, wire electrical discharge machining (EDM), milled EDM, plunge EDM, electrochemical machining (ECM), water jet trench machining, laser trench machining, or these May be processed (ie, removed material from the PSP sheet) by any suitable material removal operation, including but not limited to a combination of The material removing step may be performed either before or after the trailing edge auxiliary structure 46 is bonded to the main part. Regardless of the time for which the plurality of cooling paths 58 are formed, the plurality of cooling paths 58 are in fluid communication with at least one cooling channel 56. It is contemplated that the above embodiments can be incorporated into existing airfoils with new or various turbine systems.
図５の流れ図に示すように、また、図１乃至４を参照すると、エアフォイルの後縁領域を修理する方法１００も提供される。タービンシステム１０及びエアフォイル３６の後縁補助構造４６はすべて、すでに説明しており、具体的な構造上の構成要素について更に詳細に説明する必要はない。エアフォイルの後縁領域を修理する方法１００は、エアフォイルの後縁領域に近接する材料を除去すること１０２を含む。後縁領域の基材を露出させ１０４、少なくとも１つのＰＳＰシートを基材に接合させる１０６。少なくとも１つのＰＳＰシートを基材に接合した後、後縁補助構造を形成する１０８。エアフォイルの後縁領域の修理方法１００はまた、上で詳細に説明した通り、主要部３８の少なくとも１つの冷却チャネル５６と流体連通する少なくとも１つの冷却経路を形成することを含む。 As shown in the flow diagram of FIG. 5, and referring also to FIGS. 1-4, a method 100 for repairing the trailing edge region of an airfoil is also provided. The turbine system 10 and the trailing edge assist structure 46 of the airfoil 36 have all been described above, and the specific structural components need not be described in further detail. The method 100 of repairing the trailing edge region of the airfoil includes removing 102 material adjacent to the trailing edge region of the airfoil. The substrate in the trailing edge region is exposed 104 and at least one PSP sheet is bonded 106 to the substrate. After joining at least one PSP sheet to the substrate, a trailing edge assist structure is formed 108. The airfoil trailing edge region repair method 100 also includes forming at least one cooling path in fluid communication with the at least one cooling channel 56 of the main portion 38, as described in detail above.
本発明を、わずかに限られた数の実施形態について詳細に説明してきたが、本発明はこのような開示の実施形態に限定されるものではないことを理解されたい。むしろ、本発明を変形して、任意な数の、これまで説明していないが、本発明の精神と範囲にふさわしい変更、調整、置換又は同等の構成を取り込むようにすることも可能である。加えて、本発明の様々な実施形態を説明してきたが、本発明の態様は記載した実施形態のうち幾つかのみを含むようにしてもよいことを理解されたい、従って、本発明は、上記の説明に限定されず、添付の特許請求の範囲によってのみ限定されるものである。 Although the invention has been described in detail with respect to a limited number of embodiments, it should be understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of alterations, adjustments, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. In addition, while various embodiments of the invention have been described, it should be understood that aspects of the invention may include only some of the described embodiments, and thus the invention is described above. It is not limited to this, but is limited only by the appended claims.
