SU238287A1 - - Google Patents

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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
Application number
SU1118848A
Other languages
English (en)
Russian (ru)
Publication of SU238287A1 publication Critical patent/SU238287A1/ru

Links

SU1118848A SU238287A1 (enrdf_load_stackoverflow)

Publications (1)

Publication Number Publication Date
SU238287A1 true SU238287A1 (enrdf_load_stackoverflow)

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Cited By (2)

* Cited by examiner, † Cited by third party
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 (ru) * 2008-12-11 2014-02-20 Турбомека Рабочее колесо турбины, снабженное устройством аксиальной фиксации, стопорящим лопатки относительно диска

Cited By (2)

* Cited by examiner, † Cited by third party
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 (ru) * 2008-12-11 2014-02-20 Турбомека Рабочее колесо турбины, снабженное устройством аксиальной фиксации, стопорящим лопатки относительно диска

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