JPH0913901A - Steam turbine - Google Patents

Steam turbine

Info

Publication number
JPH0913901A
JPH0913901A JP7159096A JP15909695A JPH0913901A JP H0913901 A JPH0913901 A JP H0913901A JP 7159096 A JP7159096 A JP 7159096A JP 15909695 A JP15909695 A JP 15909695A JP H0913901 A JPH0913901 A JP H0913901A
Authority
JP
Japan
Prior art keywords
steam
rotor disk
side end
outlet side
radial direction
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.)
Granted
Application number
JP7159096A
Other languages
Japanese (ja)
Other versions
JP3499970B2 (en
Inventor
Hisakuni Takenaga
久邦 竹永
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to JP15909695A priority Critical patent/JP3499970B2/en
Publication of JPH0913901A publication Critical patent/JPH0913901A/en
Application granted granted Critical
Publication of JP3499970B2 publication Critical patent/JP3499970B2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE: To prevent the steam flowing in the radial direction along the output side end face of a rotor disk from colliding with the steam at the outlets of speed governing stage moving blades by prodding a cylinder section protruded into a bayonet point shape near the outer periphery of the outlet side end face of the rotor disk planted with the speed governing state moving blades. CONSTITUTION: A cylindrical bayonet point 9 curved on the inside is protruded near the outer periphery of the outlet side end face 4 of a rotor disk 3, and the bayonet point 9 is directed to the direction of a rotor shaft. The steam 10 flowing in the radial direction along the outlet side end face 4 of the rotor disk 3 is changed in direction toward the downstream direction of the rotor shaft or the inside of the radial direction of the rotor disk 3. Since the cylindrical bayonet point 9 is protruded toward the downstream direction of the rotor shaft near the outer periphery of the outlet side end face 4 of the rotor disk 3 of speed governing stage moving blades 2, the steam 10 flowing in the radial direction along the outlet side end face 4 of the rotor disk 3 is changed in direction and is prevented from crossing the steam 7 at the outlets of the speed governing stage moving blades 2 nearly in the perpendicular direction to collide with it.

Description

【発明の詳細な説明】Detailed Description of the Invention

【０００１】[0001]

【産業上の利用分野】本発明は、火力発電などに適用さ
れる蒸気タービンに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a steam turbine applied to thermal power generation and the like.

【０００２】[0002]

【従来の技術】図２は火力発電などに使用されている従
来の蒸気タービンの説明図である。図において、ロータ
ディスク３には調速段動翼２が植込まれており、ロータ
ディスク３は通常の円板状をなしている。図における符
号１は蒸気のノズル、４はロータディスク３の出口側端
面、５は調速段動翼２の出口空間、６は次段動翼の入口
である。2. Description of the Related Art FIG. 2 is an explanatory diagram of a conventional steam turbine used for thermal power generation and the like. In the figure, a speed control blade 2 is embedded in a rotor disk 3, and the rotor disk 3 has a normal disc shape. In the figure, reference numeral 1 is a steam nozzle, 4 is an end face on the outlet side of the rotor disk 3, 5 is an outlet space of the speed control stage moving blade 2, and 6 is an inlet of the next stage moving blade.

【０００３】[0003]

【発明が解決しようとする課題】上記のように、従来の
蒸気タービンにおいては調速段動翼２のロータディスク
３が通常の円板状をなしており、調速段動翼２出口側に
おける蒸気の一部がロータディスク３が回転することに
よりロータディスク３出口側端面４に沿って半径方向へ
流れる。この半径方向へ流れる蒸気８が調速段動翼２出
口の蒸気７と略直角に交わって衝突による流れの損失を
生じ、蒸気タービンの性能を低下させる一因となってい
る。また、半径方向へ流れる蒸気８によって調速段動翼
２の出口空間５における有効面積が減少し、調速段動翼
２出口における蒸気の運動エネルギーが圧力エネルギー
に十分に回復しないため、これも蒸気タービンの性能を
低下させる一因となっている。As described above, in the conventional steam turbine, the rotor disk 3 of the speed control blade 2 has a normal disc shape, and the rotor disk 3 on the outlet side of the speed control blade 2 is provided. A part of the steam flows in the radial direction along the outlet-side end surface 4 of the rotor disk 3 as the rotor disk 3 rotates. The steam 8 flowing in the radial direction intersects with the steam 7 at the exit of the speed control blade 2 at a substantially right angle to cause a flow loss due to collision, which is one of the causes for lowering the performance of the steam turbine. Further, since the steam 8 flowing in the radial direction reduces the effective area in the exit space 5 of the speed control blade 2, the kinetic energy of the steam at the exit of the speed control blade 2 does not sufficiently recover to the pressure energy. This is one of the causes of lowering the performance of the steam turbine.

