JP2001200701A - Turbine rotor blade and coupling method therefor - Google Patents
Turbine rotor blade and coupling method thereforInfo
- Publication number
- JP2001200701A JP2001200701A JP2000008251A JP2000008251A JP2001200701A JP 2001200701 A JP2001200701 A JP 2001200701A JP 2000008251 A JP2000008251 A JP 2000008251A JP 2000008251 A JP2000008251 A JP 2000008251A JP 2001200701 A JP2001200701 A JP 2001200701A
- Authority
- JP
- Japan
- Prior art keywords
- circumferential
- blade
- rotor
- circumferential direction
- turbine
- 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
- 238000010168 coupling process Methods 0.000 title claims description 25
- 230000008878 coupling Effects 0.000 claims description 19
- 238000005859 coupling reaction Methods 0.000 claims description 19
- 230000002093 peripheral effect Effects 0.000 claims description 16
- 238000000034 method Methods 0.000 claims description 7
- 230000001808 coupling effect Effects 0.000 abstract description 8
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、タービン動翼及び
その連成方法に関し、特に、蒸気タービン、ガスタービ
ンのような軸流タービンに適用され、インテグラルシュ
ラウド翼（ＩＳＢ）構造を持つタービン動翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine blade and a coupling method therefor, and more particularly to a turbine blade having an integral shroud blade (ISB) structure applied to an axial flow turbine such as a steam turbine or a gas turbine. About wings.
【０００２】[0002]
【従来の技術】蒸気タービン、ガスタービンのような軸
流タービンに適用され、ＩＳＢ構造を持つタービン動翼
が知られている。このような動翼は、円周方向に並ぶ複
数の動翼要素（ブレード）がロータに同体に組み付けら
れた構造を有している。複数の動翼要素は、最外周の棚
により同体化され回転時にも連成していることが求めら
れる。組立時には複数の動翼要素が円周方向に密着して
いるが、運転回転時には、遠心力で動翼どうしが互いに
離反して離隔し、棚の間に隙間が生じ、その連成的性格
が失われる。2. Description of the Related Art A turbine blade having an ISB structure, which is applied to an axial turbine such as a steam turbine and a gas turbine, is known. Such a moving blade has a structure in which a plurality of moving blade elements (blades) arranged in a circumferential direction are integrally attached to a rotor. The plurality of blade elements are required to be integrated by the outermost shelf and to be coupled during rotation. At the time of assembly, a plurality of moving blade elements are in close contact with each other in the circumferential direction, but at the time of operation rotation, the moving blades are separated from each other by centrifugal force and separated from each other, and a gap is generated between the shelves, and the coupled character is Lost.
【０００３】図７は、そのようなＩＳＢ構造のタービン
動翼を示している。タービン動翼は、複数の動翼要素１
０１から形成され、各動翼要素１０１は、ロータ１０２
に結合する根付部１０３と、図８に示されるように、軸
流生起部を形成するプロファイル部１０４と、輪帯を形
成する棚部１０５とから形成されている。動翼要素１０
１は、ロータに１０２に軸方向に差し込まれてロータ１
０２に組み付けられる。このような組み付けによる組立
後には、隣り合う動翼要素の円周方向に隣り合う棚の対
向面は密着している。このような密着により、図９に示
されるように、隣り合う動翼要素の間は、密着線１０６
で密着して、タービン動翼は全体として同体である１つ
の連成体になる。このように連成される動翼は、部分要
素間の振動応答が小さくなる。FIG. 7 shows a turbine rotor blade having such an ISB structure. The turbine blade has a plurality of blade elements 1
01, each blade element 101 includes a rotor 102
, A profile portion 104 forming an axial flow generating portion, and a shelf portion 105 forming an annular zone, as shown in FIG. Bucket element 10
1 is inserted into the rotor 102 in the axial direction and the rotor 1
02. After assembling by such assembling, the opposing surfaces of the adjacent shelves in the circumferential direction of the adjacent moving blade elements are in close contact. Due to such close contact, as shown in FIG.
And the turbine blades become one coupled body that is generally the same. The rotor blades thus coupled have a small vibration response between the partial elements.
