SU238287A1 - - Google Patents
Info
- Publication number
- SU238287A1 SU238287A1 SU1118848A SU1118848A SU238287A1 SU 238287 A1 SU238287 A1 SU 238287A1 SU 1118848 A SU1118848 A SU 1118848A SU 1118848 A SU1118848 A SU 1118848A SU 238287 A1 SU238287 A1 SU 238287A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- ring
- blades
- fixed
- groove
- turbomachine
- Prior art date
Links
- 210000001699 lower leg Anatomy 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
Description
Стопорные кольца дл ограничени перемеш ,ени лопаток в сквозных пазах диска турбомашин , устан.овлетные в кольцевой каиаеке, вьгполиешюй в торцовых выступах лопаток, известны.Retaining rings for limiting the stirring, blades in the through-slots of the turbomachine disk, fixed in the annular canal, located in the end projections of the blades, are known.
Наличие специальных замков на кольце усложн ет конструкцию колеса турбомашины и технологию сборки.The presence of special locks on the ring complicates the design of the wheel of the turbomachine and the assembly technology.
Отличие предлагаемого устройства заключаетс в том, что лопатку фиксируют от сдвига в осевом направлении неразрезным пружинным кольцом, уста1новленным в кольцевой проточке на выступе хвостовика.The difference of the proposed device lies in the fact that the blade is fixed from shear in the axial direction by a continuous spring ring installed in an annular groove on the protrusion of the shank.
На чертеже схематически изображено описываемое стопорное кольцо.The drawing schematically depicts the locking ring described.
Рабочие лопатки /, закрепл ют в диске колеса 2 при помощи хвостоВИков 3, имеющих выступ с проточкой, в которой установлено неразрезное пружинное фиксируюш,ее кольцо 4. Кроме того, имеетс упор лопатки 5.The rotor blades (i) are fixed in the disk of the wheel 2 by means of tailings 3 having a protrusion with a groove in which a continuous spring is fixed, its ring 4. In addition, there is an emphasis of the blade 5.
Во врем сборки создаетс местный прогиб фиксирующего кольца 4 к центру (на чертеже показан пунктиром). Такое выполнение стопорного кольца позвол ет повысить надежность его в работе и упрощает технологию сборки.During assembly, a local deflection of the locking ring 4 towards the center is created (shown in dotted lines in the drawing). Such an embodiment of the locking ring allows to increase its reliability in operation and simplifies the assembly technology.
Предмет изобретени Subject invention
Стопорное кольцо дл ограничени пере мещени лопаток в сквозных пазах диска турбошашины , установленное в кольцевой канавке, выполненной IB торцавых выстл пах лопаток, отличающеес тем, что, с целью упрощени A retaining ring for limiting the movement of the blades in the through slots of the turbomachine disk, mounted in an annular groove made with IB end lining of the blades, characterized in that, in order to simplify
технологии сборки и повыщени надежности креплени лопаток, кольцо выполнено упругим неразрезпым с наружным диаметром, большим посадочного диа1метра канавки с тем, чтобы при местном прогибе кольца вводить егоthe technology of assembling and increasing the reliability of fastening the blades; the ring is made elastic, uncut, with an outer diameter, a large seating diameter of the groove, so that when the ring bends locally it is inserted
в канавку.into the groove.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU238287A1 true SU238287A1 (en) |
Family
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4895490A (en) * | 1988-11-28 | 1990-01-23 | The United States Of America As Represented By The Secretary Of The Air Force | Internal blade retention system for rotary engines |
| RU2507400C2 (en) * | 2008-12-11 | 2014-02-20 | Турбомека | Running wheel of turbine equipped with axial fixation device locking blades relative to disc |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4895490A (en) * | 1988-11-28 | 1990-01-23 | The United States Of America As Represented By The Secretary Of The Air Force | Internal blade retention system for rotary engines |
| RU2507400C2 (en) * | 2008-12-11 | 2014-02-20 | Турбомека | Running wheel of turbine equipped with axial fixation device locking blades relative to disc |
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