JP3442933B2 - Heat recovery type gas turbine - Google Patents
Heat recovery type gas turbineInfo
- Publication number
- JP3442933B2 JP3442933B2 JP20193596A JP20193596A JP3442933B2 JP 3442933 B2 JP3442933 B2 JP 3442933B2 JP 20193596 A JP20193596 A JP 20193596A JP 20193596 A JP20193596 A JP 20193596A JP 3442933 B2 JP3442933 B2 JP 3442933B2
- Authority
- JP
- Japan
- Prior art keywords
- cooling
- rotor
- air
- steam
- blade
- 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.)
- Expired - Fee Related
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【０００１】[0001]
【発明の属する技術分野】本発明は蒸気冷却動翼と空気
冷却動翼を有するガスタービンロータに関する。TECHNICAL FIELD The present invention relates to a gas turbine rotor having a steam cooling blade and an air cooling blade.
【０００２】[0002]
【従来の技術】ガスタービンの熱効率向上のためにガス
タービン動翼を蒸気で冷却することが考えられている。
このような形式のものでは、タービン動翼に蒸気を供給
し、冷却を終えた蒸気を回収する通路を有する新たなロ
ータが必要とされる。2. Description of the Related Art In order to improve the thermal efficiency of a gas turbine, cooling a gas turbine moving blade with steam has been considered.
In such a type, a new rotor having a passage for supplying steam to the turbine blades and recovering the steam after cooling is required.
【０００３】その場合、冷却蒸気はコンバインドサイク
ルの蒸気タービンの抽気などが使用されるが蒸気側のサ
イクル上、洩れは極力制限される。In this case, as the cooling steam, bleed air from a steam turbine of a combined cycle is used, but leakage is limited as much as possible on the steam side cycle.
【０００４】図２は従来考えられている蒸気冷却動翼を
有するガスタービンのタービン部の断面図である。FIG. 2 is a sectional view of a turbine portion of a gas turbine having a steam cooling rotor blade which has been conventionally considered.
【０００５】同図２に示すように、冷却蒸気は、最終段
側のロータ３１方向から、ロータのスピンドルボルト３
２の隙間のある孔３３を通って供給され、第１段動翼前
室３４に流入する。そしてロータ３５，動翼３６を通っ
てそれ等を冷却した後，同じ形状の第２段ロータ３７，
第２段動翼３８の順に蒸気を通して冷却し，最終段ロー
タ３１の冷却蒸気孔３９から回収される。As shown in FIG. 2, the cooling steam is supplied to the rotor spindle bolt 3 from the direction of the rotor 31 on the final stage side.
It is supplied through the hole 33 having two gaps and flows into the first-stage rotor blade front chamber 34. After cooling them through the rotor 35 and the rotor blades 36, the second stage rotor 37 of the same shape,
The second stage moving blades 38 are sequentially cooled by passing through the steam, and are recovered from the cooling steam holes 39 of the final stage rotor 31.
【０００６】[0006]
【発明が解決しようとする課題】蒸気冷却動翼の冷却蒸
気の供給及び回収は前述のようなルートをとって行なわ
れるが、効率、出力等の効果を勘案すれば、後方段（図
示の例は第３段動翼を示す）においては、僅かの空気で
冷却することが可能である。The supply and recovery of the cooling steam of the steam cooling blade is performed by the above-mentioned route, but considering the effects of efficiency, output, etc., the rear stage (the example shown in the figure). Indicates a third stage rotor blade), and it is possible to cool with a small amount of air.
【０００７】しかし、図２に示す形式のものでは、冷却
蒸気の供給・回収通路が複雑なため、一部の動翼のみを
空気冷却しようとしてもロータ側に冷却空気通路を設け
る術がなく、冷却空気を確保することは困難であった。However, in the case of the type shown in FIG. 2, since the cooling steam supply / recovery passage is complicated, there is no way to provide a cooling air passage on the rotor side even if only some of the moving blades are cooled with air. It was difficult to secure cooling air.
【０００８】本発明はこのような点に鑑みてなされたも
ので、蒸気冷却と空気冷却を併せ備えた形式のものを提
供することを課題とするものである。The present invention has been made in view of the above circumstances, and an object thereof is to provide a type having both steam cooling and air cooling.