【０００４】運転中に遠心力が大きくなってロータ径が
拡大して隣接動翼要素の間にわずかでも隙間が生じる
と、その連成効果が発揮されず、翼の振動応答が大きく
なって、回転機械に各種の不具合が生じてしまう。連成
効果を発揮させるようにそのような不具合の発生を回避
するために、従来は、翼頂部の棚の端面を精密なスリあ
わせによって密着させることが必要であり、更に、プロ
ファイルに強制ネジリを与えた翼を組み込むこと等の色
々な工夫が必要であった。このような工夫は、当然にコ
スト上昇を招く。If the centrifugal force increases during operation, the rotor diameter increases, and even a slight gap is formed between adjacent moving blade elements, the coupling effect is not exhibited, and the blade vibration response increases, Various problems occur in the rotating machine. Conventionally, it is necessary to bring the end faces of the wing top shelves into close contact with each other by precise screwing, in order to avoid the occurrence of such defects so as to exert the coupling effect. Various measures such as incorporating the given wings were necessary. Such a contrivance naturally leads to an increase in cost.
【０００５】密着部が遠心力で密着しなくなる矛盾を取
り除くことが望まれる。更に、連成効果が低コストで発
揮されることが望まれる。[0005] It is desired to eliminate the contradiction in which the contact portion does not adhere due to centrifugal force. Further, it is desired that the coupling effect be exhibited at low cost.
【０００６】[0006]
【発明が解決しようとする課題】本発明の課題は、密着
部が遠心力で密着しなくなる矛盾を取り除き連成効果を
回転時に保証することができるタービン動翼及びその連
成方法を提供することにある。本発明の他の課題は、連
成効果が低コストで発揮されるタービン動翼及びその連
成方法を提供することにある。SUMMARY OF THE INVENTION An object of the present invention is to provide a turbine rotor blade and a coupling method thereof, which can eliminate the contradiction in which the contact portion does not adhere due to centrifugal force and can guarantee the coupling effect during rotation. It is in. Another object of the present invention is to provide a turbine blade and a method for coupling the turbine blades, which can achieve a coupling effect at low cost.
【０００７】[0007]
【課題を解決するための手段】その課題を解決するため
の手段が、下記のように表現される。その表現中に現れ
る技術的事項には、括弧（）つきで、番号、記号等が添
記されている。その番号、記号等は、本発明の実施の複
数・形態又は複数の実施例のうちの少なくとも１つの実
施の形態又は複数の実施例を構成する技術的事項、特
に、その実施の形態又は実施例に対応する図面に表現さ
れている技術的事項に付せられている参照番号、参照記
号等に一致している。このような参照番号、参照記号
は、請求項記載の技術的事項と実施の形態又は実施例の
技術的事項との対応・橋渡しを明確にしている。このよ
うな対応・橋渡しは、請求項記載の技術的事項が実施の
形態又は実施例の技術的事項に限定されて解釈されるこ
とを意味しない。Means for solving the problem are described as follows. The technical items appearing in the expression are appended with numbers, symbols, and the like in parentheses (). The numbers, symbols, and the like are technical items that constitute at least one embodiment or a plurality of the embodiments of the present invention, in particular, the embodiments or the examples. Corresponds to the reference numerals, reference symbols, and the like assigned to the technical matters expressed in the drawings corresponding to the above. Such reference numbers and reference symbols clarify the correspondence and bridging between the technical matters described in the claims and the technical matters of the embodiments or examples. Such correspondence / bridge does not mean that the technical matters described in the claims are interpreted as being limited to the technical matters of the embodiments or the examples.
【０００８】本発明によるタービン動翼は、ロータ本体
（２）と、ロータ（２）の周囲に配置されロータ本体
（２）に結合しロータ本体（２）の円周方向に並ぶ複数
の動翼要素（１）を含み、各１つの動翼要素（１）は、
ロータ本体（２）に結合する結合部（４）と、結合部
（４）に同体化され結合部（４）より半径方向外側に位
置するプロファイル部（５）と、プロファイル部（５）
に同体化されプロファイル部（５）より半径方向外側に
位置する棚部（６）とを備え、隣り合う２つの動翼要素
（１）のそれぞれの２つの棚部（６）の間には、静止時
に存在するが、回転時の遠心力より２つの棚部（６）が
円周方向に遠ざかることにより実質的に消滅するクリア
ランス１４が介設され、回転時に複数の動翼要素（１）
は連成する。動翼要素（１）の隣り合う棚部（６）は、
放射方向に延びるが円周方向には延びないため、互いに
相対的に接近して合体する。A turbine rotor blade according to the present invention has a rotor body (2) and a plurality of rotor blades arranged around the rotor (2) and connected to the rotor body (2) and arranged in a circumferential direction of the rotor body (2). Elements (1), each one blade element (1)
A coupling part (4) coupled to the rotor body (2), a profile part (5) integrated with the coupling part (4) and located radially outside the coupling part (4), and a profile part (5)
And a shelf (6) located radially outside of the profile part (5), and between each two shelf parts (6) of two adjacent blade elements (1). A clearance 14, which is present when stationary, but substantially disappears when the two shelves (6) move away in the circumferential direction due to the centrifugal force during rotation is provided, and a plurality of blade elements (1) are provided during rotation.
