JPS61229903A - Axial turbo-machine - Google Patents

Axial turbo-machine

Info

Publication number
JPS61229903A
JPS61229903A JP7003285A JP7003285A JPS61229903A JP S61229903 A JPS61229903 A JP S61229903A JP 7003285 A JP7003285 A JP 7003285A JP 7003285 A JP7003285 A JP 7003285A JP S61229903 A JPS61229903 A JP S61229903A
Authority
JP
Japan
Prior art keywords
shelf
balance hole
disk
partition board
annular projection
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
Application number
JP7003285A
Other languages
Japanese (ja)
Inventor
Hisakuni Takenaga
竹永 久邦
Satoshi Yamazaki
敏 山崎
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 JP7003285A priority Critical patent/JPS61229903A/en
Publication of JPS61229903A publication Critical patent/JPS61229903A/en
Pending legal-status Critical Current

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  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE:To reduce the leakage loss by providing an annular projection shelf larger than the outer diameter of balance hole on the upstream face of disc while providing a radial fin on the facing partition board. CONSTITUTION:An annular projection shelf 10b larger than the outer diameter of the balance hole 5 is provided on the upstream face of rotor disc 4. While a radial seal fin 12 having key type cross-section and a micro gap against said shelf 2 is provided on a partition board 2 facing against said shelf 10b. Since the majority of leaked vapor from the partition board will flow to the balance hole 5, the leakage loss to be produced at the stage can be reduced.

Description

【発明の詳細な説明】 産業上の利用分野 本発明は、タービン段落のノズル出口ルート部において
、蒸気の漏逸損失を最小化することによって、タービン
性能向上を図る技術分野で利用される。
DETAILED DESCRIPTION OF THE INVENTION Field of Industrial Application The present invention is utilized in the technical field of improving turbine performance by minimizing leakage loss of steam at the nozzle exit route of a turbine stage.

従来の技術 第2図は、従来のタービン段落の、翼部分を示した断面
図で、第3図は第2図におけるm−m線矢視の断面を示
し、符号lはノズル、2は仕切板、3は動翼、4はディ
スク、5はバランスホール、6は仕切板ラビリンス、7
は回転軸、8aはディスク入口側空間、9はノズル出口
ルート部、10は邪魔板、11はルートシール部を示す
BACKGROUND ART FIG. 2 is a cross-sectional view of a blade portion of a conventional turbine stage, and FIG. 3 is a cross-sectional view taken along line mm in FIG. 2, where l is a nozzle and 2 is a partition. plate, 3 is a moving blade, 4 is a disk, 5 is a balance hole, 6 is a partition plate labyrinth, 7
8a is a rotating shaft, 8a is a disk inlet side space, 9 is a nozzle outlet root portion, 10 is a baffle plate, and 11 is a root seal portion.

回転軸7の外周にディスク4を介して動翼3を設け、デ
ィスク4の前方にディスク入口側空間8aを介して仕切
板2を設け、動翼3の前方;;ノズル出口ルート部9を
介してノズル1を設ける。
A rotor blade 3 is provided on the outer periphery of the rotary shaft 7 via a disk 4, and a partition plate 2 is provided in front of the disk 4 via a disk inlet side space 8a. A nozzle 1 is provided.

ディスク4(二対して直角に通常円周方向等間隔(:4
〜5個のバランスホール5を設ける。ディスク4の前方
、バランスホール5の外周側に環状の邪魔板10が取り
付けられている。
Discs 4 (normally spaced at equal intervals in the circumferential direction at right angles to the 2 disks (: 4
~5 balance holes 5 are provided. An annular baffle plate 10 is attached to the front of the disk 4 and to the outer peripheral side of the balance hole 5.

ノズル1前後の圧力差による仕切板ラビリンス6部分か
らの漏洩量は通常タービン段落流量の1〜2%に及ぶ。
The amount of leakage from the partition plate labyrinth 6 portion due to the pressure difference before and after the nozzle 1 normally amounts to 1 to 2% of the turbine stage flow rate.