【０００９】[0009]
【課題を解決するための手段】本発明は前記課題を解決
するべくなされたもので、蒸気冷却動翼と空気冷却動翼
とを有するガスタービンのロータにおいて、前方段の動
翼は蒸気冷却動翼とし、冷却蒸気が前記ロータ内の孔を
通って前記蒸気冷却動翼内に供給され蒸気冷却を行なっ
て前記ロータ内の他の孔から回収されるように構成さ
れ、後方段の動翼は空気冷却動翼とし、冷却空気が前記
空気冷却動翼の前の静翼の外側シュラウド、同静翼内、
同静翼の内側シュラウドを経て前記空気冷却動翼内に供
給されるように構成されてなることを特徴とする熱回収
式ガスタービンを提供する。SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and a steam cooling blade and an air cooling blade are provided.
A rotor of a gas turbine with bets, the blades of the front stage and steam cooling the rotor blade, the cooling steam holes in the rotor
It is supplied to the inside of the steam cooling blade to cool the steam.
Configured to be recovered from other holes in the rotor.
The blades in the rear stage are air cooling blades , and the cooling air is
The outer shroud of the stator vane in front of the air-cooled rotor, inside the stator vane,
Through the inner shroud of the stator vane, it is fed into the air cooling blade.
Heat recovery characterized by being configured to be supplied
A gas turbine is provided .
【００１０】すなわち、効率、出力等への影響の大きい
前方段の動翼は蒸気冷却動翼とし、その影響の小さい後
方段の動翼は空気冷却動翼としたものであって、不必要
に構造が複雑になるのを避け、よりシンプルな構造で以
て蒸気，空気による両方の冷却を可能とし、空気冷却動
翼とした後方段動翼への冷却空気の供給は、同空気冷却
動翼の前に配置された静翼の外側シュラウド，静翼本体
内，静翼の内側シュラウドと経て冷却空気を導き、前記
後方段の空気冷却動翼へと供給するようにして、全体構
造のシンプル化，コンパクト化を可能にしたものであ
る。 That is, it has a great influence on efficiency, output, etc.
The blades in the front stage should be steam-cooled blades and
The lower stage blades are air cooling blades and are unnecessary
Avoid a complicated structure, and use a simpler structure.
To allow steam, cooling both by air Te, air cooled moving
The supply of cooling air to the rear stage blade was a wing, the air cooling
It arranged vane outer shroud before moving blade, stationary blade Body
Among direct the cooling air through the inner shroud of the stationary blade, so as to supply to the air cooling moving blade of the rear stage, the entire structure
It is possible to make the structure simple and compact .
【００１１】また、本発明は、前記冷却空気を通す静翼
は、同静翼からロータを経て空気冷却動翼に至る流路を
形成し、同静翼からロータへの冷却空気連絡部は前記空
気冷却動翼の被冷却部及び冷却空気出口孔よりもロータ
半径方向内側に位置された熱回収式ガスタービンを提供
し、冷却空気は静翼からロータを経て空気冷却動翼に至
るように供給され、その際、静翼からロータへの冷却空
気連絡位置を、後方の空気冷却動翼の被冷却部及び同被
冷却部からの冷却空気の出口位置よりロータの半径方向
で内側位置にすることによりこの両位置間の圧力差を利
用して冷却空気を確実に流通させるようにしたものであ
る。Further, according to the present invention, the stationary blades for passing the cooling air form a flow path from the stationary blades to the air cooling moving blades via the rotor, and the cooling air connecting portion from the stationary blades to the rotor is Sky
Provide a heat recovery type gas turbine located inside the cooled portion of the air cooling blade and the cooling air outlet hole in the radial direction of the rotor, and supply cooling air from the stationary blade through the rotor to the air cooling blade. At that time, the position where the cooling air is communicated from the vanes to the rotor is located radially inward of the rotor from the cooled portion of the rear air cooling blade and the outlet of the cooling air from the cooled portion. Thus, the cooling air is surely circulated by utilizing the pressure difference between the two positions.
【００１２】[0012]
【発明の実施の形態】本発明の実施の一形態を図１に基
づいて説明する。BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the present invention will be described with reference to FIG.
【００１３】１は最終段側のロータ，２はスピンドルボ
ルト，３は第１段動翼前室、４は第１段側のロータ，５
は第１段動翼，６は第２段ロータ，７は第２段動翼，８
は冷却蒸気孔，９は車室，１０は第３段の動翼でいわゆ
る空気冷却動翼，１１は前記最終段の動翼１０の前に配
置された静翼，１２は静翼１１の外側シュラウド，１３
は同様に内側シュラウド，１４は内側シュラウド下部，
１５はシールフィン，１６は第３段ロータ１７の外周に
周方向で複数個設けた孔である。1 is the rotor on the final stage side, 2 is the spindle bolt, 3 is the front chamber of the first stage moving blade, 4 is the rotor on the first stage side, 5
Is the first stage rotor blade, 6 is the second stage rotor blade, 7 is the second stage rotor blade, 8
Is a cooling steam hole, 9 is a cabin, 10 is a so-called air-cooling moving blade of a third stage moving blade, 11 is a stationary blade arranged in front of the moving blade 10 at the last stage, and 12 is an outer side of the stationary blade 11. Shroud, 13
Is also the inner shroud, 14 is the lower part of the inner shroud,
Reference numeral 15 is a seal fin, and 16 is a hole provided in the outer circumference of the third stage rotor 17 in a circumferential direction.