Is coupled. The adjacent shelf (6) of the bucket element (1)
Since they extend in the radial direction but not in the circumferential direction, they coalesce relatively close to each other.
【０００９】２つの動翼要素（１）の内の一方の動翼要
素は、それの端面から円周方向に延びる第１円周方向延
長部（８）と、第１円周方向延長部（８）の端部から半
径方向に延びる第１半径方向延長部（９）とを備え、２
つの動翼要素（１）の内の他方の動翼要素は、それの端
面から円周方向と逆方向に延びる第２円周方向延長部
（１２）と、第２円周方向延長部部（１２）の端部から
半径方向と逆方向に延びる第２半径方向延長部（１３）
とを備え、第１円周方向延長部（８）と第２円周方向延
長部（１２）との円周方向の前後関係は、一方の動翼要
素（１）と他方の動翼要素（１）との円周方向の前後関
係に対して逆関係であり、クリアランスは、第１半径方
向延長部（９）と第２半径方向延長部（１３）との円周
方向の間に介設されている。軸方向に嵌まり合う凹凸嵌
合は、製作が容易で、且つ、組立が容易である。One of the two blade elements (1) has a first circumferential extension (8) extending circumferentially from an end face thereof, and a first circumferential extension (8). 8) a first radial extension (9) extending radially from the end of (8).
The other one of the blade elements (1) has a second circumferential extension (12) extending in a direction opposite to the circumferential direction from an end face thereof, and a second circumferential extension ( A second radial extension (13) extending in a direction opposite to the radial direction from the end of 12);
And the circumferential relationship between the first circumferential extension (8) and the second circumferential extension (12) is such that one blade element (1) and the other blade element ( The clearance is opposite to the circumferential relationship of 1), and the clearance is provided between the first radial extension (9) and the second radial extension (13) in the circumferential direction. Have been. The concave-convex fitting that fits in the axial direction is easy to manufacture and easy to assemble.
【００１０】２つの動翼要素（１）の内の一方の動翼要
素は、それの端面から円周方向に延びる第１円周方向延
長部（８’）を備え、２つの動翼要素（１）の内の他方
の動翼要素は、それの端面から円周方向と逆方向に延び
る第２円周方向延長部（１２’）を備え、第１円周方向
延長部（８’）と第２円周方向延長部（１２’）とに
は、半径方向に嵌まりあう凸部（２１）と凹部（２２）
が形成され、クリアランスは、凸部（２１）と凹部（２
２）との円周方向の間に形成されている。One of the two blade elements (1) has a first circumferential extension (8 ') extending circumferentially from an end face thereof, and the two blade elements (1). The other blade element of 1) has a second circumferential extension (12 ') extending in a direction opposite to the circumferential direction from its end face, and has a first circumferential extension (8'). A convex portion (21) and a concave portion (22) that fit in the radial direction are provided on the second circumferential extension (12 ′).
Are formed, and the clearance is formed between the convex portion (21) and the concave portion (2).
2) is formed in the circumferential direction.
【００１１】そのクリアランスの幅は、現実には実際の
機種で２０μｍ〜７０μｍの程度であり、十分な機械的
精度で製作することができる。The width of the clearance is actually about 20 μm to 70 μm in an actual model, and it can be manufactured with sufficient mechanical accuracy.
【００１２】本発明によるタービン動翼の連成方法又は
タービン動翼の組立方法は、ロータ本体（２）に結合す
る結合部（４）と、結合部（４）に同体化され結合部
（４）より半径方向外側に位置するプロファイル部
（５）と、プロファイル部（５）に同体化されプロファ
イル部（５）より半径方向外側に位置する棚部（６）と
を備える動翼要素（１）の多数が円周方向に並ぶタービ
ン翼の連成方法であり、静止時に隣り合う２つの棚部
（６）の間に円周方向のクリアランスを与えること、回
転時に遠心力により２つの棚部（６）を円周方向に離隔
させることにより、そのクリアランスを実質的に消滅さ
せることとを含む。According to the present invention, there is provided a method for coupling a turbine blade or assembling a turbine blade, comprising: a coupling portion (4) coupled to the rotor body (2); and a coupling portion (4) integrated with the coupling portion (4). ) A bucket element (1) including a profile part (5) located radially outward from the profile part, and a shelf part (6) integrated with the profile part (5) and located radially outside the profile part (5). Is a method of coupling turbine blades arranged in a circumferential direction, providing a circumferential clearance between two adjacent shelves (6) at rest, and two shelves (2) by centrifugal force during rotation. 6) in the circumferential direction to substantially eliminate the clearance.