１０ タービンシステム
１２ 圧縮部
１４ 燃焼器アセンブリ
１８ 燃焼部
２４ タービン部
２６−２８ 複数段
３０ 回転子
３２ ノズル
３４ バケット
３６ エアフォイル
３８ 主要部
４０ 前縁
４２ 後縁領域
４４ 後縁領域後部幅
４６ 後縁補助構造
４８ 後縁補助構造後部幅
５０ ＰＳＰシート
５２ 第２のＰＳＰシート
５４ 冷却配置
５６ 冷却チャネル
５８ 冷却経路
１００ エアフォイルの後縁領域の修理方法
１０２ エアフォイルの後縁領域に近接する材料を除去
１０４ 後縁領域の基材を露出
１０６ 少なくとも１つのＰＳＰシートを基材に接合
１０８ 少なくとも１つのＰＳＰシートを基材に接合した後、後縁補助構造を形成
DESCRIPTION OF SYMBOLS 10 Turbine system 12 Compression part 14 Combustor assembly 18 Combustion part 24 Turbine part 26-28 Multiple stage 30 Rotor 32 Nozzle 34 Bucket 36 Airfoil 38 Main part 40 Leading edge 42 Trailing edge area 44 Trailing edge area Rear width 46 Trailing edge Auxiliary structure 48 Trailing edge auxiliary structure rear width 50 PSP sheet 52 Second PSP sheet 54 Cooling arrangement 56 Cooling channel 58 Cooling path 100 Airfoil trailing edge region repair method 102 Removing material adjacent to airfoil trailing edge region 104 Expose the substrate in the trailing edge region 106 Join at least one PSP sheet to the substrate 108 Form the trailing edge auxiliary structure after joining at least one PSP sheet to the substrate
Claims (14)
前記主要部の後縁領域と、
前記後縁に近接して、前記基材と動作可能に結合される少なくとも１つの予備焼結予備成形（ＰＳＰ）材料を含み、後縁補助構造後部幅を有する後縁補助構造と、
前記主要部の前記基材内に形成される少なくとも１つの冷却チャネルと、
前記後縁補助構造内に形成され、前記少なくとも１つの冷却チャネルと流体連通する少なくとも１つの冷却経路と、
を備え、
前記後縁補助構造後部幅が前記後縁領域後部幅より狭い、エアフォイル。 A rear edge region having a rear width, and a main portion made of a base material;
A trailing edge region of the main part;
In proximity to the trailing edge, seen including at least one pre-sintered preform (PSP) material is operably coupled to the base, the edge assist structure after having trailing edge assist structure rear width,
At least one cooling channel formed in the substrate of the main part;
At least one cooling path formed in the trailing edge assist structure and in fluid communication with the at least one cooling channel;
With
An airfoil in which the rear edge auxiliary structure rear width is narrower than the rear edge region rear width .
燃料及び圧縮空気を受け、高温高圧燃焼生成物を生成する燃焼部と、 A combustion section that receives fuel and compressed air and produces a high-temperature and high-pressure combustion product;
高温高圧燃焼生成物により駆動されるタービン部と、 A turbine section driven by high temperature and high pressure combustion products;
を備え、 With
タービン部が、前記エアフォイルを備えるノズルまたは、前記エアフォイルを備えるバケットを備える、請求項１１に記載のタービンシステム。 The turbine system according to claim 11, wherein the turbine unit includes a nozzle including the airfoil or a bucket including the airfoil.
前記エアフォイルの前記後縁領域に近接する材料を除去することと、
前記後縁領域の基材を露出させることと、
少なくとも１つのＰＳＰ材料を前記基材に結合させることと、
前記少なくとも１つのＰＳＰ材料を前記基材に接合した後、後縁補助構造を形成すること、
前記少なくとも１つのＰＳＰ材料を前記基材に結合する前に、前記少なくとも１つのＰＳＰ材料内に少なくとも１つの冷却経路を形成することと、
前記少なくとも１つのＰＳＰ材料を前記基材に結合した後に、前記少なくとも１つのＰＳＰ材料内に少なくとも１つの冷却経路を形成することと、
を含み、
前記後縁補助構造の後縁補助構造後部幅が前記基材の前記後縁領域の後縁領域後部幅より狭い、方法。 A method for repairing a trailing edge region of an airfoil, comprising:
Removing material proximate to the trailing edge region of the airfoil;
Exposing the substrate in the trailing edge region;
Bonding at least one PSP material to the substrate;
After joining the at least one PSP material to the substrate, forming a trailing edge assist structure ;
Forming at least one cooling path in the at least one PSP material prior to bonding the at least one PSP material to the substrate ;
Forming at least one cooling path in the at least one PSP material after bonding the at least one PSP material to the substrate ;
It includes,
The rear edge auxiliary structure rear width of the trailing edge auxiliary structure is narrower than the rear edge area rear width of the rear edge area of the substrate .
