SU158752A1 - - Google Patents

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Publication number
SU158752A1
SU158752A1 SU807667A SU807667A SU158752A1 SU 158752 A1 SU158752 A1 SU 158752A1 SU 807667 A SU807667 A SU 807667A SU 807667 A SU807667 A SU 807667A SU 158752 A1 SU158752 A1 SU 158752A1
Authority
SU
USSR - Soviet Union
Prior art keywords
installation
turbine
temperature
compressor
gas
Prior art date
Application number
SU807667A
Other languages
English (en)
Russian (ru)
Publication of SU158752A1 publication Critical patent/SU158752A1/ru

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SU807667A SU158752A1 (https=)

Publications (1)

Publication Number Publication Date
SU158752A1 true SU158752A1 (https=)

Family

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4083181A (en) * 1976-06-14 1978-04-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Gas turbine engine with recirculating bleed
US6532745B1 (en) * 2002-04-10 2003-03-18 David L. Neary Partially-open gas turbine cycle providing high thermal efficiencies and ultra-low emissions

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4083181A (en) * 1976-06-14 1978-04-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Gas turbine engine with recirculating bleed
US6532745B1 (en) * 2002-04-10 2003-03-18 David L. Neary Partially-open gas turbine cycle providing high thermal efficiencies and ultra-low emissions

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