JPS63273000A - Impeller of compressor - Google Patents
Impeller of compressorInfo
- Publication number
- JPS63273000A JPS63273000A JP62104380A JP10438087A JPS63273000A JP S63273000 A JPS63273000 A JP S63273000A JP 62104380 A JP62104380 A JP 62104380A JP 10438087 A JP10438087 A JP 10438087A JP S63273000 A JPS63273000 A JP S63273000A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- rotor
- solid portion
- embedding
- solid
- 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
- 239000007787 solid Substances 0.000 claims abstract description 42
- 239000007943 implant Substances 0.000 claims description 10
- 230000000694 effects Effects 0.000 abstract description 14
- 230000002093 peripheral effect Effects 0.000 abstract 1
- 238000013016 damping Methods 0.000 description 12
- 230000006835 compression Effects 0.000 description 8
- 238000007906 compression Methods 0.000 description 8
- 239000012530 fluid Substances 0.000 description 6
- 238000009434 installation Methods 0.000 description 6
- 230000005284 excitation Effects 0.000 description 5
- 239000002184 metal Substances 0.000 description 4
- 230000002238 attenuated effect Effects 0.000 description 3
- 238000002513 implantation Methods 0.000 description 3
- 239000000470 constituent Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 241000283973 Oryctolagus cuniculus Species 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 230000005279 excitation period Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 210000002784 stomach Anatomy 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 238000011144 upstream manufacturing 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F01D5/16—Form or construction for counteracting blade vibration
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の目的〕
（産業上の利用分野）
本発明は、軸流圧縮機等に採用される圧縮機１ｌＩＨに
係り、特にＩ！ｌＩ９！において発生する振動を効果的
に減衰し得る圧縮機動翼に関する。[Detailed Description of the Invention] [Object of the Invention] (Industrial Application Field) The present invention relates to a compressor 11IH employed in an axial flow compressor, etc., and particularly relates to an I! lI9! The present invention relates to a compressor rotor blade that can effectively damp vibrations generated in a compressor.
（従来の技術）
軸流圧縮機等の圧縮機動翼の構造は一般に第４図に例示
するように、ロータ１の外周部に所定間隔を・おいて軸
方向に複数のロータ植込溝２を形成し、この０−夕植込
溝２に嵌合体３が嵌入される。嵌合体３は、四右効部４
を一体に接合したＮ植込ソリッド部３ａと、翼植込ソリ
ッド部３ａからロータ１の周方向に膨出した翼植込嵌合
部３ｂとから成る。(Prior Art) Generally, the structure of a compressor rotor blade such as an axial flow compressor, as illustrated in FIG. The fitting body 3 is fitted into this zero-seam planting groove 2. The fitted body 3 has four right-handed parts 4
It consists of an N-embedded solid part 3a which is integrally joined to the blade-embedded solid part 3a, and a vane-embedded fitting part 3b that bulges out in the circumferential direction of the rotor 1 from the vane-embedded solid part 3a.
動翼本体となる翼有効部はその機能上の制約から従来の
タービン動黄と比較して翼厚が薄く構成されており、こ
の翼有効部によって圧縮機に吸い込まれた気体に仕事が
付与され、気体は圧縮される。Due to functional constraints, the blade effective part, which is the main body of the rotor blade, is thinner than that of conventional turbine rotors, and this blade effective part imparts work to the gas sucked into the compressor. , the gas is compressed.
一方、翼有効部を所定位置に固定する嵌合体３の翼植込
ソリッド部３ａの高ざ１−１は、高速回転時における体
積力を可及的に低減するために小さく設定され、また翼
有動部４に作用する遠心力がＮ植込嵌合部３ｂに均等に
伝達されたときにロータ１が強麿的に十分耐え（７る必
要最小高さに調整されている。On the other hand, the height 1-1 of the blade embedded solid part 3a of the fitting body 3 that fixes the blade effective part in a predetermined position is set small in order to reduce the body force as much as possible during high-speed rotation, and the blade The rotor 1 is adjusted to the required minimum height so that it can withstand sufficiently when the centrifugal force acting on the active part 4 is evenly transmitted to the N-type fitting part 3b.
