RU1313055C

RU1313055C - Turbomachine composite blade

Info

Publication number: RU1313055C
Application number: SU843689094A
Authority: RU
Inventors: Ю.Е. Слюсарев; Ю.В. Вигант; С.В. Николаевский; Ю.В. Тельнов
Original assignee: Запорожское машиностроительное конструкторское бюро "Прогресс"
Priority date: 1984-01-09
Filing date: 1984-01-09
Publication date: 1995-12-10

Abstract

FIELD: manufacture of gas turbines. SUBSTANCE: fin reinforcing layers 3 are located by their ends at fin center line at varying distance relative to each other. Reinforcing layers have varying areas in sections which reduce in direction from back 7 and trough of the fin to center line in the amount from 50 to 20 percent of total area of reinforcing layers. Screened cover plate is provided on trailing portion of fin over entire side. Transverse slots in metal cover plate 5 are inclined relative to fin longitudinal axis and distance between their axes is equal to length of slots. In case of impact of foreign matter against blade fin, reinforcing layers smoothly distribute forces and ensure smooth dampening cutting off stage by stage the amplitude of waves generated at impact. EFFECT: enhanced reliability. 2 cl, 3 dwg

Description

Изобретение относится к области газотурбостроения. The invention relates to the field of gas turbine construction.

Целью изобретения является повышение надежности в работе. The aim of the invention is to increase reliability.

На фиг.1 изображена композиционная лопатка турбомашины; на фиг.2 сечение по А-А на фиг.1; на фиг.3 узел Б на фиг.2 в увеличенном масштабе. Figure 1 shows a composite blade of a turbomachine; figure 2 section along aa in figure 1; in Fig.3 node B in Fig.2 on an enlarged scale.

Композиционная лопатка турбомашины содержит перо 1, выполненное из чередующихся и ориентированных вдоль его профиля графитных 2 и армирующих 3 слоев и поперечных волокон 4, соединенных между собой связующим материалом (не показан), и металлическую накладку 5 с поперечными прорезями 6, расположенную на входной части пера 1. При этом армирующие слои 3 размещены концами у средней линии пера 1, расположены друг от друга на переменном расстоянии и в поперечных сечениях имеют переменную площадь, уменьшающуюся в направлении от спинки 7 и корыта 8 пера и средней линии от 50 до 20% от общей площади армирующих слоев 3. Прорези 6 накладки 5 наклонены к продольной оси пера 1 а расстояние l между их осями равно длине l₁ прорезей 9, расположенных на его выходной части по всей высоте.The composite blade of the turbomachine contains a feather 1 made of alternating and oriented along its profile graphite 2 and reinforcing 3 layers and transverse fibers 4 interconnected by a binder material (not shown), and a metal plate 5 with transverse slots 6 located on the input part of the pen 1. In this case, the reinforcing layers 3 are placed at the ends of the midline of the pen 1, are spaced from each other at a variable distance, and in cross sections have a variable area that decreases in the direction from the back 7 and the trough 8 of the pen and the middle line from 50 to 20% of the total area of the reinforcing layers 3. The slots 6 of the lining 5 are inclined to the longitudinal axis of the pen 1 and the distance l between their axes is equal to the length l _{1 of the} slots 9 located at its output part along the entire height.

При ударе о перо 1 лопатки посторонних предметов армирующие слои 3 равномерно распределяют усилия не только вдоль пера 1 лопатки, но и вдоль ее хорды и обеспечивают плавное демпфирование, поэтапно срезая амплитуду генерируемых при ударе волн. Усилия на сдвиг в слоях после удара распределяют поперечные волокна 4, разгружая графитовые слои 2. Эластичным материалом в поперечных прорезях 6 защитной накладки 5 у входной части снижаются усилия на сдвиг за счет демпфирования. Кроме того, при демпфировании пера 1 лопатки после удара концы частей накладки 5 у передней кромки между прорезями 6, работая по типу ножниц, срезают часть эластичного материала, тем самым уменьшая усилия на сдвиг. When the blade 1 of a foreign object hits the feather 1, the reinforcing layers 3 evenly distribute the forces not only along the blade feather 1, but also along its chord and provide smooth damping, gradually cutting off the amplitude of the waves generated during the impact. The shear forces in the layers after impact distribute the transverse fibers 4, unloading the graphite layers 2. The shear forces due to damping are reduced by elastic material in the transverse slots 6 of the protective strip 5 at the inlet part. In addition, when damping the pen 1 of the blade after impact, the ends of the lining 5 at the leading edge between the slots 6, working as scissors, cut off part of the elastic material, thereby reducing shear forces.

Claims

1. COMPOSITION TURBO MACHINE SHOULDER containing a pen made of alternating and reinforcing layers of graphite and reinforcing layers and transverse fibers interconnected by a bonding material, and a metal plate with transverse slots located on the inlet of the pen, characterized in that, with In order to increase reliability in work, the reinforcing layers are placed at the ends of the midline of the pen, are spaced from each other at a variable distance, and in cross sections have a variable area that decreases in n board from the back of the pen and the trough to the center line of from 50 to 20% of the total area of the reinforcing layers and the slits are inclined to the longitudinal laths pen axis, and the distance between their axes is equal to the length of the slits.

2. The blade according to claim 1, characterized in that the feather is equipped with a secate plate, located on its output part along the entire height.