【００１３】更に好ましくは、ロータ本体（２）に１つ
の動翼要素（１）を軸方向に挿入してロータ本体（２）
の外周側に動翼要素（１）を同体化すること、ロータ本
体（２）に他の１つの動翼要素（１）を軸方向に挿入し
てロータ本体（２）の外周側に動翼要素（１）を同体化
すること、１つの動翼要素（１）の最外周領域部分の円
周方向に面する端面と他の１つの動翼要素の最外周領域
部分の円周方向に面する端面とを接合することとを含
み、１つの動翼要素（１）の最外周領域部分の円周方向
に面する他の端面と他の１つの動翼要素（１）の最外周
領域部分の円周方向に面する他の端面との間に、２つの
動翼要素（１）が遠心力により円周方向に離隔する時に
円周方向に縮小するクリアランスが与えられている。More preferably, one rotor element (1) is inserted in the rotor body (2) in the axial direction, and the rotor body (2) is inserted.
The rotor blade element (1) is integrated on the outer peripheral side of the rotor body, and another rotor blade element (1) is inserted into the rotor main body (2) in the axial direction to form a rotor blade on the outer peripheral side of the rotor main body (2). Integrating the element (1) with the peripheral surface of the outermost peripheral region of one rotor blade element (1) and the circumferential surface of the outermost peripheral region of another rotor blade element. And the other end face facing the circumferential direction of the outermost peripheral region portion of one bucket element (1) and the outermost peripheral region portion of another bucket element (1). Is provided with a clearance that is reduced in the circumferential direction when the two blade elements (1) are separated in the circumferential direction by centrifugal force.
【００１４】このような構造の連成方法は、その構造の
組立にも好都合であり、本発明の連成方法は実質的に組
み立て方法にほとんど一致している。Such a coupling method for a structure is also advantageous for assembling the structure, and the coupling method of the present invention substantially matches the assembling method.
【００１５】[0015]
【発明の実施の形態】図に一致対応して、本発明による
タービン動翼の実施の形態は、動翼要素がロータ本体と
ともに設けられている。その動翼要素１は、図１に示さ
れるように、そのロータ本体２の外周域に複数体が取り
付けられている。各動翼要素１は、ロータ本体２に形成
された中心方向にすぼむ溝面３に対応する曲面を有する
根付部４を備えている。根付部４は、ロータ本体２に軸
方向に差し込まれてロータ本体２に組み付けられる。動
翼要素１は、更に、根付部４の外周側に同体化されてい
るプロファイル部５を備えている。プロファイル部５
は、翼面を形成している。動翼要素１は、プロファイル
部５の外周側に同体化されている棚部６を備えている。
棚部６の集合は、輪板を形成する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Corresponding to the drawings, an embodiment of a turbine rotor blade according to the present invention has a rotor blade element provided together with a rotor body. As shown in FIG. 1, a plurality of rotor blade elements 1 are attached to the outer peripheral region of the rotor main body 2. Each rotor blade element 1 includes a root portion 4 having a curved surface corresponding to the groove surface 3 formed in the rotor main body 2 and narrowing toward the center. The root portion 4 is inserted into the rotor main body 2 in the axial direction and assembled to the rotor main body 2. The bucket element 1 further includes a profile portion 5 integrated on the outer peripheral side of the root portion 4. Profile part 5
Form a wing surface. The bucket element 1 has a shelf 6 integrated on the outer peripheral side of the profile section 5.
The collection of the shelves 6 forms a wheel plate.
【００１６】隣り合う棚部６は、凹凸嵌合している。図
２に示されるように、２つの棚部６−１，６−２の内の
一方の棚部６−１は、それの端面７から円周方向Ａに延
びる第１円周方向延長部８と、第１円周方向鉛直部８の
端部から半径方向外側に延びる第１半径方向延長部９と
を備えている。Adjacent shelves 6 are fitted to each other. As shown in FIG. 2, one of the two shelves 6-1 and 6-2 has a first circumferential extension 8 extending in the circumferential direction A from an end face 7 thereof. And a first radial extension 9 extending radially outward from an end of the first circumferential vertical portion 8.