ところで、回転翼を有する流体機器においては、一般に
流体の流れの不均一さに起因してその運転に支障をぎた
′？ｉ場合がある。特に圧縮機動翼においは、いわゆる
サージング現牟によって軸振動成分およびΦ力等により
励振力が作用し、さらにこの励振力が配管を含めた＃ｆ
Ｍ器系仝休に体わる固有振動数とも競合覆る結果、比較
的低い振動数で振動を生じ、同１、ｉに特定の周期で吐
出ＪＥ力および叶出吊が変動する場合がある。By the way, in fluid equipment having rotary blades, the operation of the equipment is generally hindered due to non-uniformity of fluid flow. There are cases. In particular, on compressor rotor blades, excitation force acts on shaft vibration components and Φ force due to the so-called surging phenomenon, and this excitation force also acts on #f including piping.
As a result of competition with the natural frequency associated with the M system's rest, vibrations occur at a relatively low frequency, and the discharge JE force and leaf suspension may fluctuate at a specific period.
上記のような振動に対処するために、圧縮別動Ｗは、そ
のＷ植込嵌合部３ｂと０−夕植込満２との間の摩擦によ
る振動の減衰作用によって振幅を抑制し、Ｗ有効部４に
作用する振動応力の低減を図っている。In order to cope with the above-mentioned vibrations, the compression separate movement W suppresses the amplitude by a vibration damping effect due to the friction between the W implant fitting part 3b and the 0-Yu implant 2, and the W This is intended to reduce the vibration stress acting on the effective portion 4.
（発明が解決しようとする問題点）
しかしながら、従来の圧縮機のｖＪ翼構造においては、
ロータ植込溝に嵌入された翼植込ンリツド部およびＮ植
込嵌合部の剛性が田有動部の剛性と比較して極めて大ぎ
い。そのために、実際に振動が発生した場合の変形モー
ドは第５図に破線で例示するように舅有動部のみが大き
く変形することとなり、Ｎ植込嵌合部とロータ植込溝と
の摩擦による振動の減衰効果は極め°て少ない。(Problems to be solved by the invention) However, in the vJ blade structure of the conventional compressor,
The rigidity of the blade implanted lid part and the N implanted fitting part fitted into the rotor implanted groove is extremely large compared to the rigidity of the field moving part. Therefore, when vibration actually occurs, the deformation mode is such that only the leg moving part is greatly deformed, as illustrated by the broken line in Figure 5, and the friction between the N stud fitting part and the rotor implant groove is The vibration damping effect caused by this is extremely small.
上記構造の圧縮機動翼において前記の励振力が翼有動部
に作用すると、第５図の通り大きな変形を生じ、特に励
振周期と翼有動部の固有振動数とが共振した場合には、
相開的に増加する振動応力と部材の疲労のためにＷ有効
部の基端部が９期に破損に至る可能性がある。とりわけ
ガスタービンにおいては、その圧縮機は最上流部に配置
されているため、その破損により生じた金属片は下流部
のタービンまで流下し、タービン全体のＫｌ（＄２とい
う重大事故を誘発する可能性がある。When the excitation force acts on the moving part of the compressor blade having the above structure, a large deformation occurs as shown in Fig. 5, and especially when the excitation period and the natural frequency of the moving part resonate,
There is a possibility that the proximal end of the W effective part will break in the 9th stage due to the progressively increasing vibration stress and member fatigue. In particular, in gas turbines, the compressor is located at the most upstream part, so metal fragments caused by its damage may flow down to the downstream turbine, causing a serious accident with a total loss of Kl ($2) for the entire turbine. There is sex.
このように従来の圧縮機動翼においては、その構成材料
の特性による振動減衰作用と構成材料相互の摩擦による
振動減衰作用とを利用しているに過ぎないため、総合的
に減衰効果が極めて低いという問題点がある。In this way, conventional compressor rotor blades only utilize the vibration damping effect due to the characteristics of the constituent materials and the vibration damping effect due to friction between the constituent materials, so the overall damping effect is extremely low. There is a problem.
上記問題点を解決するために、タービンｆＪＪ 胃にお
いては、隣接する動翼を相互にレーシングワイヤで結束
する防振構造を採用したり、または第６図で例示するよ
うに各衷心動部４の上端部に板状のスナバカバー５を装
着して振動域＊’ｇ！１構とする対策もなされている。In order to solve the above problems, in the turbine fJJ stomach, a vibration isolation structure is adopted in which adjacent rotor blades are tied together with racing wires, or as illustrated in FIG. Attach a plate-shaped snubber cover 5 to the upper end to increase the vibration range*'g! Measures have also been taken to reduce the number of buildings to one.