【００１４】このような構成を有する本実施の形態にお
いて、冷却蒸気は最終段側ロータ１方向からロータのス
ピンドルボルト２の隙間のある孔を通って供給され第１
段動翼前室３に流入する。In the present embodiment having such a configuration, the cooling steam is supplied from the direction of the rotor 1 on the final stage side through a hole having a gap in the spindle bolt 2 of the rotor.
It flows into the stage blade front chamber 3.
【００１５】そしてロータ４，動翼５を通ってそれ等を
冷却した後、同型の第２段ロータ６，第２段動翼７と順
に蒸気冷却し、最終段ロータ１の冷却蒸気孔８から回収
される。After passing through the rotor 4 and the rotor blades 5 to cool them, the second stage rotor 6 and the second stage rotor blades 7 of the same type are sequentially cooled by steam, and the cooling steam holes 8 of the final stage rotor 1 are used. Be recovered.
【００１６】一方冷却空気は、ガスタービン圧縮機（図
示されていない）から抽気された抽気空気が車室９内に
導入され空気冷却する動翼１０の前の静翼１１の外側シ
ュラウド１２、同静翼１１内，内側シュラウド１３，内
側シュラウド下部１４の孔を通ってシールフィン部１５
に至る。On the other hand, as the cooling air, the extracted air extracted from a gas turbine compressor (not shown) is introduced into the vehicle compartment 9 to cool the air. The seal fin portion 15 passes through the holes in the vane 11, the inner shroud 13, and the lower portion 14 of the inner shroud.
Leading to.
【００１７】そしてシールフィン部１５に放出された冷
却空気は、ロータ１７の外周の複数孔１６からロータ１
７及び動翼１０内に流入するが、前記シールフィン部１
５に放出された冷却空気は、抽気圧力の絶対値の大きさ
とロータ入口孔とロータ出口孔の両孔の高さ位置の違い
ΔＨによるポンプアクション作用とによってロータ孔か
ら吸引され動翼１０内に確実に流入し、最終的にガス本
流に放出される。The cooling air discharged to the seal fin portion 15 is supplied from the plurality of holes 16 on the outer periphery of the rotor 17 to the rotor 1.
7 and the rotor blade 10 flow into the seal fin portion 1
The cooling air discharged to 5 is sucked from the rotor hole by the magnitude of the absolute value of the extraction pressure and the pump action action due to the difference ΔH in the height positions of the rotor inlet hole and the rotor outlet hole into the rotor blade 10. It surely flows in and is finally discharged into the main gas stream.
【００１８】本実施の形態ではこのようにして空気冷却
が蒸気冷却構造部に干渉することなく巧みに組み込まれ
て空気冷却を可能とすることができたものである。In this embodiment, as described above, the air cooling can be skillfully incorporated without interfering with the steam cooling structure to enable the air cooling.
【００１９】以上、本発明を図示の実施の形態について
説明したが、本発明はかかる実施の形態に限定されず、
本発明の範囲内でその具体的構造に種々の変更を加えて
よいことはいうまでもない。Although the present invention has been described above with reference to the illustrated embodiments, the present invention is not limited to such embodiments.
It goes without saying that various modifications may be made to the specific structure within the scope of the present invention.
【００２０】[0020]
【発明の効果】以上、本願請求項１の発明の熱回収式ガ
スタービンロータによれば効率、出力等を向上させるた
めに採用する蒸気冷却ガスタービンにおいて、効率、出
力等への影響の大きい前方段の動翼は蒸気冷却動翼と
し、その影響の小さい後方段の動翼は空気冷却動翼と
し、不必要に構造が複雑になるのを避け、よりシンプル
な構造で以て蒸気，空気による両方の冷却を可能にする
ことができた。Effect of the Invention] According to the heat recovery type gas turbine rotor of the invention of this gun according to claim 1 efficiency in the steam cooling gas turbine employed to improve the output and the like, efficiency, output
The blades in the front stage, which have a large effect on force, are
However, the moving blades in the rear stage, which are less affected, are
And, it avoids unnecessary structure is complicated, and Te than in a more simple structure steam can enable both cooling by air.
