JP2010014113A - Rear frame having elliptic cooling slot and associated method - Google Patents

Rear frame having elliptic cooling slot and associated method Download PDF

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Publication number
JP2010014113A
JP2010014113A JP2009143807A JP2009143807A JP2010014113A JP 2010014113 A JP2010014113 A JP 2010014113A JP 2009143807 A JP2009143807 A JP 2009143807A JP 2009143807 A JP2009143807 A JP 2009143807A JP 2010014113 A JP2010014113 A JP 2010014113A
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rear frame
bottom wall
pair
cooling
side walls
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Vijay Kumar Turaga
ヴィジェイ・クマール・トゥラガ
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General Electric Co
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General Electric Co
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Abstract

<P>PROBLEM TO BE SOLVED: To provide a rear frame (10) for joining a combustor transition piece and a first stage turbine nozzle. <P>SOLUTION: This rear frame (10) includes a closed peripheral frame part composed of an upper wall (12), a bottom wall (14) and a pair of sidewalls (16 and 18). A plurality of cooling holes or apertures (26) having an oval or elliptic cross-sectional shape are arranged in one or more of the upper wall, the bottom wall and the pair of sidewalls, and extend by penetrating in the axial direction through the closed peripheral frame part. The cooling holes have the major axis and the minor axis, and are constituted so that the major axis becomes substantially parallel to the upper wall and the bottom wall. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

本発明は、タービン冷却技術に関し、より具体的には、燃焼器トランジションピースと第１段タービンノズルとの間を結合する後方フレームの冷却に関する。   The present invention relates to turbine cooling technology and, more particularly, to cooling a rear frame that couples between a combustor transition piece and a first stage turbine nozzle.

発電ガスタービン用の缶−アニュラ型燃焼器との関連で理解されるような「トランジションピース」は、燃焼器ライナをタービンの第１段ノズルと連結するダクトである。後方フレームは、トランジションピースの出口端部に設置され、トランジションピースと第１段ノズルとの間の結合部としての役割を果たす。後方フレーム部品は、第１段ノズルに流れる高温ガスに曝されるので、それら後方フレーム部品の冷却は大きな関心事である。   A “transition piece” as understood in the context of a can-annular combustor for a power gas turbine is a duct that connects the combustor liner with the first stage nozzle of the turbine. The rear frame is installed at the outlet end of the transition piece and serves as a connection between the transition piece and the first stage nozzle. Since the rear frame parts are exposed to the hot gas flowing through the first stage nozzle, cooling of the rear frame parts is of great concern.

より具体的には、トランジションピースを通って流れる高温ガスは、後方フレームと第１段ノズルとの間の溝内で再循環して、大きな温度勾配を生じる。従って、後方フレームの後面、すなわち該フレームの第１段ノズルに面する側に対して有効な冷却を行う必要がある。現在の一般的な後方フレーム構成では、円形断面を有する冷却孔を組込んで、インピンジメントスリーブ（トランジションピースを囲む）を通る流れの一部分をこれらの孔内に迂回させて該後方フレームを冷却するようにしている。   More specifically, the hot gas flowing through the transition piece is recirculated in the groove between the rear frame and the first stage nozzle, creating a large temperature gradient. Therefore, it is necessary to effectively cool the rear surface of the rear frame, that is, the side of the frame facing the first stage nozzle. Current common rear frame configurations incorporate cooling holes with a circular cross-section to divert a portion of the flow through the impingement sleeve (surrounding the transition piece) into these holes to cool the rear frame. I am doing so.

米国特許第６４１２２６８号明細書US Pat. No. 6,412,268 米国特許第６５４７２５７号明細書US Pat. No. 6,547,257 米国特許第４９２３３７１号明細書US Pat. No. 4,923,371 米国特許第５２３３８２８号明細書US Pat. No. 5,233,828 米国特許第６１８６７４１号明細書US Pat. No. 6,186,741 米国特許第６２８７０７５号明細書US Pat. No. 6,287,075 米国特許第６３６８０６０号明細書US Pat. No. 6,368,060 米国特許第６３７５４２５号明細書US Pat. No. 6,375,425 米国特許第６７４３３５０号明細書US Pat. No. 6,743,350 米国特許第６９８４１００号明細書US Pat. No. 6,984,100 米国特許第７０６６７１６号明細書US Pat. No. 7,066,716 米国特許第７２９６９６７号明細書US Pat. No. 7,296,967 米国特許第７３７７７４３号明細書US Pat. No. 7,377,743 欧州特許出願公開第１０２２４３４号明細書European Patent Application No. 1022434

しかしながら、トランジションピースの後方フレームのより有効な冷却の必要性が依然として存在している。   However, there remains a need for more effective cooling of the rear frame of the transition piece.