振動発生時には、隣接するスナバカバー５の接触面６に
おけるｆｆ、擦および衝突による振動の減衰を図ってい
る。When vibration occurs, vibrations due to ff, friction, and collision on the contact surfaces 6 of the adjacent snubber covers 5 are attenuated.
しかしながら、上記構成の減衰機構をそのまま圧縮ｍ動
翼に採用りることは不可能である。すなわち、Ｆ１縮機
ｌｌｌ翼においでは翼右動部４の厚さが軽量であり、そ
の頂部にスナバカバー５を装着すると、回転による遠心
力が増大し、兎有動部４のす端部４ａの応力が許容応力
を超える危険性がある。However, it is impossible to directly apply the damping mechanism having the above structure to a compression m rotor blade. In other words, in the F1 compressor Ill wing, the thickness of the wing right moving part 4 is light, and when the snubber cover 5 is attached to the top, the centrifugal force due to rotation increases, and the end part 4a of the rabbit moving part 4 is There is a risk that the stress will exceed the allowable stress.
一方、スナバカバー５の遠心力をＪ：り低減するために
習有動部４の中間部位にスナバカバー５を取付けた場合
は、流体の流通に障害となり、翼の圧縮性能が低下する
原因となり、その性能低下は一般に１〜３％にも達し、
実用上好ましくない。On the other hand, if the snubber cover 5 is attached to the intermediate part of the driven moving part 4 in order to reduce the centrifugal force of the snubber cover 5, it will impede fluid circulation and cause a decrease in the compression performance of the blade. Performance degradation generally reaches 1-3%,
Practically unfavorable.
本発明は上記の問題点を解決するためになされたもので
あり、動翼による流体の圧縮性能を低下させることなく
、動翼に作用する振動を効果的に減衰し得る圧縮機動翼
を提供することを目的とする。The present invention has been made to solve the above problems, and provides a compressor rotor blade that can effectively damp vibrations acting on the rotor blade without reducing the fluid compression performance of the rotor blade. The purpose is to
（問題点を解決するための手段）
本発明に係る圧縮機動翼は、圧縮機ロータの外周部に所
定開隔をおいて軸方向に複数のロータ植込溝を形成し、
翼り動部を一体に接合した翼植込ソリッド部と翼植込ソ
リッド部からロータの周方向に膨出するＮ植込嵌合部と
から成る嵌合体を上記ロータ植込溝に■大して構成され
る圧縮機動内において、上記嵌合体の四植込ソリッド部
の断面二次モーメントと、翼右動部の断面二次モーメン
トとを等しく設定するとともに、ｍ１ｌｉ′ｉ込ソリッ
ド部外面と、対向する〇−タ植込満内面との間に間隙を
形成したことを特徴とする。(Means for Solving the Problems) A compressor rotor blade according to the present invention has a plurality of rotor implant grooves formed in the axial direction at a predetermined interval on the outer circumference of the compressor rotor,
A fitted body consisting of a blade embedded solid part that integrally joins the blade moving part and an N embedded fitting part that bulges out in the circumferential direction of the rotor from the blade embedded solid part is arranged in the rotor embedded groove. In the compressor machine, the moment of inertia of the four embedded solid parts of the fitted body and the moment of inertia of the wing right moving part are set to be equal, and the outer surface of the solid part with m1li'i and the 〇-A gap is formed between the implant and the full surface.
（作用）
上記構成の圧縮Ｒ動響によれば、翼構造ソリッド部とＷ
有効部との断面二次モーメントが等しく設定されて一体
に接合され、かつ翼構造ソリッド部とロータ植込溝との
間に間隙が設けられているため、翼構造ソリッド部の剛
性は従来と比較して低下し、翼有動部と黄植込ソリッド
部とは一体になって振動による変形作用を受ける。その
ため、従来と比較して変形時に苦有動部の基端の接合部
に作用する応力が低下し、接合部の金属疲労が防止され
る。また、舅桶込ソリッド部は、対向するロータ植込溝
の内縁と衝突を繰り返し、その衝撃による減衰作用によ
って振動は急速に減衰される。(Function) According to the compressed R dynamic with the above configuration, the wing structure solid part and the W
Since the moment of inertia of the effective section and the effective section are set equal and they are joined together, and a gap is provided between the wing structure solid section and the rotor installation groove, the stiffness of the wing structure solid section is lower than before. The blade moving part and the yellow embedded solid part are integrally subjected to deformation action due to vibration. Therefore, compared to the conventional case, the stress acting on the joint at the proximal end of the moving part during deformation is reduced, and metal fatigue at the joint is prevented. In addition, the solid part with the toe bucket repeatedly collides with the inner edge of the opposing rotor installation groove, and the vibration is rapidly attenuated by the damping effect of the impact.