【０００４】[0004]

【課題を解決するための手段】本発明に係る蒸気タービ
ンは上記課題の解決を目的にしており、調速段動翼が植
込まれたロータディスクの出口側端面の外周近傍に剣先
状に突設され上記ロータディスクの出口側端面に沿って
半径方向へ流れる蒸気をロータ軸方向の下流乃至上記ロ
ータディスクの半径方向内側へ方向転換させる円筒部を
備えた構成を特徴とする。SUMMARY OF THE INVENTION A steam turbine according to the present invention is intended to solve the above-mentioned problems, and has a sword-like projection near the outer periphery of the outlet-side end face of a rotor disk in which speed-control blades are embedded. It is characterized in that it is provided with a cylindrical portion which is provided to divert steam flowing in the radial direction along the outlet side end surface of the rotor disk to a downstream side in the axial direction of the rotor or a radial inside of the rotor disk.

【０００５】[0005]

【作用】即ち、本発明に係る蒸気タービンにおいては、
調速段動翼が植込まれたロータディスクの出口側端面の
外周近傍に剣先状に円筒部が突設されロータディスクの
出口側端面に沿って半径方向へ流れる蒸気をロータ軸方
向の下流乃至ロータディスクの半径方向内側へ方向転換
させるようになっており、ロータディスクの出口側端面
の外周近傍に設けられた剣先状の円筒部によってロータ
ディスクの出口側端面に沿って半径方向へ流れる蒸気が
半径方向からロータ軸の下流方向乃至ロータディスクの
半径方向内側へ方向転換されることにより調速段動翼の
出口の蒸気と略直角に衝突しなくなって衝突による流れ
の損失を生じなくなるとともに、調速段動翼の出口空間
が半径方向へ流れる蒸気の影響を受けなくなって出口空
間における有効面積が確保され、調速段動翼の出口にお
ける蒸気の運動エネルギーが圧力エネルギーに十分に回
復する。That is, in the steam turbine according to the present invention,
A cylindrical portion projecting like a sword is formed near the outer periphery of the outlet side end surface of the rotor disk in which the speed control blades are implanted, and steam flowing in the radial direction along the outlet side end surface of the rotor disk is provided downstream or in the axial direction of the rotor. It is designed to change the direction to the inner side of the rotor disk in the radial direction, and the steam flowing in the radial direction along the outlet side end surface of the rotor disk is formed by the sword-shaped cylindrical portion provided near the outer circumference of the outlet side end surface of the rotor disk. By changing the direction from the radial direction to the downstream direction of the rotor shaft or the radial direction inside of the rotor disc, the steam does not collide with the steam at the outlet of the speed control blade at a substantially right angle, and the flow loss due to the collision does not occur. The exit space of the speed-changing blade is not affected by the steam flowing in the radial direction, so that the effective area in the exit space is secured, and the motion of the steam at the exit of the speed-control blade is Energy is sufficiently recovered to pressure energy.