【００１７】２つの棚部の内の他方の棚部６−２は、そ
れの端面１１から円周方向Ａと逆方向である逆円周方向
Ｂに延びる第２円周方向延長部１２と、第２円周方向鉛
直部の端部から前記半径方向と逆方向に延びる第２半径
方向延長部１３とを備えている。第１半径方向延長部９
と第２半径方向延長部１３との円周方向の前後関係は、
一方の棚部６−１と他方の棚部６−２との円周方向の前
後関係に対して逆関係である。The other of the two shelves 6-2 has a second circumferential extension 12 extending from an end face 11 thereof in a reverse circumferential direction B opposite to the circumferential direction A; A second radially extending portion extending in a direction opposite to the radial direction from an end of the second circumferentially vertical portion. First radial extension 9
The circumferential front-back relationship between the second radial extension 13 and
This is opposite to the circumferential front-back relationship between one shelf 6-1 and the other shelf 6-2.
【００１８】第１半径方向延長部９の円周方向Ａに後方
の後端面と第２半径方向延長部１３の逆円周方向Ｂに後
方の後端面との間に、円周方向隙間幅がδであるクリア
ランス１４が与えられている。A circumferential gap width is defined between the rear end face of the first radial extension 9 in the circumferential direction A and the rear end face of the second radial extension 13 in the reverse circumferential direction B. A clearance 14 of δ is provided.
【００１９】組立時には、隣り合う棚部６−１，６−２
は、図３に示されるように、密着線１５で密着してい
る。運転時に動翼が回転して遠心力場が発生して、各動
翼要素は遠心方向に伸びる。その伸びは、棚部６の直径
の増大を促すが、円周長さの増大を促すことがなく、隣
り合う棚部は１円周上で相対的に逆方向に離反する。こ
の離反は、その離反方向にそれぞれに逆方向に相対的に
接近する第１半径方向延長部９と第２半径方向延長部１
３との間に形成されるクリアランスδを縮小させる。こ
の縮小は、やがて、クリアランスδを零にする。定格運
転時に、そのクリアランスδは零になるように適正に設
計されている。クリアランスδが実質的に零になって、
隣り合う棚部６は、円周方向にも同体化して連成し、棚
部６−１，・・ｎの集合体は、単一の連続帯状回転体と
して連成される。単一の連続帯状回転体の形成により、
動翼は無限翼として形成される。At the time of assembling, adjacent shelves 6-1 and 6-2
Are in close contact with each other by a contact line 15 as shown in FIG. During operation, the rotor blades rotate to generate a centrifugal force field, and each rotor blade element extends in the centrifugal direction. The expansion promotes an increase in the diameter of the shelf 6, but does not promote an increase in the circumferential length, and the adjacent shelves are relatively separated from each other on one circumference. This separation is caused by the first radial extension 9 and the second radial extension 1 relatively approaching each other in the separating direction.
3 is reduced. This reduction eventually reduces the clearance δ to zero. At the time of rated operation, the clearance δ is properly designed to be zero. When the clearance δ becomes substantially zero,
Adjacent shelves 6 are also integrated and coupled in the circumferential direction, and an aggregate of the shelves 6-1,... N is coupled as a single continuous band-shaped rotator. By the formation of a single continuous belt-like rotating body,
The blade is formed as an infinite wing.
【００２０】隣り合う動翼の間、特に、隣り合う棚部の
両対向端面の間には、全面的にクリアランスが設けら
れ、密着線１５の線領域は隙間であってよい。そのよう
な隙間の存在は、かえって動翼の組立を容易にする。A clearance is provided entirely between the adjacent moving blades, in particular, between both opposing end surfaces of the adjacent shelves, and a line region of the contact line 15 may be a gap. The existence of such a gap rather facilitates the assembly of the blade.
【００２１】図４は、本発明によるタービン動翼の実施
の他の形態を示している。隣り合う棚部６は、凹凸嵌合
している。２つの棚部６−１，６−２の内の一方の棚部
６−１は、図５に示されるように、それの端面７から円
周方向Ａに延びる第１円周方向延長部８’を備えてい
る。第１円周方向鉛直部８’には、それの面上から放射
方向（半径方向外側）に突出する円錐状突起２１が第１
円周方向延長部８’と一体に形成されている。FIG. 4 shows another embodiment of the turbine bucket according to the present invention. Adjacent shelves 6 are fitted with concave and convex. As shown in FIG. 5, one of the two shelves 6-1 and 6-2 has a first circumferentially extending portion 8 extending in a circumferential direction A from an end face 7 thereof. Have '. The first circumferential vertical portion 8 'is provided with a conical projection 21 projecting radially outward from the surface of the first vertical portion 8'.
It is formed integrally with the circumferential extension 8 '.