本発明の例示的だが非限定的な実施形態によると、楕円形状冷却孔が、後方フレームの周辺部の周りに設けられる。長円形状又は楕円形状孔は、所定の断面積においてより多くの有効対流冷却用表面積を備えるので、後方フレームの冷却が改善される。   According to an exemplary but non-limiting embodiment of the present invention, elliptical cooling holes are provided around the periphery of the rear frame. The oval or elliptical holes provide more effective convection cooling surface area at a given cross-sectional area, thus improving the cooling of the rear frame.

従って、１つの態様では、本発明は、燃焼器トランジションピースと第１段タービンノズルとの間を結合する後方フレームに関し、本後方フレームは、上壁、底壁及び一対の側壁から成る閉鎖周辺フレーム部と、該上壁、底壁及び一対の側壁の１以上を貫通して延びる複数の冷却アパーチャとを含み、冷却アパーチャは、楕円形又は長円形断面形状を有する。   Accordingly, in one aspect, the present invention relates to a rear frame that couples between a combustor transition piece and a first stage turbine nozzle, the rear frame being a closed peripheral frame comprising a top wall, a bottom wall, and a pair of side walls. And a plurality of cooling apertures extending through one or more of the top wall, the bottom wall, and the pair of side walls, wherein the cooling aperture has an elliptical or oval cross-sectional shape.

別の態様では、本発明は、燃焼器トランジションピースと第１段タービンノズルとの間を結合する後方フレームに関し、本後方フレームは、上壁、底壁及び一対の側壁から成る閉鎖周辺フレーム部と、楕円形又は長円形断面形状を有し、上壁、底壁及び一対の側壁の各々に設けられかつ該フレーム部を軸方向に貫通して延びる複数の冷却アパーチャとを含み、冷却アパーチャは、長軸及び短軸を有しかつ該長軸が上壁及び底壁とほぼ平行になるように構成される。   In another aspect, the invention relates to a rear frame that couples between a combustor transition piece and a first stage turbine nozzle, the rear frame comprising a closed peripheral frame portion comprising a top wall, a bottom wall, and a pair of side walls. A plurality of cooling apertures having an elliptical or oval cross-sectional shape, provided on each of the top wall, the bottom wall, and the pair of side walls and extending through the frame portion in the axial direction. A major axis and a minor axis are provided, and the major axis is configured to be substantially parallel to the top wall and the bottom wall.

さらに別の態様では、本発明は、燃焼器トランジションピースと第１段タービンノズルとの間を結合するタービン後方フレームを形成する方法に関し、本方法は、ａ）上壁、底壁及び一対の側壁を有する閉鎖周辺後方フレーム部を準備するステップと、ｂ）上壁、底壁及び一対の側壁の少なくとも１つに、該後方フレーム部を軸方向に貫通して延びる楕円形状冷却孔を形成するステップとを含む。   In yet another aspect, the present invention relates to a method of forming a turbine rear frame that couples between a combustor transition piece and a first stage turbine nozzle, the method comprising: a) a top wall, a bottom wall, and a pair of side walls. And b) forming an elliptical cooling hole extending through the rear frame portion in the axial direction in at least one of the upper wall, the bottom wall, and the pair of side walls. Including.

次に、以下に特定する図に関連させて、本発明を一層詳細に説明する。   The invention will now be described in more detail in connection with the figures identified below.

公知の構造の一般的なトランジションピース後方フレームの斜視図。The perspective view of the common transition piece rear frame of a well-known structure. 後方フレームに形成された公知の円形冷却孔又はスロットを示す拡大詳細図。FIG. 3 is an enlarged detail view showing a known circular cooling hole or slot formed in the rear frame. 例えば図１に示すタイプの後方フレーム内で使用することになる冷却孔の長円形状又は楕円形状を例示する拡大詳細図。For example, an enlarged detail view illustrating an oval shape or an oval shape of a cooling hole to be used in a rear frame of the type shown in FIG.

