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Research Papers

The Effect of Ultrapolish on a Transonic Axial Rotor

[+] Author and Article Information
William B. Roberts

Airfoil Technologies International and Flow Application Research,
Freemont, CA 94539
e-mail: bbclipper@hotmail.com

Scott A. Thorp

National Aeronautics and Space Administration,
Glenn Research Center,
Cleveland, OH 44135
e-mail: Scott.A.Thorp@nasa.gov

Patricia S. Prahst

AP Solutions,
Solon, OH 44135
e-mail: Patricia.S.Prahst@nasa.gov

Anthony J. Strazisar

National Aeronautics and Space Administration,
Glenn Research Center,
Cleveland, OH 44135
e-mail: Anthony.J.Strazisar@nasa.gov

Contributed by International Gas Turbine Institute (IGTI) of ASME for publication in JOURNAL OF TURBOMACHINERY. Manuscript received April 7, 2011; final manuscript received August 24, 2011 published online October 12, 2012. Editor: David Wisler.

J. Turbomach 135(1), 011001 (Oct 12, 2012) (6 pages) Paper No: TURBO-11-1060; doi: 10.1115/1.4006496 History: Received April 07, 2011; Revised August 24, 2011

Back-to-back testing was done using NASA fan rotor 67 in the Glenn Research Center W8 Axial Compressor Test Facility. The rotor was baseline tested with a normal industrial root-mean-square (RMS) surface finish of 0.5 μm to 0.6 μm (20 microinches to 24 microinches) at 60, 80, and 100% of design speed. At design speed the tip relative Mach number was 1.38. The blades were then removed from the facility and ultrapolished to a surface finish of 0.125 μm (5 microinch) or less and retested. At 100% speed near the design point, the ultrapolished blades showed approximately 0.3% to 0.5% increase in adiabatic efficiency. The difference was greater near maximum flow. Due to increased relative measurement error at 60 and 80% speed, the performance difference between the normal and ultrapolished blades was indeterminate at these speeds.

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References

Figures

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Fig. 1

Pressure rise characteristics of a transonic compressor rotor as a function of the extent of surface roughness, from Suder [1]

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Fig. 3

Schematic diagram of the NASA Glenn Axial Compressor Test Facility

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Fig. 4

Location of aerodynamic survey measurement stations

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Fig. 5

Pressure rise characteristics for baseline and ultrapolished surface finishes

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Fig. 6

Adiabatic efficiency characteristics for baseline and ultrapolished surface finishes

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Fig. 7

Impact of leading edge shape on the thrust-specific fuel consumption of a high by-pass ratio turbofan engine, from Roberts [6]. (a) Blade leading edge shape before and after enhanced refurbishment. (b) Comparison of thrust-specific fuel consumption before and after enhanced refurbishment.

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Fig. 8

Magnified photograph of rotor 67 leading edge before and after ultrapolishing

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Fig. 9

Measured blade leading edge profile before and after ultrapolishing

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Fig. 10

Comparison of predicted surface Mach number distribution at 70% span from the hub at design speed using blade geometry as measured before (baseline) and after ultrapolish

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Fig. 13

Approximate variation of adiabatic efficiency with surface finish for transonic rotors

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Fig. 12

Spanwise profile of adiabatic efficiency for ultrapolished blade at start of operation in atmospheric air and after 19 h of operation in atmospheric air at 100% speed

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Fig. 11

Spanwise profile of adiabatic efficiency for baseline and ultrapolished blade in dry air at 100% speed

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