【００２２】２つの棚部の内の他方の棚部６−２には、
それから円周方向Ａと逆方向である逆円周方向Ｂに延び
る第２円周方向延長部１２’を備えている。第２円周方
向延長部１２’には、逆放射方向（半径方向内側）に貫
通する円錐状穴２２が形成されている。円錐状突起２１
と円錐状穴２２との円周方向の間に、円周方向隙間幅が
δであるクリアランス１４’が図４に示されるように与
えられている。クリアランス１４’は、隣り合う２つの
棚部６−１，６−２が円周方向に離反する際に、零化す
るように形成されている。In the other shelf 6-2 of the two shelves,
There is a second circumferential extension 12 'extending in a reverse circumferential direction B which is opposite to the circumferential direction A. The second circumferential extension 12 ′ is formed with a conical hole 22 that penetrates in the reverse radial direction (radially inward). Conical projection 21
A clearance 14 ′ having a circumferential gap width of δ is provided between the groove and the conical hole 22 in the circumferential direction as shown in FIG. The clearance 14 'is formed so as to be nullified when two adjacent shelves 6-1 and 6-2 separate in the circumferential direction.
【００２３】本実施の形態では、一方の動翼要素に他方
の動翼要素が相対的に軸方向に差し込まれる際、円錐状
突起２１と円錐状穴２２とは無理矢理に嵌まり合う。隣
り合う棚部６−１，６−２が接合する密着線１５が、隙
間として形成され得ることは既述の先の実施の形態に同
じである。In the present embodiment, when the one moving blade element is inserted into the other moving blade element relatively in the axial direction, the conical projection 21 and the conical hole 22 are forcedly fitted. It is the same as the previous embodiment that the contact line 15 where the adjacent shelves 6-1 and 6-2 are joined can be formed as a gap.
【００２４】[0024]
【発明の効果】本発明によるタービン動翼及びその連成
方法は、放射方向の伸びを利用して回転時の連成を実現
しているので、連成効果を低コストで実現することがで
きる。According to the turbine rotor blade and the coupling method thereof according to the present invention, the coupling at the time of rotation is realized by utilizing the elongation in the radial direction, so that the coupling effect can be realized at low cost. .
【図１】図１は、本発明によるタービン動翼の実施の形
態を示す断面図である。FIG. 1 is a cross-sectional view showing an embodiment of a turbine bucket according to the present invention.
【図２】図２は、図１の一部の断面図である。FIG. 2 is a cross-sectional view of a part of FIG.
【図３】図３は、図２の一部の平面図である。FIG. 3 is a plan view of a part of FIG. 2;
【図４】図４は、本発明によるタービン動翼の実施の形
態を示す断面図である。FIG. 4 is a cross-sectional view showing an embodiment of a turbine bucket according to the present invention.
【図５】図５は、図４の一部を示す射軸投影図である。FIG. 5 is an axial projection view showing a part of FIG. 4;
【図６】図６は、図５の一部の平面図である。FIG. 6 is a plan view of a part of FIG. 5;
【図７】図７は、公知装置を示す断面図である。FIG. 7 is a cross-sectional view showing a known device.
【図８】図８は、図７の一部の射軸投影図である。FIG. 8 is an axial projection view of a part of FIG. 7;
【図９】図９は、図７の一部の平面図である。FIG. 9 is a plan view of a part of FIG. 7;
２…ロータ本体 ４…結合部 ５…プロファイル部 ６…棚部 ８，８’…第１円周方向延長部 ９…第１半径方向延長部 １２，１２’…第２円周方向延長部 １３…第２半径方向延長部 ２１…凸部 ２２…凹部 2 rotor body 4 coupling part 5 profile part 6 shelf 8 and 8 'first circumferential extension 9 ... first radial extension 12 and 12' second circumferential extension 13 2nd radial extension part 21 ... convex part 22 ... concave part
Claims (6)
し前記ロータ本体の円周方向に並ぶ複数の動翼要素を含
み、 各１つの前記動翼要素は、 前記ロータ本体に結合する結合部と、 前記結合部に同体化され前記結合部より半径方向外側に
位置するプロファイル部と、 前記プロファイル部に同体化され前記プロファイル部よ
り前記半径方向外側に位置する棚部とを備え、 隣り合う２つの前記動翼要素のそれぞれの２つの前記棚
部の間には、静止時に存在するが、回転時の遠心力より
前記２つの棚部が円周方向に遠ざかることにより実質的
に消滅するクリアランスが介設され、 前記回転時に前記複数の動翼要素は連成するタービン動
翼。1. A rotor body, comprising: a plurality of blade elements arranged around the rotor body, connected to the rotor body, and arranged in a circumferential direction of the rotor body; A coupling portion coupled to the rotor body; a profile portion integrated with the coupling portion and positioned radially outward from the coupling portion; and a shelf integrated with the profile portion and positioned radially outward from the profile portion. And between the two shelves of each of the two adjacent blade elements, which are present at rest, but are separated in the circumferential direction by the two shelves due to centrifugal force during rotation. A turbine rotor blade having a clearance that substantially disappears, wherein the plurality of rotor blade elements are coupled during the rotation.