図１を参照すると、従来のトランジションピース（図示せず）と第１段タービンノズル（これも図示せず）との間の結合部としての役割を果たす後方フレーム１０は、それぞれ上壁１２及び底壁１４と閉鎖周辺フレームを完成させる一対の側壁１６、１８とを含む。ブラケット２０及び２２のような取付けハードウェアは、第１段タービンノズルに対する後方フレームの連結を可能にする。しかしながら、正確な取付け方法は、本発明の不可欠な要素ではなく、いずれにしても、あらゆる好適な取付け法を使用することができる。従来のトランジションピースは、後方フレームの反対側に取付けられて、第１段ノズルと燃焼器ライナとの間で延びていることを理解されたい。このタイプの構成の実施例は、米国特許第６４１２２６８号及び第６５４７２５７号に見ることができる。   Referring to FIG. 1, the rear frame 10, which serves as a connection between a conventional transition piece (not shown) and a first stage turbine nozzle (also not shown), has a top wall 12 and a bottom respectively. It includes a wall 14 and a pair of side walls 16, 18 that complete a closed peripheral frame. Mounting hardware, such as brackets 20 and 22, allows for connection of the rear frame to the first stage turbine nozzle. However, the exact attachment method is not an integral part of the present invention and any suitable attachment method can be used in any event. It should be understood that a conventional transition piece is mounted on the opposite side of the rear frame and extends between the first stage nozzle and the combustor liner. Examples of this type of configuration can be found in US Pat. Nos. 6,412,268 and 6,547,257.

次に、図２を参照すると、円形冷却孔２４は一般的に、後方フレームの周辺の周りに間隔を置いて配置されて、冷却空気が孔内にかつ後方フレームを貫通して流れ、それによって該フレームを冷却するのを可能にする。   Referring now to FIG. 2, the circular cooling holes 24 are generally spaced around the periphery of the rear frame so that cooling air flows into the holes and through the rear frame, thereby Allows the frame to cool.

図３は、後方フレームのより良好かつより効率的な冷却を可能にする修正冷却孔形状を例示している。具体的には、軸方向に延びる冷却孔又はアパーチャ２６の幾つか又は全ては、楕円形又は長円形断面形状を有しており、所定の断面積において有効対流冷却用表面積が増大している。楕円形冷却孔又はアパーチャ２６は、特定の冷却要件によって定まるものとして、単独に或いは円形冷却孔（例えば、孔２４）と組合せて使用することができる。楕円形孔の寸法はまた、冷却要件に従って変化させることができる。楕円形冷却孔２６は、後方フレームのそれぞれ上壁１２、底壁１４及び一対の側壁１６、１８のいずれか１以上に設けることができる。冷却アパーチャの長軸は、後方フレームの上壁及び底壁にほぼ平行であるのが好ましい。   FIG. 3 illustrates a modified cooling hole shape that allows for better and more efficient cooling of the rear frame. Specifically, some or all of the axially extending cooling holes or apertures 26 have an elliptical or oval cross-sectional shape, increasing the effective convective cooling surface area at a given cross-sectional area. The elliptical cooling hole or aperture 26 can be used alone or in combination with a circular cooling hole (eg, hole 24) as determined by the particular cooling requirements. The size of the elliptical hole can also be varied according to the cooling requirements. The elliptical cooling holes 26 can be provided in any one or more of the upper wall 12, the bottom wall 14, and the pair of side walls 16, 18 of the rear frame. The major axis of the cooling aperture is preferably substantially parallel to the top and bottom walls of the rear frame.

現在最も実用的かつ好ましい実施形態であると考えられるものに関して本発明を説明してきたが、本発明は開示した実施形態に限定されるものではなく、逆に特許請求の範囲の技術思想及び技術的範囲内に含まれる様々な変更及び均等な構成を保護しようとするものであることを理解されたい。   Although the present invention has been described with respect to what is presently considered to be the most practical and preferred embodiments, the present invention is not limited to the disclosed embodiments, and conversely, the technical concept and technical scope of the claims. It should be understood that various changes and equivalent arrangements included within the scope are intended to be protected.

１０ 後方フレーム
１２ 上壁
１４ 底壁
１６、１８ 側壁
２０、２２ ブラケット
２４ 円形冷却孔
２６ 楕円形冷却孔 10 Rear frame 12 Upper wall 14 Bottom wall 16, 18 Side wall 20, 22 Bracket 24 Circular cooling hole 26 Elliptical cooling hole

Claims (10)