さらに、翼構造ソリッド部を遊嵌状態にしたことにより
Ｘ植込嵌合部がロータ植込溝に対して微動できるように
なるため、両省間に生じるｌ？擦による減衰作用も増加
し、振動は効果的に減衰される。Furthermore, by making the blade structure solid part into a loosely fitted state, the X-embedded fitting part can move slightly with respect to the rotor-embedded groove, so the l? The damping effect due to friction is also increased, and vibrations are effectively damped.
（実施例）
次に、本発明の一実施例について添付図面を参照して説
明する。(Example) Next, an example of the present invention will be described with reference to the accompanying drawings.
第１図は本発明に係る圧縮Ｉａ動翼の一実施例を示す断
面図である。なお、第４図〜第６図に示す従来例と同一
要素には同一符号を付している。FIG. 1 is a sectional view showing an embodiment of a compression Ia rotor blade according to the present invention. Note that the same elements as those in the conventional example shown in FIGS. 4 to 6 are given the same reference numerals.
本実施例の圧縮機動翼は、ロータ１の外周部に所定間隔
をおいて軸方向に形成された複数のロータ植込溝２と、
このロータ植込溝２に嵌入される嵌合体３と、嵌合体３
に一体に接合された翼有効？ｌ ４とから構成される。The compressor rotor blade of this embodiment includes a plurality of rotor installation grooves 2 formed in the axial direction at predetermined intervals on the outer circumference of the rotor 1,
A fitting body 3 fitted into this rotor implantation groove 2 and a fitting body 3
Is it possible to use a wing that is integrally joined to a wing? It consists of 4.
さらに、嵌合体３は、衷右動部４ど接合する翼構造ソリ
ッド部３ａと、翼植込ンリッド２１＜３ａからロータ１
の周方向に膨出する翼構造１！；合部３ｂとから成る。Furthermore, the fitted body 3 includes a blade structure solid part 3a that joins the lateral movement part 4, and a rotor 1 from the blade implant lid 21<3a.
Wing structure 1 that bulges out in the circumferential direction! ; and a joining part 3b.
１■合体３のＷ植込ソリッド部３ａの断面二次モーメシ
トと■有効部４の断面二次モーメントは等しく設定され
る。具体的には、翼植込ンリッド部３ａとｖＩＪ植込嵌
合部３ｂとの境界部Ａの高面積を減少きせることによっ
て、その部分の断面二次モーメントを翼有動部４の振動
方向に対する断面二次モーメントに等しく調整している
。また、翼構造ソリッド部３ａと、対向するロータ植込
溝２との間には間隙７が形成される。1) The cross-sectional moment of inertia of the W implanted solid portion 3a of the combined body 3 and (2) the cross-sectional moment of inertia of the effective portion 4 are set to be equal. Specifically, by reducing the high area of the boundary part A between the blade implantable lid part 3a and the vIJ implantable fitting part 3b, the moment of inertia of that part is reduced with respect to the vibration direction of the blade driven part 4. Adjusted to be equal to the moment of inertia. Further, a gap 7 is formed between the blade structure solid portion 3a and the opposing rotor installation groove 2.
本実施例に係る圧縮機動翼において、運転中にリーーシ
ング等が発生し、動翼に励振力が作用し、または動翼の
共振現宋が発生した場合、翼構造ソリッド部３ａと一体
になって柔構造を構成した翼右動部４は、第２図におい
て破線で例示するように、嵌合体３の境界部へを節とし
た振動モードを形成する。そのため、従来のようにＷ有
効部４の基端部４ａに振動変形による応力が集中するこ
とが少なく、基端部４ａの金属疲労が防止される。In the compressor rotor blade according to this embodiment, if leasing or the like occurs during operation, excitation force acts on the rotor blade, or resonance occurs in the rotor blade, the rotor blade becomes integral with the blade structure solid portion 3a. The wing right movement section 4 having a flexible structure forms a vibration mode with a node at the boundary of the fitted body 3, as illustrated by the broken line in FIG. Therefore, stress due to vibration deformation is less likely to concentrate on the base end 4a of the W effective portion 4 as in the prior art, and metal fatigue of the base end 4a is prevented.
