NDLI: Cf6 jet engine diagnostics program. high pressure turbine roundness/clearance investigation

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Cf6 jet engine diagnostics program. high pressure turbine roundness/clearance investigation

Content Provider	NASA Technical Reports Server (NTRS)
Author	Fasching, W. A. Howard, W. D.
Copyright Year	1982
Description	The effects of high pressure turbine clearance changes on engine and module performance was evaluated in addition to the measurement of CF6-50C high pressure turbine Stage 1 tip clearance and stator out-of-roundness during steady-state and transient operation. The results indicated a good correlation of the analytical model of round engine clearance response with measured data. The stator out-of-roundness measurements verified that the analytical technique for predicting the distortion effects of mechanical loads is accurate, whereas the technique for calculating the effects of certain circumferential thermal gradients requires some modifications. A potential for improvement in roundness was established in the order of 0.38 mm (0.015 in.), equivalent to 0.86 percent turbine efficiency which translates to a cruise SFC improvement of 0.36 percent. The HP turbine Stage 1 tip clearance performance derivative was established as 0.44 mm (17 mils) per percent of turbine efficiency at take-off power, somewhat smaller, therefore, more sensitive than predicted from previous investigations.
File Size	5244693
Page Count	123
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19830004830
Archival Resource Key	ark:/13960/t2z36nc80
Language	English
Publisher Date	1982-06-01
Access Restriction	Open
Subject Keyword	Aircraft Propulsion And Power Temperature Distribution Blade Tips Performance Tests Turbine Blades Shrouds Stators Fuel Consumption Turbofan Engines Clearances Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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