scholarly journals The Variation of Slat Noise with Mach and Reynolds Numbers

2011 ◽  
Author(s):  
David Lockard ◽  
Meelan Choudhari
Keyword(s):  
Reynolds Numbers ◽  
Slat Noise ◽  
Mach And Reynolds Numbers

The Application of Convective Cooling Enhancement of Span-Wise Cooling Holes in a Typical First Stage Turbine Blade

1991 ◽  
Author(s):  
D. J. Stankiewicz ◽  
T. R. Kirkham
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Enhancement ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Reynolds Numbers ◽  
Transfer Enhancement ◽  
Test Rig ◽  
Heated Oil ◽  
Cooling Enhancement ◽  
Mach And Reynolds Numbers

A technique of heat transfer enhancement is investigated whereby the internal span-wise cooling passages of a typical first stage gas turbine blade are modified by the introduction of circumferential ribs. The technique is verified by the use of a test rig incorporating a heated internally ribbed tube operating at the same range of Mach and Reynolds numbers as the turbine blade as well as by a test rig incorporating actual production blades immersed in a heated oil bath.

Influence of Mach and Reynolds numbers on heat transfer to the leeward surface of a half-cone at hypersonic speed

1977 ◽  
Vol 11 (5) ◽  
pp. 736-739 ◽  
Author(s):  
M. M. Ardasheva ◽  
V. Ya. Borovoi ◽  
P. I. Gorenbukh ◽  
M. V. Ryzhkova
Keyword(s):  
Heat Transfer ◽  
Reynolds Numbers ◽  
Hypersonic Speed ◽  
Half Cone ◽  
Mach And Reynolds Numbers

Combined influence of the mach and Reynolds numbers on transition in the boundary layer

1975 ◽  
Vol 9 (1) ◽  
pp. 126-129 ◽  
Author(s):  
V. G. Pridanov ◽  
A. M. Kharitonov ◽  
V. V. Chernykh
Keyword(s):  
Boundary Layer ◽  
Reynolds Numbers ◽  
Mach And Reynolds Numbers

Conversion of Centrifugal Compress Performance Curves Considering Non-Similar Flow Conditions

1982 ◽  
Author(s):  
W. Fister ◽  
J. Kotzur
Keyword(s):  
Energy Transfer ◽  
Centrifugal Compressor ◽  
Performance Testing ◽  
Reynolds Numbers ◽  
New Method ◽  
Flow Conditions ◽  
Flow Losses ◽  
Performance Curves ◽  
Thermodynamic Performance ◽  
Mach And Reynolds Numbers

Thermodynamic performance testing of centrifugal compressor cannot always be implemented at the same conditions on which the rating of the machine was based. To permit them to be compared to the rated values, the test values must therefore be converted to the respective suction data, gas properties and speeds. Conversion methods applied today which assume similar or approximately similar flow conditions for testing and rating, specify in various instance too narrow limits for this. A new conversion method based on few measurement values was developed to consider the influence exerted by the most important parameters, such as Mach and Reynolds numbers, etc. on energy transfer in the stage and on flow losses. Performance curves converted according to the new method, are compared to actually measured values.

Effects of Purge Jet Momentum on Sealing Effectiveness

2016 ◽  
Author(s):  
Kenneth Clark ◽  
Michael Barringer ◽  
Karen Thole ◽  
Carey Clum ◽  
Paul Hiester ◽  
...  
Keyword(s):  
Flow Rate ◽  
Momentum Flux ◽  
Reynolds Numbers ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Swirl Velocity ◽  
Purge Flow ◽  
Secondary Air ◽  
Flow Tracer ◽  
Mach And Reynolds Numbers

Driven by the need for higher cycle efficiencies, overall pressure ratios for gas turbine engines continue to be pushed higher thereby resulting in increasing gas temperatures. Secondary air, bled from the compressor, is used to cool turbine components and seal the cavities between stages from the hot main gas path. This paper compares a range of purge flows and two different purge hole configurations for introducing the purge flow into the rim cavities. In addition, the mate face gap leakage between vanes is investigated. For this particular study, stationary vanes at engine relevant Mach and Reynolds numbers were used with a static rim seal and rim cavity to remove rotational effects and isolate gas path effects. Sealing effectiveness measurements, deduced from the use of CO2 as a flow tracer, indicate that the effectiveness levels on the stator and rotor side of the cavity depend on the mass and momentum flux ratios of the purge jets relative to the swirl velocity. For a given purge flow rate, fewer purge holes resulted in better sealing than the case with a larger number of holes.

scholarly journals Thermal effects influencing measurements in a supersonic blowdown wind tunnel

2016 ◽  
Vol 20 (6) ◽  
pp. 2101-2112 ◽  
Author(s):  
Djordje Vukovic ◽  
Dijana Damljanovic
Keyword(s):  
Wind Tunnel ◽  
Thermal Effects ◽  
Temperature Drop ◽  
Reynolds Numbers ◽  
Force Balance ◽  
Wind Tunnels ◽  
Large Temperature ◽  
Long Run ◽  
Short Run ◽  
Mach And Reynolds Numbers

During a supersonic run of a blowdown wind tunnel, temperature of air in the test section drops which can affect planned measurements. Adverse thermal effects include variations of the Mach and Reynolds numbers, variation of airspeed, condensation of moisture on the model, change of characteristics of the instrumentation in the model, et cetera. Available data on thermal effects on instrumentation are pertaining primarily to long-run-duration wind tunnel facilities. In order to characterize such influences on instrumentation in the models, in short-run-duration blowdown wind tunnels, temperature measurements were made in the wing-panel-balance and main-balance spaces of two wind tunnel models tested in the T-38 wind tunnel. The measurements showed that model-interior temperature in a run increased at the beginning of the run, followed by a slower drop and, at the end of the run, by a large temperature drop. Panel-force balance was affected much more than the main balance. Ways of reducing the unwelcome thermal effects by instrumentation design and test planning are discussed.

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