また、翼構造ソリッド部３ａは、対向するロータ植込溝
２に繰り返して衝突するため、その衡撃ににる減衰作用
によって振動が効果的に減衰される。Further, since the blade structure solid portion 3a repeatedly collides with the opposing rotor installation groove 2, vibrations are effectively damped by the damping effect caused by the equal impact.
また、（２）有効部４の最大振幅に対応して境界部へに
発生する応力を部材の許容応力以内に収めるように間隙
７の１払δを設定することにより、共振時においても動
Ｗの破損という事態を回避することができる。(2) By setting the δ of the gap 7 so that the stress generated in the boundary part corresponding to the maximum amplitude of the effective part 4 is within the allowable stress of the member, the dynamic W It is possible to avoid the situation of damage.
さらに本実施例では、兎有効部４自体には流体の流れを
阻害する障害物を何ら装着するものではなく、嵌合部の
形状のみを変更している。したがって、動翼による流体
の圧縮性能を低下させることな（、振動を効果的に減衰
さゼることができる。Furthermore, in this embodiment, no obstacle to obstruct the flow of fluid is attached to the effective part 4 itself, and only the shape of the fitting part is changed. Therefore, vibrations can be effectively damped without reducing the fluid compression performance of the rotor blades.
次に、本発明の他の実施例を第３図に従って説明する。Next, another embodiment of the present invention will be described with reference to FIG.
本実施例においては、翼構造ソリッド部３ａの高８１−
１を、第１図に示す実施例と比較して半径り向に廷伸し
ている。In this embodiment, the height 81-
1 has been extended in the radial direction compared to the embodiment shown in FIG.
この場合、翼構造ソリッド部３ａに一体に接合された川
石動部４の見掛は上の剛性はさらに低下し、振動発生時
に基端部４ａｋ：発生する応）Ｊは、第１図に示す実施
例の場合と比較してさらに低減される。また、ロータ植
込溝２に対する翼構造ソリッド部３ｂの衝突が容易にな
るため、その衝撃による振動の減衰効果が高まる。In this case, the apparent stiffness of the river stone moving part 4 integrally joined to the wing structure solid part 3a is further reduced, and when vibration occurs, the base end part 4ak: generated (response) J is as shown in FIG. This is further reduced compared to the example. Furthermore, since the blade structure solid portion 3b collides easily with the rotor implant groove 2, the effect of damping vibrations caused by the impact is enhanced.
以上説明の通り、本発明の圧縮ｔｉ動翼によれば、！Ｆ
２植込ソリッド部と専有動部との断面二次モーメントが
等しく設定され、かつ嬰植込ソリッド部とロータ植込溝
との間に間隙が設けられているため、翼構込ソリッド部
の剛性は従来と比較して大幅に低下する。そのため、動
翼部に励振力が作用した場合は、Ｗ植込ソリッド部と専
有動部とは一体となって間隙の範囲内で変形する。As explained above, according to the compression Ti rotor blade of the present invention,! F
2. The moment of inertia of the solid part and the dedicated moving part are set equal, and a gap is provided between the solid part and the rotor groove, so the rigidity of the solid part of the wing is increased. is significantly lower than before. Therefore, when an excitation force is applied to the rotor blade section, the W-embedded solid section and the dedicated moving section are deformed as one within the range of the gap.
したがって、腎石動部の翼構込ソリッド部との接合部に
作用する応力が低下し、接合部の金属疲労が防１トされ
る。また、翼構込ソリッド部は対向するロータ植込溝と
衝突を繰り返し、その衝撃にＪ、る減衰作用によって振
動を減衰覆ることができる。Therefore, the stress acting on the joint between the nephrolithic part and the wing-containing solid part is reduced, and metal fatigue at the joint is prevented. In addition, the blade built-in solid portion repeatedly collides with the opposing rotor installation groove, and the vibration can be damped and covered by the damping effect of the impact.