【０００６】[0006]

【実施例】図１は本発明の一実施例に係る蒸気タービン
の説明図である。図において、本実施例に係る蒸気ター
ビンは火力発電などに使用されるもので、ロータディス
ク３には調速段動翼２が植込まれており、ロータディス
ク３は円板状をなしている。図における符号１は蒸気の
ノズル、４はロータディスク３の出口側端面、５は調速
段動翼の出口空間、６は次段動翼の入口である。1 is an explanatory view of a steam turbine according to an embodiment of the present invention. In the figure, the steam turbine according to the present embodiment is used for thermal power generation, etc., in which a rotor disk 3 is embedded with speed control blades 2, and the rotor disk 3 has a disk shape. . In the figure, reference numeral 1 is a steam nozzle, 4 is an end face on the outlet side of the rotor disk 3, 5 is an outlet space of the speed control stage moving blade, and 6 is an inlet of the next stage moving blade.

【０００７】本蒸気タービンにおいては図に示すように
ロータディスク３出口側端面４の外周近傍に内側が湾曲
した円筒状の剣先９が突設され、この剣先９をロータ軸
方向へ向けたことにより、ロータディスク３出口側端面
４に沿って半径方向へ流れる蒸気１０をロータ軸下流方
向乃至はロータディスク３半径方向の内側へ向けて方向
転換させるようにしている。このように調速段動翼２の
ロータディスク３出口側端面４を外周近傍に円筒状の剣
先９をロータ軸下流方向に向けて突出させた形状とした
ことにより、ロータディスク３出口側端面４に沿って半
径方向へ流れる蒸気１０が半径方向からロータ軸下流方
向乃至ロータディスク３半径内側方向へ方向転換されて
調速段動翼２出口の蒸気７と略直角方向に交わって衝突
することがなくなる。In the present steam turbine, as shown in the figure, a cylindrical blade tip 9 having a curved inside is provided in the vicinity of the outer periphery of the outlet side end surface 4 of the rotor disk 3, and the blade tip 9 is directed in the axial direction of the rotor. The steam 10 flowing in the radial direction along the outlet-side end surface 4 of the rotor disk 3 is redirected toward the downstream side of the rotor shaft or the inner side of the rotor disk 3 in the radial direction. In this way, the rotor disk 3 outlet side end surface 4 of the speed control blade 2 has a cylindrical blade tip 9 projecting toward the rotor shaft downstream in the vicinity of the outer periphery, whereby the rotor disk 3 outlet side end surface 4 The steam 10 flowing in the radial direction may be diverted from the radial direction to the downstream direction of the rotor shaft or the radial direction of the rotor disk 3 and may collide with the steam 7 at the outlet of the speed control stage rotor blade 2 at a substantially right angle. Disappear.

