SINGLE-SHAFT LOW-POWER GAS-TURBINE ENGINE (ODNOVALNYI GAZOTURBINNYI DVIGATEL MALOI MOSHCHNOSTI),

reportActive / Technical Report | Accession Number: AD0678429 | Need Help?

Abstract:

The report introduces a low-power gas turbine engine incorporating a centrifugal compressor and a mixed-flow turbine. The turbines output shaft is connected perpendicularly to the engine shaft through a reducing gear located between the turbine and the compressor. This arrangement reduces the overall dimensions of the engine and provides for an axial air inlet into compressor. The reducer is composed of a pair of spur gears and a pair of conical gears. A one-way clutch and a starter are mounted co-axially with the shaft of the engine. Author

Author(s):
Svetlakov, Ch. L. ; Klisanich, N. P. ; Kartashov, V. G.
Author Organization(s):
FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OHIO
Supplementary Note:
Edited trans. of Patent (USSR) 165 039 2p, 3 May 63, by E. Harter.
Annotation:
Single-shaft low-power gas-turbine engine--Translation.
Pagination:
0005

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
FTD-HT-1010-67
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
(*GAS TURBINES, PATENTS), AXIAL FLOW COMPRESSORS, MIXED FLOW COMPRESSORS, REDUCTION GEARS, ENGINE AIR SYSTEMS COMPONENTS, POWER, DRIVE SHAFTS, USSR
Field(s)/Group(s):
Jet and Gas Turbine Engines
Keyword(s):
TRANSLATIONS
Report Date:
1967 Nov 21