さらに、Ｆ！植込ソリッド部を遊嵌状態にしたことによ
り翼構込嵌合部がロータ植込溝に対して微動できるよう
になるため、両者の接触面に生じる摩擦による減衰作用
も増加し、振動がより効宋的に減衰される。Furthermore, F! By making the embedded solid part into a loose fit state, the blade structure fitting part can move slightly with respect to the rotor embedded groove, so the damping effect due to the friction generated on the contact surface between the two increases, and vibration is further reduced. The effect was attenuated during the Song Dynasty.
第１図は本発明の圧縮機動翼の一実施例を示す断面図、
第２図は専有動部に振動が発生した状態を示す断面図、
第３図は本発明の他の実施例を示す断面図、第４図は従
来の圧縮１ｉｊＭ ｆｌＪＩＢのｖ４造を示す斜視図、
第５図は第４図の専有動部を拡大して示寸断面図、第６
図は従来のタービン動翼の一構成例を示す斜視図である
。
１・・・ロータ、２・・・ロータ植込溝、３・・・嵌合
体、３ａ・・・ＴＡ植込ソリッド部、３ｂ・・・翼構込
嵌合部、４・・・専有動部、４ａ・・・基端部、５・・
・スナバカバー、６・・・接触面、７・・・間隙、Ａ・
・・境界部、１１・・・Ｗ植込ソリッド部の高さ、δ・
・・間隙寸法。
出願人代理人 波 多 野 久第４図
−トー−１賑FIG. 1 is a sectional view showing an embodiment of the compressor rotor blade of the present invention;
Figure 2 is a cross-sectional view showing a state where vibration occurs in the proprietary moving part.
FIG. 3 is a sectional view showing another embodiment of the present invention, FIG. 4 is a perspective view showing a conventional compression 1ijM flJIB v4 structure,
Figure 5 is an enlarged cross-sectional view of the proprietary moving part in Figure 4;
The figure is a perspective view showing an example of the configuration of a conventional turbine rotor blade. DESCRIPTION OF SYMBOLS 1... Rotor, 2... Rotor implantation groove, 3... Fitting body, 3a... TA implantation solid part, 3b... Blade structure fitting part, 4... Exclusive moving part , 4a... proximal end, 5...
・Snubber cover, 6...Contact surface, 7...Gap, A・
・Boundary part, 11...Height of W implanted solid part, δ・
・Gap dimension. Applicant's agent Hisashi Hatano Figure 4-To-1 Busy
Claims (1)
のロータ植込溝を形成し、翼有効部を一体に接合した翼
植込ソリッド部と翼植込ソリッド部からロータの周方向
に膨出する翼植込嵌合部とから成る嵌合体を上記ロータ
植込溝に嵌入して構成される圧縮機動翼において、上記
嵌合体の翼植込ソリッド部の断面二次モーメントと、翼
有効部の断面二次モーメントとを等しく設定するととも
に、翼植込ソリッド部外面と、対向するロータ植込溝内
面との間に間隙を形成したことを特徴とする圧縮機動翼
。A plurality of rotor implant grooves are formed in the axial direction at predetermined intervals on the outer periphery of the compressor rotor, and a blade implant solid part where the blade effective part is integrally joined and a blade implant solid part are formed in the circumferential direction of the rotor. In a compressor rotor blade configured by fitting a fitted body consisting of a bulging blade embedded fitting part into the rotor embedded groove, the moment of inertia of the blade solid part of the fitted body and the blade effective 1. A compressor rotor blade, characterized in that the moment of inertia of the solid part of the blade is set to be equal, and a gap is formed between the outer surface of the blade-embedded solid part and the opposing inner surface of the rotor-embedded groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP62104380A JPS63273000A (en) | 1987-04-30 | 1987-04-30 | Impeller of compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP62104380A JPS63273000A (en) | 1987-04-30 | 1987-04-30 | Impeller of compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63273000A true JPS63273000A (en) | 1988-11-10 |
Family
ID=14379164
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP62104380A Pending JPS63273000A (en) | 1987-04-30 | 1987-04-30 | Impeller of compressor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63273000A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2669478A1 (en) | 2012-05-31 | 2013-12-04 | Hitachi, Ltd. | Compressor |
-
1987
- 1987-04-30 JP JP62104380A patent/JPS63273000A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2669478A1 (en) | 2012-05-31 | 2013-12-04 | Hitachi, Ltd. | Compressor |
| CN103452905A (en) * | 2012-05-31 | 2013-12-18 | 株式会社日立制作所 | Compressor |
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