燃焼器トランジションピースと第１段タービンノズルとの間を結合する後方フレーム（１０）であって、
上壁（１２）、底壁（１４）及び一対の側壁（１６、１８）から成る閉鎖周辺フレーム部と、
前記上壁、底壁及び一対の側壁の１以上を貫通して延びる複数の冷却アパーチャと
を備えていて、前記複数の冷却アパーチャ（２６）が楕円形又は長円形断面形状を有する、後方フレーム。 A rear frame (10) connecting between the combustor transition piece and the first stage turbine nozzle,
A closed peripheral frame portion comprising a top wall (12), a bottom wall (14) and a pair of side walls (16, 18);
A rear frame comprising a plurality of cooling apertures extending through one or more of the top wall, the bottom wall and the pair of side walls, wherein the plurality of cooling apertures (26) have an elliptical or oval cross-sectional shape. 前記複数の冷却アパーチャ（２６）の１以上が、前記上壁（１２）、底壁（１４）及び一対の側壁（１６、１８）の各々に設けられる、請求項１記載の後方フレーム。   The rear frame according to claim 1, wherein one or more of the plurality of cooling apertures (26) are provided on each of the top wall (12), the bottom wall (14) and the pair of side walls (16, 18). 前記複数の冷却アパーチャ（２６）が、前記閉鎖周辺フレーム部を軸方向に貫通して延びる、請求項１記載の後方フレーム。   The rear frame of any preceding claim, wherein the plurality of cooling apertures (26) extend axially through the closed peripheral frame portion. 前記複数の冷却アパーチャ（２６）が、前記閉鎖周辺フレーム部を軸方向に貫通して延びる、請求項２記載の後方フレーム。   The rear frame of claim 2, wherein the plurality of cooling apertures (26) extend axially through the closed peripheral frame portion. 前記複数の冷却アパーチャ（２６）が、長軸及び短軸を有しかつ該長軸が前記上壁及び底壁とほぼ平行になるように構成される、請求項１記載の後方フレーム。   The rear frame of any preceding claim, wherein the plurality of cooling apertures (26) are configured to have a major axis and a minor axis, the major axis being substantially parallel to the top wall and the bottom wall. 前記複数の冷却アパーチャ（２６）が、長軸及び短軸を有しかつ該長軸が前記上壁及び底壁とほぼ平行になるように構成される、請求項４記載の後方フレーム。   The rear frame of claim 4, wherein the plurality of cooling apertures (26) are configured to have a major axis and a minor axis, the major axis being substantially parallel to the top wall and the bottom wall. 燃焼器トランジションピースと第１段タービンノズルとの間を結合する後方フレーム（１０）であって、
上壁（１２）、底壁（１４）及び一対の側壁（１６、１８）から成る閉鎖周辺フレーム部と、
楕円形又は長円形断面形状を有し、前記上壁、底壁及び一対の側壁の各々に設けられかつ前記閉鎖周辺フレーム部を軸方向に貫通して延びる複数の冷却アパーチャ（２６）と
を備えていて、前記複数の冷却アパーチャ（２６）が、長軸及び短軸を有しかつ該長軸が前記上壁及び底壁とほぼ平行になるように構成される、後方フレーム。 A rear frame (10) connecting between the combustor transition piece and the first stage turbine nozzle,
A closed peripheral frame portion comprising a top wall (12), a bottom wall (14) and a pair of side walls (16, 18);
A plurality of cooling apertures (26) having an elliptical or oval cross-sectional shape, provided on each of the upper wall, the bottom wall and the pair of side walls and extending through the closed peripheral frame portion in the axial direction; A rear frame, wherein the plurality of cooling apertures (26) have a major axis and a minor axis, and the major axis is substantially parallel to the top wall and the bottom wall. 燃焼器トランジションピースと第１段タービンノズルとの間を結合するタービン後方フレーム（１０）を形成する方法であって、
ａ）上壁（１２）、底壁（１４）及び一対の側壁（１６、１８）を有する閉鎖周辺後方フレーム部を準備するステップと、
ｂ）前記上壁、底壁及び一対の側壁の少なくとも１つに、前記後方フレーム部を軸方向に貫通して延びる楕円形状冷却孔（２６）を形成するステップと
を含む方法。 A method of forming a turbine aft frame (10) coupling between a combustor transition piece and a first stage turbine nozzle comprising:
a) providing a closed peripheral rear frame having a top wall (12), a bottom wall (14) and a pair of side walls (16, 18);
b) forming an elliptical cooling hole (26) extending through the rear frame portion in the axial direction in at least one of the top wall, the bottom wall, and the pair of side walls. 前記楕円形状冷却孔（２６）を前記上壁、底壁及び一対の側壁の全てに設けるステップを含む、請求項８記載の方法。   The method of claim 8, comprising providing the elliptical cooling holes (26) in all of the top wall, bottom wall and pair of side walls. 前記楕円形状冷却孔（２６）が、長軸及び短軸を有し、前記ステップｂ）が、前記長軸が前記上壁及び底壁にほぼ平行になるように前記楕円形状冷却孔を構成するステップを含む、請求項８記載の方法。   The elliptical cooling hole (26) has a major axis and a minor axis, and the step b) configures the elliptical cooling hole so that the major axis is substantially parallel to the upper wall and the bottom wall. The method of claim 8, comprising steps.
JP2009143807A 2008-06-30 2009-06-17 Rear frame having elliptic cooling slot and associated method Pending JP2010014113A (en)

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