Feasibility Study for a Practical High Rotor Tip Clearance Turbine.

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Abstract:

Turbine tip clearance loss prediction methods were investigated analytically. Vector diagram variations, flow path wall curvature, and stator tangential lean and axial sweep affect the magnitude of this loss for given turbine design requirements and tip clearance. For a model core turbine, a potential 30 reduction in clearance loss relative to an equivalent free vortex turbine is predicted for a practical application of these variations. A follow-on investigation is proposed. Author

Author(s):
Evans, Dennis C. ; Prince, Timothy C.
Author Organization(s):
GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP
Descriptive Note:
Final rept. 30 Apr 71-29 Feb 72,
Pagination:
0049

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Contract/Grant Number(s):
N00019-71-C-0417
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
*GAS TURBINE BLADES), (*TURBINE BLADES, TOLERANCES(MECHANICS)), (*TURBOFAN ENGINES, GAS TURBINES, AXIAL FLOW TURBINES, AXIAL FLOW TURBINE ROTORS, AERODYNAMIC CONFIGURATIONS, LEAKAGE(FLUID), MEASUREMENT, TEST METHODS, PERFORMANCE(ENGINEERING), MATHEMATICAL PREDICTION, REDUCTION, PRESSURE, PREDICTIONS, NOZZLE GAS FLOW, COMBUSTION CHAMBER GASES, GAS FLOW
Field(s)/Group(s):
Fluid Mechanics, Jet and Gas Turbine Engines
Keyword(s):
CORE ENGINES, RANNIE METHOD, TF 39 ENGINES, TURBINE TIP CLEARANCE
Report Date:
1972 Feb 29