【００２１】また、冷却空気の取り入れを、空気冷却動
翼の前にある静翼の外側シュラウド、同静翼内、同静翼
の内側シュラウドを経て行うように特定したことによ
り、全体構造のシンプル化，コンパクト化は確実とな
り、実現性の極めて高いものとすることができたもので
ある。[0021] In addition, the intake of cold却空care, the outer shroud of the stationary blade in front of the air cold 却動 <br/> wing, the static in the wings, Doseitsubasa
Since it was specified to be performed via the inner shroud of the above, the simplification and compactness of the entire structure were ensured, and the feasibility was extremely high.
【００２２】また、請求項２の発明によれば、静翼，ロ
ータ，そして目的の空気冷却動翼へと至る冷却空気は，
静翼からロータへの移行位置と、空気冷却動翼への移行
位置との圧力差により、冷却空気の移動は確実，かつ正
確となり、所期の冷却機能を達成し得たものである。According to the second aspect of the present invention, the cooling air reaching the stationary blade, the rotor, and the target air cooling moving blade is
Due to the pressure difference between the transition position from the stationary blade to the rotor and the transition position to the air-cooling moving blade, the movement of the cooling air becomes reliable and accurate, and the desired cooling function can be achieved.
【図１】本発明の実施の一形態に係る蒸気─空気冷却タ
ービンの断面図。FIG. 1 is a cross-sectional view of a steam-air cooling turbine according to an embodiment of the present invention.
【図２】従来、考えられていた蒸気冷却タービンの断面
図。FIG. 2 is a cross-sectional view of a conventionally considered steam cooling turbine.
１ 最終段側ロータ ２ スピンドルボルト ３ 第１段動翼前室 ４ ロータ ５ 第１段動翼 ６ 第２段ロータ ７ 第２段動翼 ８ 冷却蒸気孔 ９ 車室 １０ 空気冷却動翼 １１ 静翼 １２ 外側シュラウド １３ 内側シュラウド １４ 外側シュラウド下部 １５ シールフィン １６ 孔 １７ 第３段ロータ 1 Final stage rotor 2 spindle bolt 3 First stage rotor blade front chamber 4 rotor 5 First stage rotor blades 6 Second stage rotor 7 Second stage rotor blade 8 Cooling steam holes 9 car compartment 10 Air cooling blades 11 static wings 12 Outer shroud 13 Inner shroud 14 Lower outer shroud 15 Seal fin 16 holes 17 Third stage rotor
フロントページの続き (56)参考文献 特開 昭53−64113（ＪＰ，Ａ) 特開 昭50−119115（ＪＰ，Ａ) 特開 平９−13902（ＪＰ，Ａ) 特開 平７−301127（ＪＰ，Ａ) 特開 平３−96628（ＪＰ，Ａ) 特開 昭57−176309（ＪＰ，Ａ) (58)調査した分野(Int.Cl.7，ＤＢ名) F01D 1/00 - 11/10 F02C 1/00 - 9/58 F23R 3/00 - 7/00 Continuation of the front page (56) Reference JP-A-53-64113 (JP, A) JP-A-50-119115 (JP, A) JP-A-9-13902 (JP, A) JP-A-7-301127 (JP , A) JP-A-3-96628 (JP, A) JP-A-57-176309 (JP, A) (58) Fields investigated (Int.Cl. 7 , DB name) F01D 1 / 00-11 / 10 F02C 1/00-9/58 F23R 3/00-7/00
Claims (2)
ガスタービンのロータにおいて、前方段の動翼は蒸気冷
却動翼とし、冷却蒸気が前記ロータ内の孔を通って前記
蒸気冷却動翼内に供給され蒸気冷却を行なって前記ロー
タ内の他の孔から回収されるように構成され、後方段の
動翼は空気冷却動翼とし、冷却空気が前記空気冷却動翼
の前の静翼の外側シュラウド、同静翼内、同静翼の内側
シュラウドを経て前記空気冷却動翼内に供給されるよう
に構成されてなることを特徴とする熱回収式ガスタービ
ン。1. A rotor of a gas turbine having steam cooling blades and air cooling blades, wherein the blades at the front stage are steam cooling blades , and the cooling steam passes through holes in the rotor.
The steam is supplied into the steam cooling blade to cool it
The cooling blade is configured to be recovered from other holes in the rotor , and the rear stage moving blade is an air cooling moving blade , and the cooling air is
Shroud in front of the vane, inside the vane, inside the vane
So that it can be fed into the air cooling blades through the shroud
Heat recovery type gas turbine, characterized by comprising configured.
