Variable Inlet Vane Assembly for a Gas Turbine Combustor.

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Abstract:

This report describes a variable inlet vane assembly for use within the inlet area of a combustor, the vane assembly having a plurality of rotatable vanes situated within an annular-shaped opening in the inlet area of the combustor. Each vane is operated by the rotation of a crank assembly and actuator. The actuator meshes with the crank assembly through a sliding interface in order to accommodate axial andor radial growth of the combustor with no loss in the precision of the control of air entering the combustor during rotation of the vanes. Such an arrangement substantially enhances the relight capability of the combustor.Author

Author(s):
Marshall, Charles
Author Organization(s):
DEPARTMENT OF THE AIR FORCE WASHINGTON DC
Descriptive Note:
Patent Application,
Pagination:
0020

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Availability: This Government-owned Invention Available For U.s. Licensing And, Possibly, For Foreign Licensing. Copy Of Application Available Ntis.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
PAT-APPL-350 493
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*Patent applications, *Guide vanes, *Combustors, *Gas turbines, Inventions, Air flow, Engine components, Systems engineering, Ignition, Actuators, Assembly
Field(s)/Group(s):
Jet and Gas Turbine Engines
Keyword(s):
Relight capability
Report Date:
1982 Feb 19