その漏洩量がディスク4に設けられたバランスホール5
を完全:;通過するのが望ましいが、従来構造では、ロ
ータの熱伸び等によりルートシール部11のクリアラン
スが拡がり易く、全漏洩量の一部は、バランスホール5
を通過せず、ノズル出口ルート部9へ漏れ込んでいる。
The amount of leakage is determined by the balance hole 5 provided in the disk 4.
Although it is desirable that the leakage completely pass through the balance hole 5, in the conventional structure, the clearance of the root seal part 11 tends to expand due to thermal expansion of the rotor, etc., and a part of the total leakage amount is
It leaks into the nozzle exit route 9 without passing through.

この漏洩蒸気はタービン性能を大幅に低下させる原因と
なっている。
This leaked steam causes a significant reduction in turbine performance.

発明が解決しようとする問題点 本発明は、上記したようなタービン段落のノズル出口ル
ート部9においての、漏逸量を大幅に減少させ、漏逸損
失を最小限にすることにある。
Problems to be Solved by the Invention The present invention aims to significantly reduce the leakage amount and minimize the leakage loss in the nozzle outlet route section 9 of the turbine stage as described above.

問題点を解決するための手段 本発明は、上述の問題を解決するために、次のような手
段を採っている。すなわち、 ディスクの上流面にバランスホールの外周直径より大き
い環状突起の棚を設け、かつ、対向する仕切り板より前
記環状突起の棚に対して微小すき間を付与した断面形状
が鍵形のラジアルシールフィンを設ける。
Means for Solving the Problems The present invention takes the following measures in order to solve the above-mentioned problems. That is, the radial seal fin has a key-shaped cross-sectional shape in which a shelf of an annular projection larger than the outer diameter of the balance hole is provided on the upstream surface of the disk, and a minute gap is provided from the opposing partition plate to the shelf of the annular projection. will be established.

作用 仕切板ラビリンス6部分からの漏洩蒸気は、バランスホ
ールの入口部分で、ディスクの棚によって流れがせき止
められ、シールフィンのシール機能によって大部分がバ
ランスホール5へ流入し、ノズル出口ルート部の漏込流
れは微小になる。
The flow of steam leaking from the labyrinth 6 section of the working partition plate is stopped by the disc shelf at the entrance of the balance hole, and most of it flows into the balance hole 5 due to the sealing function of the seal fin, and the leakage at the nozzle exit route is stopped. The inflow becomes minute.

実施例 第1図に本発明の実施例を示し、説明する。図において
、符号が上記従来例と同じのものは同一部分を示す。
Embodiment An embodiment of the present invention is shown in FIG. 1 and will be explained. In the figures, the same reference numerals as in the conventional example above indicate the same parts.

ロータディスク4において、バランスホール5の外径側
、入口側に環状突起の棚10bを設ける。
In the rotor disk 4, a shelf 10b having an annular projection is provided on the outer diameter side and the entrance side of the balance hole 5.

この棚10bと仕切板2に設けられる断面形状が鍵形の
ラジアルシールフィン12によって、微小なすき間とな
り、漏れ面積が小さくなり、ノズル出口ルート部9への
漏洩量は極少となる。
The radial seal fins 12 having a key-shaped cross section provided on the shelf 10b and the partition plate 2 create a small gap, the leakage area becomes small, and the amount of leakage to the nozzle exit route 9 becomes extremely small.

上記棚10bとフィン12とのラジアルクリアランスは
ロータの遠心力および熱による伸びを考慮して選定され
る。
The radial clearance between the shelf 10b and the fins 12 is selected in consideration of centrifugal force of the rotor and elongation due to heat.

仕切板ラビリンス6部分からの漏洩蒸気はバランスホー
ル5の入口部分8でロータディスク4に設けた棚10b
によって流れがせき止められ、その動圧利用により、バ
ランスホール5の能力が増加し、ラジアルシールフィン
12のシール機能によって、大部分がバランスホール5
へ流入し、ノズル出口ルート部9の漏込流れが極めて小
さくなる。
Steam leaking from the labyrinth 6 part of the partition plate is removed from the shelf 10b provided on the rotor disk 4 at the entrance part 8 of the balance hole 5.
By using the dynamic pressure, the capacity of the balance hole 5 is increased, and due to the sealing function of the radial seal fin 12, most of the flow is
The leakage flow from the nozzle outlet route section 9 becomes extremely small.