ロータを経て空気冷却動翼に至る流路を形成し、同静翼
からロータへの冷却空気連絡部は前記空気冷却動翼の被
冷却部及び冷却空気出口孔よりもロータ半径方向内側に
位置させたことを特徴とする請求項１に記載の熱回収式
ガスタービン。 2. The stationary vane for passing the cooling air is from the stationary vane.
A flow path is formed from the rotor to the air-cooled moving blade,
The cooling air connection from the rotor to the rotor is covered by the air cooling blade.
Inside the cooling section and cooling air outlet hole in the rotor radial direction
Heat recovery type gas turbine according to claim 1, characterized in that was positioned.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP20193596A JP3442933B2 (en) | 1996-07-31 | 1996-07-31 | Heat recovery type gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP20193596A JP3442933B2 (en) | 1996-07-31 | 1996-07-31 | Heat recovery type gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH1047006A JPH1047006A (en) | 1998-02-17 |
| JP3442933B2 true JP3442933B2 (en) | 2003-09-02 |
Family
ID=16449233
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP20193596A Expired - Fee Related JP3442933B2 (en) | 1996-07-31 | 1996-07-31 | Heat recovery type gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3442933B2 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20000071653A (en) * | 1999-04-15 | 2000-11-25 | 제이 엘. 차스킨, 버나드 스나이더, 아더엠. 킹 | Cooling supply system for stage 3 bucket of a gas turbine |
| JP3361501B2 (en) | 2000-03-02 | 2003-01-07 | 株式会社日立製作所 | Closed-circuit blade cooling turbine |
| EP1452688A1 (en) * | 2003-02-05 | 2004-09-01 | Siemens Aktiengesellschaft | Steam turbine rotor, method and use of actively cooling such a rotor |
| JP5865798B2 (en) * | 2012-07-20 | 2016-02-17 | 株式会社東芝 | Turbine sealing device and thermal power generation system |
-
1996
- 1996-07-31 JP JP20193596A patent/JP3442933B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH1047006A (en) | 1998-02-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6416284B1 (en) | Turbine blade for gas turbine engine and method of cooling same | |
| JP4130321B2 (en) | Gas turbine engine components | |
| US6402471B1 (en) | Turbine blade for gas turbine engine and method of cooling same | |
| JP5166830B2 (en) | Intermediate cooling turbine engine | |
| JP4492951B2 (en) | Triple circuit turbine cooling | |
| JP3761572B2 (en) | Airfoil dual source cooling | |
| JP4958737B2 (en) | Combined turbine cooling engine | |
| US5215435A (en) | Angled cooling air bypass slots in honeycomb seals | |
| JP4733876B2 (en) | Cooling turbine airfoils offset in clockwise direction | |
| JP6661702B2 (en) | Airfoil with tip rail cooling | |
| JP2000145403A (en) | Turbine nozzle with purge air circuit | |
| US6174133B1 (en) | Coolable airfoil | |
| US20240011399A1 (en) | Blade with tip rail cooling | |
| EP2055895A2 (en) | Turbomachine rotor disk | |
| JP2001207862A (en) | Method and device for purging turbine wheel cavity | |
| US10815806B2 (en) | Engine component with insert | |
| JP2000310127A (en) | Coolant supply system for third stage bucket for gas turbine | |
| JP2012077749A (en) | Apparatus and method for cooling platform region of turbine rotor blade | |
| US6261054B1 (en) | Coolable airfoil assembly | |
| WO1997025522A1 (en) | Stationary blade for gas turbine | |
| US20040076511A1 (en) | Gas turbine | |
| JP2017110652A (en) | Active high pressure compressor clearance control | |
| US7246989B2 (en) | Shroud leading edge cooling | |
| JP3442933B2 (en) | Heat recovery type gas turbine | |
| EP0933517A1 (en) | Heat recovery type gas 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: 20030527 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090620 Year of fee payment: 6 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100620 Year of fee payment: 7 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100620 Year of fee payment: 7 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110620 Year of fee payment: 8 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110620 Year of fee payment: 8 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120620 Year of fee payment: 9 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130620 Year of fee payment: 10 |
|
| S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313111 |
|
| R360 | Written notification for declining of transfer of rights |
Free format text: JAPANESE INTERMEDIATE CODE: R360 |
|
| R370 | Written measure of declining of transfer procedure |
Free format text: JAPANESE INTERMEDIATE CODE: R370 |
|
| S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313111 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| LAPS | Cancellation because of no payment of annual fees |