【０００８】従来の蒸気タービンにおいては調速段動翼
のロータディスクが通常の円板状をなしており、調速段
動翼出口側における蒸気の一部がロータディスクが回転
することによりロータディスク出口側端面に沿って半径
方向へ流れる。この半径方向へ流れる蒸気が調速段動翼
出口の蒸気と略直角に交わって衝突による流れの損失を
生じ、蒸気タービンの性能を低下させる一因となってい
る。また、半径方向へ流れる蒸気によって調速段動翼の
出口空間における有効面積が減少し、調速段動翼出口に
おける蒸気の運動エネルギーが圧力エネルギーに十分に
回復しないため、これも蒸気タービンの性能を低下させ
る一因となっているが、本蒸気タービンにおいてはこの
流れの損失を低減させ、また運動エネルギーを有効に回
復させることによって蒸気タービンの性能を向上させる
ために調速段動翼２のロータディスク３出口側端面４の
外周近傍に円筒状の剣先９を突設することによってロー
タディスク３出口側端面４に沿って半径方向に流れる蒸
気１０の方向をコントロールするようにしており、この
剣先９によってロータディスク３出口側端面４に沿って
半径方向へ流れる蒸気１０がほぼ９０°或いは９０°以
上方向転換されてロータ軸下流方向乃至はロータディス
ク３半径内側へ向けて流れることにより、蒸気１０の流
れの方向が調速段動翼２出口の蒸気７と略同一方向にな
って衝突による流れの損失が非常に小さくなる。また、
蒸気１０がこのような流れになることにより、調速段動
翼２の出口空間５においてロータディスク３半径方向へ
流れる蒸気による有効面積の減少が解消されて調速段動
翼２の出口空間５における有効面積が確保され、調速段
動翼２出口における蒸気７の運動エネルギーが次段動翼
の入口６までに有効な圧力に回復する。これらにより、
蒸気タービンの性能が向上する。In the conventional steam turbine, the rotor disk of the speed control blade has a normal disk shape, and a part of the steam on the outlet side of the speed control blade causes the rotor disk to rotate to cause the rotor disk to rotate. It flows in the radial direction along the end face on the outlet side. The steam flowing in the radial direction intersects with the steam at the exit of the speed control blades at a substantially right angle to cause a flow loss due to collision, which is one of the causes for lowering the performance of the steam turbine. In addition, since the effective area in the exit space of the speed-control blades is reduced by the steam flowing in the radial direction, the kinetic energy of the steam at the exit of the speed-control blades does not sufficiently recover to the pressure energy. However, in the present steam turbine, in order to improve the performance of the steam turbine by reducing the loss of this flow and effectively recovering the kinetic energy in this steam turbine, By projecting a cylindrical sword tip 9 in the vicinity of the outer periphery of the rotor disc 3 outlet side end surface 4, the direction of the steam 10 flowing in the radial direction along the rotor disc 3 outlet side end surface 4 is controlled. The steam 10 flowing in the radial direction along the outlet-side end surface 4 of the rotor disk 3 is redirected by about 9 ° or 90 ° or more to rotate the rotor 10. By flowing in the axial downstream direction or inward of the radius of the rotor disk 3, the flow direction of the steam 10 becomes substantially the same direction as the steam 7 at the exit of the speed control blade 2, and the flow loss due to collision is extremely small. Become. Also,
By the steam 10 having such a flow, the reduction of the effective area due to the steam flowing in the radial direction of the rotor disk 3 in the exit space 5 of the speed control blade 2 is eliminated and the exit space 5 of the speed control blade 2 is eliminated. , The kinetic energy of the steam 7 at the outlet of the speed control blade 2 is restored to an effective pressure by the inlet 6 of the next stage blade. By these,
The performance of the steam turbine is improved.

【０００９】[0009]

【発明の効果】本発明に係る蒸気タービンは前記のよう
に構成されており、ロータディスクの出口側端面に沿っ
て半径方向へ流れる蒸気が調速段動翼の出口の蒸気と衝
突しなくなって衝突による流れの損失を生じなくなると
ともに、調速段動翼の出口空間における有効面積が確保
されて調速段動翼の出口における蒸気の運動エネルギー
が圧力エネルギーに十分に回復するので、蒸気タービン
の性能が向上する。The steam turbine according to the present invention is constructed as described above, and the steam flowing in the radial direction along the end face on the outlet side of the rotor disk does not collide with the steam at the outlet of the speed control blade. The flow loss due to collision does not occur, the effective area in the exit space of the speed control blade is secured, and the kinetic energy of steam at the exit of the speed control blade is sufficiently restored to the pressure energy. Performance is improved.

【図面の簡単な説明】[Brief description of the drawings]

【図１】図１は本発明の一実施例に係る蒸気タービンの
調速段動翼の断面図である。FIG. 1 is a sectional view of a speed control blade of a steam turbine according to an embodiment of the present invention.

【図２】図２は従来の蒸気タービンの調速段動翼の断面
図である。FIG. 2 is a sectional view of a speed control blade of a conventional steam turbine.

【符号の説明】[Explanation of symbols]

１ ノズル ２ 調速段動翼 ３ ロータディスク ４ ロータディスクの出口側端面 ５ 調速段動翼の出口空間 ６ 次段動翼の入口 ７ 調速段動翼出口の蒸気 ９ 剣先 １０ ロータディスクの出口側端面に沿って半径方向
へ流れる蒸気1 Nozzle 2 Speed control blade 3 Rotor disk 4 End face of rotor disk 5 Exit space of speed control blade 6 Inlet of second speed blade 7 Steam at speed control blade outlet 9 Blade point 10 Exit of rotor disk Steam flowing radially along the side edge

