RU1401952C - Blade of gas turbine - Google Patents

Blade of gas turbine Download PDF

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Publication number
RU1401952C
RU1401952C SU4121547A RU1401952C RU 1401952 C RU1401952 C RU 1401952C SU 4121547 A SU4121547 A SU 4121547A RU 1401952 C RU1401952 C RU 1401952C
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RU
Russia
Prior art keywords
plug
gas turbine
blade
boss
pin
Prior art date
Application number
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Russian (ru)
Inventor
И.А. Черняев
Original Assignee
Акционерное общество "Авиадвигатель"
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Application filed by Акционерное общество "Авиадвигатель" filed Critical Акционерное общество "Авиадвигатель"
Priority to SU4121547 priority Critical patent/RU1401952C/en
Application granted granted Critical
Publication of RU1401952C publication Critical patent/RU1401952C/en

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Abstract

FIELD: aircraft engine engineering. SUBSTANCE: plug 4 is secured in boss 2 of a fin by threaded connection 5 and provided with cylindric pin 6 from the outer side. The pin has flat 7 and forms clearance 9 with wall 8 of a technological opening. This provides reliable fixing of plug 4 in the technological opening when air is issued from blade. EFFECT: enhanced reliability. 3 dwg

Description

Изобретение относится к транспортному машиностроению и может быть использовано в газовых турбинах авиационных двигателей. The invention relates to transport engineering and can be used in gas turbines of aircraft engines.

Цель изобретения - повышение надежности путем обеспечения надежной фиксации заглушки в технологическом отверстии. The purpose of the invention is to increase reliability by ensuring reliable fixation of the plugs in the technological hole.

На фиг. 1 показаны лопатки газовой турбины; на фиг. 2 - узел I на фиг. 1; на фиг. 3 - вид А на фиг. 2. In FIG. 1 shows gas turbine blades; in FIG. 2 - node I in FIG. 1; in FIG. 3 is a view A in FIG. 2.

Лопатка газовой турбины содержит полое перо 1, снабженное на периферии внутренней торцовой бобышкой 2 с отверстием 3, и расположенную в нем заглушку 4. Заглушка 4 закреплена в бобышке 2 при помощи резьбового соединения 5 и снабжена с внешней стороны цилиндрическим штырем 6, имеющим по крайней мере одну лыску 7 и образующим со стенкой 8 отверстия 3, кольцевой зазор 9, заполненный припоем. The gas turbine blade contains a hollow feather 1, provided on the periphery with an internal end boss 2 with an opening 3, and a plug 4 located therein. The plug 4 is fixed in the boss 2 by means of a threaded connection 5 and provided with an external cylindrical pin 6 having at least one flange 7 and forming with the wall 8 of the hole 3, an annular gap 9, filled with solder.

При работе турбины охлаждающий воздух поступает в перо 1, охлаждает его и выбрасывается из лопатки. При этом заглушка 4 надежно закрывает технологическое отверстие 3. (56) Скубачевский Г. С. Авиационные газотурбинные двигатели. М. : Машиностроение, 1981, с. 132. During the operation of the turbine, cooling air enters feather 1, cools it and is thrown out of the blade. In this case, the plug 4 reliably closes the technological hole 3. (56) G. Skubachevsky. Aviation gas turbine engines. M.: Mechanical Engineering, 1981, p. 132.

Claims (1)

ЛОПАТКА ГАЗОВОЙ ТУРБИНЫ, содержащая полое перо, снабженное на периферии внутренней торцовой бобышкой с отверстием, и расположенную в нем заглушку, отличающаяся тем, что, с целью повышения надежности, заглушка закреплена в бобышке при помощи резьбового соединения и снабжена с внешней стороны цилиндрическим штырем, имеющим по крайней мере одну лыску и образующим со стенкой отверстия кольцевой зазор, заполненный припоем. GAS TURBINE SHOULDER, containing a hollow feather, provided on the periphery with an internal end boss with a hole, and a plug located therein, characterized in that, in order to increase reliability, the plug is secured to the boss by means of a threaded connection and provided on the outside with a cylindrical pin having at least one flange and forming with the hole wall an annular gap filled with solder.
SU4121547 1986-09-19 1986-09-19 Blade of gas turbine RU1401952C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU4121547 RU1401952C (en) 1986-09-19 1986-09-19 Blade of gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU4121547 RU1401952C (en) 1986-09-19 1986-09-19 Blade of gas turbine

Publications (1)

Publication Number Publication Date
RU1401952C true RU1401952C (en) 1994-05-15

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Family Applications (1)

Application Number Title Priority Date Filing Date
SU4121547 RU1401952C (en) 1986-09-19 1986-09-19 Blade of gas turbine

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RU (1) RU1401952C (en)

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