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| US13/963,322 US20150044059A1 (en) | 2013-08-09 | 2013-08-09 | Airfoil for a turbine system |
| US13/963,322 | 2013-08-09 |
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Families Citing this family (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9434017B2 (en) * | 2014-06-30 | 2016-09-06 | General Electric Company | Braze methods and components with heat resistant materials |
| US10520193B2 (en) | 2015-10-28 | 2019-12-31 | General Electric Company | Cooling patch for hot gas path components |
| US10815782B2 (en) * | 2016-06-24 | 2020-10-27 | General Electric Company | Methods for repairing airfoil trailing edges to include ejection slots therein |
| CN107799225B (en) * | 2016-08-29 | 2019-08-13 | 贝尔威勒电子股份有限公司 | High-frequency transmission cable |
| US10240465B2 (en) | 2016-10-26 | 2019-03-26 | General Electric Company | Cooling circuits for a multi-wall blade |
| US10465521B2 (en) | 2016-10-26 | 2019-11-05 | General Electric Company | Turbine airfoil coolant passage created in cover |
| US10301946B2 (en) | 2016-10-26 | 2019-05-28 | General Electric Company | Partially wrapped trailing edge cooling circuits with pressure side impingements |
| US10598028B2 (en) * | 2016-10-26 | 2020-03-24 | General Electric Company | Edge coupon including cooling circuit for airfoil |
| US10273810B2 (en) | 2016-10-26 | 2019-04-30 | General Electric Company | Partially wrapped trailing edge cooling circuit with pressure side serpentine cavities |
| US10309227B2 (en) | 2016-10-26 | 2019-06-04 | General Electric Company | Multi-turn cooling circuits for turbine blades |
| US10352176B2 (en) | 2016-10-26 | 2019-07-16 | General Electric Company | Cooling circuits for a multi-wall blade |
| US10450875B2 (en) | 2016-10-26 | 2019-10-22 | General Electric Company | Varying geometries for cooling circuits of turbine blades |
| US10450950B2 (en) | 2016-10-26 | 2019-10-22 | General Electric Company | Turbomachine blade with trailing edge cooling circuit |
| US10233761B2 (en) | 2016-10-26 | 2019-03-19 | General Electric Company | Turbine airfoil trailing edge coolant passage created by cover |
| US10746035B2 (en) * | 2017-08-30 | 2020-08-18 | General Electric Company | Flow path assemblies for gas turbine engines and assembly methods therefore |
| US11614233B2 (en) | 2020-08-31 | 2023-03-28 | General Electric Company | Impingement panel support structure and method of manufacture |
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Family Cites Families (10)
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| JP3297271B2 (en) * | 1995-11-22 | 2002-07-02 | 三菱重工業株式会社 | Steam cooled vane |
| JPH11114662A (en) * | 1997-10-09 | 1999-04-27 | Ishikawajima Harima Heavy Ind Co Ltd | Joining method for casting material and manufacture of turbine blade |
| WO2000071764A2 (en) * | 1999-05-07 | 2000-11-30 | Rolls-Royce Corporation | Cobalt-base composition and method for diffusion braze repair of superalloy articles |
| JP2003166404A (en) * | 2001-11-30 | 2003-06-13 | Suwa Netsukogyo Kk | Manufacturing method and repairing method of turbine blade |
| US7343676B2 (en) * | 2004-01-29 | 2008-03-18 | United Technologies Corporation | Method of restoring dimensions of an airfoil and preform for performing same |
| US7887300B2 (en) * | 2007-02-27 | 2011-02-15 | Siemens Energy, Inc. | CMC airfoil with thin trailing edge |
| JP5391616B2 (en) * | 2008-09-18 | 2014-01-15 | 株式会社Ｉｈｉ | Preform brazing material, method of repairing low-pressure turbine component with sintered preform brazing material, and repaired low-pressure turbine component |
| EP2196276A1 (en) * | 2008-12-15 | 2010-06-16 | Siemens Aktiengesellschaft | Form bodies for welding, assembly of form bodies, method and component |
| US20120231295A1 (en) * | 2011-03-08 | 2012-09-13 | General Electric Company | Method of fabricating a component and a component |
| JP2012237270A (en) * | 2011-05-13 | 2012-12-06 | Hitachi Ltd | Gas turbine stator blade |
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| US20150044059A1 (en) | 2015-02-12 |
| JP2015036546A (en) | 2015-02-23 |
| DE102014111005A1 (en) | 2015-02-12 |
| CH708445A2 (en) | 2015-02-13 |
| CN204344175U (en) | 2015-05-20 |
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