JPS6195904U

JPS6195904U -

Info

Publication number: JPS6195904U
Application number: JP18074784U
Authority: JP
Priority date: 1984-11-30
Filing date: 1984-11-30
Publication date: 1986-06-20

Description

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

第１図は本考案の一実施例を示す断面図、第２
図はシヨンピーニング加工により疲労耐久限が向
上する様子を示す疲労限度線図、第３図は従来技
術による蒸気タービンの蒸気入口近傍を示す断面
図、第４図は軸方向からみた第３図の蒸気室の縦
断面図、第５図はロータの外周に動翼を配置した
状態を示す正面図、第６図は動翼とロータデイス
クの詳細説明図、第７図は動翼１枚に作用する蒸
気力を負荷に対して示した説明図、第８図は部分
負荷時に羽根が受ける蒸気力と蒸気力による羽根
の振動変化の関係を示す説明図、第９図は高圧初
段後の蒸気温度の負荷による変化を示す説明図、
第１０図は動翼の単位群にかかる蒸気力による羽
根曲げモーメントの分布を示す説明図である。２…第１段ノズル、３…動翼、３ｂ…ダブテイ
ル溝、４ａ…ロータデイスク、４ｂ，１８…タブ
テイル。 Fig. 1 is a sectional view showing one embodiment of the present invention;
The figure is a fatigue limit diagram showing how the fatigue durability limit is improved by shock peening, Figure 3 is a sectional view showing the vicinity of the steam inlet of a steam turbine according to the prior art, and Figure 4 is the same as Figure 3 seen from the axial direction. A vertical cross-sectional view of the steam chamber, Figure 5 is a front view showing the rotor blades arranged around the outer periphery of the rotor, Figure 6 is a detailed explanatory diagram of the rotor blades and rotor disk, and Figure 7 is the action on one rotor blade. Fig. 8 is an explanatory diagram showing the relationship between the steam force applied to the blades during partial load and the vibration change of the blades due to steam force, and Fig. 9 is the steam temperature after the high-pressure first stage. An explanatory diagram showing changes due to load,
FIG. 10 is an explanatory diagram showing the distribution of blade bending moment due to steam force applied to a unit group of rotor blades. 2... First stage nozzle, 3... Moving blade, 3b... Dovetail groove, 4a... Rotor disk, 4b, 18... Tab tail.

Claims

【実用新案登録請求の範囲】[Scope of utility model registration request]

適数の動翼をロータデイスクの外周部に密に連
ねて一体的に構成したものであつて、前記ロータ
デイスクは周方向に連なるダブテイル、前記動翼
はこのダブテイルに対抗するダブテイル溝をそれ
ぞれ備え、前記ダブテイル溝を前記ロータデイス
クのダブテイルに係合することにより、同ロータ
デイスクと同動翼とを一体にするようにしたもの
において、前記ロータデイスクのダブテイルに圧
縮加工を施し、ダブテイルの表層部に残留圧縮応
力を付与せしめたことを特徴とする動翼結合装置
。 An appropriate number of rotor blades are integrally formed by closely arranging them on the outer periphery of a rotor disk, the rotor disk having dovetails continuous in the circumferential direction, and the rotor blades having dovetail grooves opposing the dovetails. , wherein the rotor disk and the rotor blade are integrated by engaging the dovetail groove with the dovetail of the rotor disk, wherein the dovetail of the rotor disk is compressed, and the surface layer of the dovetail is compressed. A moving blade coupling device characterized in that a residual compressive stress is applied to a rotor blade.