Claims (1)

【特許請求の範囲】[Claims] 【請求項１】 調速段動翼が植込まれたロータディスク
の出口側端面の外周近傍に剣先状に突設され上記ロータ
ディスクの出口側端面に沿って半径方向へ流れる蒸気を
ロータ軸方向の下流乃至上記ロータディスクの半径方向
内側へ方向転換させる円筒部を備えたことを特徴とする
蒸気タービン。1. A steam disk which projects in the shape of a sword in the vicinity of the outer circumference of the outlet side end surface of a rotor disk in which speed control blades are implanted and flows in a radial direction along the outlet side end surface of the rotor disk. A steam turbine having a cylindrical portion for changing the direction from the downstream side to the radial inside of the rotor disk.
JP15909695A 1995-06-26 1995-06-26 Steam turbine Expired - Fee Related JP3499970B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP15909695A JP3499970B2 (en) 1995-06-26 1995-06-26 Steam turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP15909695A JP3499970B2 (en) 1995-06-26 1995-06-26 Steam turbine

Publications (2)

Publication Number Publication Date
JPH0913901A true JPH0913901A (en) 1997-01-14
JP3499970B2 JP3499970B2 (en) 2004-02-23

Family

ID=15686156

Family Applications (1)

Application Number Title Priority Date Filing Date
JP15909695A Expired - Fee Related JP3499970B2 (en) 1995-06-26 1995-06-26 Steam turbine

Country Status (1)

Country Link
JP (1) JP3499970B2 (en)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS557936A (en) * 1978-07-03 1980-01-21 Hitachi Ltd Stage structure of axial-flow turbine
JPH07145707A (en) * 1993-11-24 1995-06-06 Mitsubishi Heavy Ind Ltd Steam turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS557936A (en) * 1978-07-03 1980-01-21 Hitachi Ltd Stage structure of axial-flow turbine
JPH07145707A (en) * 1993-11-24 1995-06-06 Mitsubishi Heavy Ind Ltd Steam turbine

Also Published As

Publication number Publication date
JP3499970B2 (en) 2004-02-23

Similar Documents

Publication Publication Date Title
US5520508A (en) Compressor endwall treatment
JP3226543B2 (en) Turbine vane assembly with integrally cast cooling fluid nozzle
KR101464910B1 (en) Turbine
US6413045B1 (en) Turbine blades
JP2001065367A (en) Device and method for cooling rotary part in turbine
KR19990063333A (en) Method and apparatus for sealing a separation gap formed between the rotor and the stator in a non-contact manner
JP5592326B2 (en) Steam turbine stationary blade and steam turbine using the same
WO2004040099A1 (en) Steam valve
JPS6138103A (en) Step for steam turbine
JPS5982580A (en) Francis type hydraulic turbine impeller
GB2355768A (en) Turbine/compressor rotor with helical blade
JP2009036118A (en) Axial-flow exhaust gas turbine
JP4013356B2 (en) Water wheel
JPH0913901A (en) Steam turbine
JPH09317696A (en) Stator blade structure of axial flow compressor
US1748892A (en) Hydraulic process and apparatus
JP4184565B2 (en) Steam turbine nozzle and steam turbine using the steam turbine nozzle
JP3686233B2 (en) Axial flow turbine
CA3048394C (en) Power generation plant having a kaplan, bulb, diagonal flow or propeller turbine
JPH0450401Y2 (en)
JPH11173104A (en) Turbine rotor blade
JP2001355592A (en) Mixed flow pump of high specific speed
EP0984136A1 (en) Double-sided centrifugal-centripetral turbine
US20040052638A1 (en) Cover for lp first stage diaphragm and method for improving inflow to first stage diaphragm
JP2007138864A (en) Steam turbine stage and steam turbine

Legal Events

Date Code Title Description
A01 Written decision to grant a patent or to grant a registration (utility model)

Free format text: JAPANESE INTERMEDIATE CODE: A01

Effective date: 20031111

LAPS Cancellation because of no payment of annual fees