と、 前記第１円周方向延長部の端部から半径方向に延びる第
１半径方向延長部とを備え、 前記２つの前記動翼要素の内の他方の動翼要素は、 それの端面から前記円周方向と逆方向に延びる第２円周
方向延長部と、 前記第２円周方向延長部の端部から前記半径方向と逆方
向に延びる第２半径方向延長部とを備え、 前記第１円周方向延長部と前記第２円周方向延長部との
円周方向の前後関係は、前記一方の動翼要素と前記他方
の動翼要素との円周方向の前後関係に対して逆関係であ
り、 前記クリアランスは、前記第１半径方向延長部と前記第
２半径方向延長部との円周方向の間に介設されているタ
ービン動翼。2. The blade according to claim 1, wherein one of the two blade elements has a first circumferential extension extending circumferentially from an end face thereof, and the first circumference. A first radial extension extending radially from an end of a direction extension, wherein the other of the two blade elements has a direction opposite to the circumferential direction from an end face thereof. A second circumferential extension extending from the end of the second circumferential extension, and a second radial extension extending in a direction opposite to the radial direction from an end of the second circumferential extension. The circumferential relationship with the second circumferential extension is opposite to the circumferential relationship between the one moving blade element and the other moving blade element, and the clearance is: Turbine interposed between the first radial extension and the second radial extension in the circumferential direction Rotor blades.
備え、 前記２つの前記動翼要素の内の他方の動翼要素は、 それの端面から前記円周方向と逆方向に延びる第２円周
方向延長部を備え、 前記第１円周方向延長部と前記第２円周方向延長部とに
は、半径方向に嵌まりあう凸部と凹部が形成され、 前記クリアランスは、前記凸部と前記凹部と円周方向の
間に形成されているタービン動翼。3. The blade element according to claim 1, wherein one of the two blade elements has a first circumferential extension extending circumferentially from an end surface thereof. The other blade element of the blade element has a second circumferential extension extending from an end face thereof in a direction opposite to the circumferential direction, and the first circumferential extension and the second circumference. A turbine blade is formed in the direction extension portion so as to have a convex portion and a concave portion fitted in the radial direction, and the clearance is formed between the convex portion and the concave portion and the circumferential direction.
いて、 前記クリアランスの幅は２０μｍ〜７０μｍであるター
ビン動翼。4. The turbine bucket according to claim 1, wherein the width of the clearance is 20 μm to 70 μm.
部に同体化され前記結合部より半径方向外側に位置する
プロファイル部と、前記プロファイル部に同体化され前
記プロファイル部より前記半径方向外側に位置する棚部
とを備える動翼要素の多数が円周方向に並ぶタービン翼
の連成方法であり、 静止時に隣り合う２つの前記棚部の間に円周方向のクリ
アランスを与えること、 回転時に遠心力により２つの前記棚部（６）を円周方向
に離隔させることにより、前記クリアランスを実質的に
消滅させることとを含むタービン動翼の連成方法。5. A coupling portion coupled to the rotor body, a profile portion integrated with the coupling portion and located radially outward from the coupling portion, and a profile portion integrated with the profile portion and radially outward from the profile portion. A turbine blade having a plurality of blade elements arranged in a circumferential direction, the method comprising: providing a circumferential clearance between two adjacent shelves at rest, A method for coupling turbine blades, which comprises substantially eliminating the clearance by separating the two ledges (6) in the circumferential direction sometimes by centrifugal force.