発明の効果 本発明によれば、上記した如く、シール機能強化および
バランスホール能力増大とによって、仕切板からの漏洩
蒸気は、大部分バランスホールへ流れるので、従来段落
で発生していた漏逸損失は大幅に減少する。その結果、
タービン効率は向上する。
Effects of the Invention According to the present invention, as described above, by strengthening the sealing function and increasing the capacity of the balance hole, most of the steam leaking from the partition plate flows to the balance hole, thereby reducing the leakage loss that conventionally occurred in the paragraph. decreases significantly. the result,
Turbine efficiency increases.

【図面の簡単な説明】[Brief explanation of the drawing]

;   第1図は本発明の構成を示すタービン、段落の
翼部分の断面図、第2図は従来例の翼部分の構成を示す
断面図、第3図は第2図のm−m断面図である。 1・・ノズル、2・・仕切板、3・・動翼、4・・ディ
スク、5・・バランスホール、6・・仕切板ラビリンス
、7・・回転軸、8・・バランスホール入口部、9・・
ノズル出口ルート部、lOb・・棚、11・・ルートシ
ール部、12・・ラジアルシールフィン。 第1図 第2図 第3図 11r4矢j!図
; Fig. 1 is a cross-sectional view of a blade section of a turbine and a stage showing the configuration of the present invention, Fig. 2 is a cross-sectional view showing the configuration of a conventional blade section, and Fig. 3 is a cross-sectional view taken along line mm in Fig. 2. It is. 1. Nozzle, 2. Partition plate, 3. Moving blade, 4. Disk, 5. Balance hole, 6. Partition plate labyrinth, 7. Rotating shaft, 8. Balance hole entrance, 9・・・
Nozzle exit root section, lOb... Shelf, 11... Root seal section, 12... Radial seal fin. Figure 1 Figure 2 Figure 3 11r4 arrow j! figure

Claims (1)

【特許請求の範囲】[Claims] 回転軸に固設されるディスクに貫通されたバランスホー
ルを有する軸流ターボ機械であつて、前記ディスクの上
流面にバランスホールの外周直径より大きい環状突起の
棚を設け、かつ、対向する仕切板より前記環状突起の棚
に対して微小すき間を付与した断面形状が鍵形のラジア
ルシールフィンを設けた軸流ターボ機械。
An axial flow turbomachine having a balance hole penetrated through a disk fixed to a rotating shaft, wherein a shelf of an annular protrusion larger than the outer circumferential diameter of the balance hole is provided on the upstream surface of the disk, and opposing partition plates. An axial flow turbomachine provided with a radial seal fin having a key-shaped cross section and providing a minute gap with respect to the shelf of the annular projection.
JP7003285A 1985-04-04 1985-04-04 Axial turbo-machine Pending JPS61229903A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP7003285A JPS61229903A (en) 1985-04-04 1985-04-04 Axial turbo-machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP7003285A JPS61229903A (en) 1985-04-04 1985-04-04 Axial turbo-machine

Publications (1)

Publication Number Publication Date
JPS61229903A true JPS61229903A (en) 1986-10-14

Family

ID=13419845

Family Applications (1)

Application Number Title Priority Date Filing Date
JP7003285A Pending JPS61229903A (en) 1985-04-04 1985-04-04 Axial turbo-machine

Country Status (1)

Country Link
JP (1) JPS61229903A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013019285A (en) * 2011-07-08 2013-01-31 Toshiba Corp Steam turbine
JP2017172564A (en) * 2016-03-25 2017-09-28 三菱日立パワーシステムズ株式会社 Rotary machine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013019285A (en) * 2011-07-08 2013-01-31 Toshiba Corp Steam turbine
JP2017172564A (en) * 2016-03-25 2017-09-28 三菱日立パワーシステムズ株式会社 Rotary machine
WO2017163911A1 (en) * 2016-03-25 2017-09-28 三菱日立パワーシステムズ株式会社 Rotary machine
CN108779676A (en) * 2016-03-25 2018-11-09 三菱日立电力系统株式会社 Rotating machinery
US20190071991A1 (en) * 2016-03-25 2019-03-07 Mitsubishi Hitachi Power Systems, Ltd. Rotary machine
CN108779676B (en) * 2016-03-25 2020-10-13 三菱日立电力系统株式会社 Rotary machine
US11092026B2 (en) 2016-03-25 2021-08-17 Mitsubishi Power, Ltd. Rotary machine

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