ータ本体（２）の外周側に動翼要素を同体化すること、 ロータ本体に他の１つの動翼要素を軸方向に挿入して前
記ロータ本体の外周側に前記動翼要素を同体化するこ
と、 前記１つの動翼要素の最外周領域部分の円周方向に面す
る端面と前記他の１つの動翼要素の最外周領域部分の円
周方向に面する端面とを接合することとを含み、 前記１つの動翼要素の最外周領域部分の円周方向に面す
る他の端面と前記他の１つの動翼要素の最外周領域部分
の円周方向に面する他の端面との間に、前記２つの動翼
要素が遠心力により円周方向に離隔する時に前記円周方
向に縮小する前記クリアランスが与えられているタービ
ン動翼の連成方法。6. The rotor body according to claim 5, wherein one rotor element is inserted in the rotor body in the axial direction so that the rotor element is integrated on the outer peripheral side of the rotor body. Inserting three moving blade elements in the axial direction to integrate the moving blade elements on the outer peripheral side of the rotor main body; and a circumferentially facing end face of an outermost peripheral region portion of the one moving blade element and the other. Joining the end face of the outermost peripheral region portion of the one moving blade element facing in the circumferential direction, and the other end surface of the outermost peripheral region portion of the one moving blade element facing in the circumferential direction. When the two blade elements are separated in the circumferential direction by centrifugal force between the other blade surface and the other circumferentially facing end face of the outermost peripheral region portion of the other one blade element, A method for coupling a turbine blade provided with the clearance to be reduced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000008251A JP2001200701A (en) | 2000-01-17 | 2000-01-17 | Turbine rotor blade and coupling method therefor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000008251A JP2001200701A (en) | 2000-01-17 | 2000-01-17 | Turbine rotor blade and coupling method therefor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2001200701A true JP2001200701A (en) | 2001-07-27 |
Family
ID=18536558
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2000008251A Pending JP2001200701A (en) | 2000-01-17 | 2000-01-17 | Turbine rotor blade and coupling method therefor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2001200701A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003102378A1 (en) * | 2002-05-31 | 2003-12-11 | Kabushiki Kaisha Toshiba | Turbine moving blade |
| EP1764479A1 (en) * | 2005-09-15 | 2007-03-21 | ALSTOM Technology Ltd | Coupled shroud plates for a row of blades of a turbomachine |
| JP2008215091A (en) * | 2007-02-28 | 2008-09-18 | Hitachi Ltd | Turbine blade |
| WO2012041651A1 (en) * | 2010-09-30 | 2012-04-05 | Siemens Aktiengesellschaft | Blade ring segment, turbomachine and method for producing same |
| EP2888450A4 (en) * | 2012-08-27 | 2016-11-02 | United Technologies Corp | DOOR-TO-FAULT STATOR FOR FOLDING BOARD |
| EP3597861A1 (en) * | 2018-07-19 | 2020-01-22 | United Technologies Corporation | Contact coupled airfoil singlets |
| WO2023247903A1 (en) * | 2022-06-22 | 2023-12-28 | Safran Aircraft Engines | Bladed assembly for a turbomachine, turbine for a turbomachine, and turbomachine |
| FR3159626A1 (en) * | 2024-02-27 | 2025-08-29 | Safran Aircraft Engines | Device for damping the bladed assembly of an aircraft turbomachine |
-
2000
- 2000-01-17 JP JP2000008251A patent/JP2001200701A/en active Pending
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003102378A1 (en) * | 2002-05-31 | 2003-12-11 | Kabushiki Kaisha Toshiba | Turbine moving blade |
| EP1764479A1 (en) * | 2005-09-15 | 2007-03-21 | ALSTOM Technology Ltd | Coupled shroud plates for a row of blades of a turbomachine |
| US7874791B2 (en) | 2005-09-15 | 2011-01-25 | Alstom Technology Ltd. | Turbomachine |
| JP2008215091A (en) * | 2007-02-28 | 2008-09-18 | Hitachi Ltd | Turbine blade |
| WO2012041651A1 (en) * | 2010-09-30 | 2012-04-05 | Siemens Aktiengesellschaft | Blade ring segment, turbomachine and method for producing same |
| EP3339608A3 (en) * | 2012-08-27 | 2018-09-05 | United Technologies Corporation | Shiplap cantilevered stator |
| EP2888450A4 (en) * | 2012-08-27 | 2016-11-02 | United Technologies Corp | DOOR-TO-FAULT STATOR FOR FOLDING BOARD |
| US10309235B2 (en) | 2012-08-27 | 2019-06-04 | United Technologies Corporation | Shiplap cantilevered stator |
| EP3597861A1 (en) * | 2018-07-19 | 2020-01-22 | United Technologies Corporation | Contact coupled airfoil singlets |
| US10738634B2 (en) | 2018-07-19 | 2020-08-11 | Raytheon Technologies Corporation | Contact coupled singlets |
| WO2023247903A1 (en) * | 2022-06-22 | 2023-12-28 | Safran Aircraft Engines | Bladed assembly for a turbomachine, turbine for a turbomachine, and turbomachine |
| FR3137122A1 (en) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Bladed assembly with inter-platform connection by friction member |
| FR3159626A1 (en) * | 2024-02-27 | 2025-08-29 | Safran Aircraft Engines | Device for damping the bladed assembly of an aircraft turbomachine |
| WO2025181450A1 (en) * | 2024-02-27 | 2025-09-04 | Safran Aircraft Engines | Aircraft turbine engine bladed assembly, centred on a central axis, and aircraft turbine engine turbine |
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