The Application of Pressure- and Temperature-Sensitive Paints to an Advanced Compressor

2000 ◽  
Vol 123 (4) ◽  
pp. 823-829 ◽  
Author(s):  
Kelly R. Navarra ◽  
Douglas C. Rabe ◽  
Sergey D. Fonov ◽  
Larry P. Goss ◽  
Chunill Hah
Keyword(s):  
Wind Tunnel ◽  
Molecular Spectroscopy ◽  
State Of The Art ◽  
Temperature Sensitive ◽  
Pressure Sensitive Paint ◽  
Suction Surface ◽  
Transonic Compressor ◽  
Pressure Sensitive ◽  
Oxygen Sensitive ◽  
Design Speed

An innovative pressure-measurement technique that employs the tools of molecular spectroscopy has been widely investigated by the aerospace community. Measurements are made via oxygen-sensitive molecules attached to the surface of interest as a coating, or paint. The pressure-sensitive-paint (PSP) technique is now commonly used in stationary wind-tunnel tests; this paper presents the use of this technique in advanced turbomachinery applications. New pressure- and temperature-sensitive paints (P/TSPs) have been developed for application to a state-of-the-art transonic compressor where pressures up to 1.4 atm and surface temperatures to 90°C are expected for the suction surface of the first-stage rotor. PSP and TSP data images have been acquired from the suction surface of the first-stage rotor at 85 percent of the corrected design speed for the compressor near-stall condition. A comparison of experimental results with CFD calculations is discussed.

The Application of Pressure- and Temperature-Sensitive Paints to an Advanced Compressor

2000 ◽  
Author(s):  
Kelly R. Navarra ◽  
Douglas C. Rabe ◽  
Larry P. Goss
Keyword(s):  
Pressure Transducer ◽  
Molecular Spectroscopy ◽  
State Of The Art ◽  
Temperature Sensitive ◽  
Pressure Sensitive Paint ◽  
Suction Surface ◽  
Transonic Compressor ◽  
Pressure Sensitive ◽  
Oxygen Sensitive ◽  
Design Speed

An innovative pressure-measurement technique that employs the tools of molecular spectroscopy has been widely investigated by the aerospace community. Measurements are made via oxygen-sensitive molecules attached to the surface of interest as a coating, or paint. The pressure-sensitive-paint (PSP) technique is now commonly used in stationary wind-tunnel tests; this paper presents the use of this technique in advanced turbomachinery applications. New pressure- and temperature-sensitive paints (P/TSPs) have been developed for application to a state-of-the-art transonic compressor where pressures up to 1.4 atm and surface temperatures to 90°C are expected for the suction surface of the first-stage rotor. PSP and TSP data images have been acquired from the suction surface of the first-stage rotor at 85% of the corrected design speed for the compressor near-stall condition. A comparison to over-the-rotor pressure transducer measurements will be presented.

Pressure-Sensitive Paint Investigation for Turbomachinery Application

1995 ◽  
Author(s):  
K. Sabroske ◽  
D. Rabe ◽  
C. Williams
Keyword(s):  
Surface Pressure ◽  
Rotor Blade ◽  
Ccd Camera ◽  
Pressure Sensitive Paint ◽  
Blade Surface ◽  
Pressure Data ◽  
Operational Environment ◽  
Suction Surface ◽  
Transonic Compressor ◽  
Pressure Sensitive

Two preliminary tests are discussed which investigate the feasibility of using pressure-sensitive paint (PSP) technology to acquire blade surface pressures in turbomachinery. The first test determined the prospect of using PSP in an operational environment. In this test, PSP was applied to a first stage rotor blade of a state-of-the-art transonic compressor. The paint survived the normal operating temperature, pressure, and centrifugal forces present in this compressor at rotational speeds up to 13,000 RPM. The second test investigated techniques to acquire blade surface pressure data. Suction surface intensity measurements were acquired from a low speed, high-aspect ratio compressor using a back illuminated charge coupled device (CCD) camera while the compressor was rotating at 1500 RPM. An optical derotating mechanism was used to hold the rotor blade image stationary while acquiring PSP data. Both experiments demonstrate that PSP is a viable technique to acquire blade surface pressure data in full scale compressor testing. Special considerations required in applying PSP techniques to turbomachinery are also reported.

Development of a Lifetime Pressure Sensitive Paint Procedure for High-Pressure Vane Testing

2021 ◽  
Author(s):  
Papa Aye N. Aye-Addo ◽  
Guillermo Paniagua ◽  
David G. Cuadrado ◽  
Lakshya Bhatnagar ◽  
Antonio Castillo Sauca ◽  
...  
Keyword(s):  
High Pressure ◽  
Test Section ◽  
Static Pressure ◽  
Pressure Field ◽  
Optical Measurements ◽  
Wall Region ◽  
Pressure Amplitude ◽  
Pressure Sensitive Paint ◽  
Suction Surface ◽  
Pressure Sensitive

Abstract Optical measurements based on fast response Pressure Sensitive Paint (PSP) provide enhanced spatial resolution of the pressure field. This paper presents laser lifetime PSP at 20 kHz, with precise calibrations, and results from a demonstration in an annular vane cascade. The laser lifetime PSP methodology is first evaluated in a linear wind tunnel with a converging-diverging nozzle followed by a wavy surface. This test section is fully optically accessible with maximum modularity. A data reduction procedure is proposed for the PSP calibration, and optimal pixel binning is selected to reduce the uncertainty. In the annular test section, laser lifetime PSP was used to measure the time-averaged static pressure field on a section of the suction surface of a high-pressure turbine vane. Tests were performed at engine representative conditions in the Purdue Big Rig for Annular Stationary Turbine Analysis module at the Purdue Experimental Turbine Aerothermal Lab. The 2-D pressure results showed a gradual increase of pressure in the spanwise and flow directions, corroborated with local static pressure taps and computational results. The variation in PSP thickness was measured as a contribution to the uncertainty. The discrete Fourier transform of the unsteady pressure signal showed increased frequency content in wind-on conditions compared to wind-off conditions at the mid-span and 30% span. Compared to the mid-span region, the hub end wall region had an increase in frequencies and pressure amplitude. This result was anticipated given the expected presence of secondary flow structures in the near hub region.

Unsteady Wake and Coolant Density Effects on Turbine Blade Film Cooling Using Pressure Sensitive Paint Technique

2012 ◽  
Vol 134 (8) ◽  
Author(s):  
Akhilesh P. Rallabandi ◽  
Shiou-Jiuan Li ◽  
Je-Chin Han
Keyword(s):  
Film Cooling ◽  
Density Ratio ◽  
Suction Side ◽  
Pressure Sensitive Paint ◽  
Suction Surface ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Pressure Sensitive ◽  
Unsteady Wake ◽  
Film Cooling Holes

The effect of an unsteady stator wake (simulated by wake rods mounted on a spoke-wheel wake generator) on the modeled rotor blade is studied using the pressure sensitive paint (PSP) mass-transfer analogy method. Emphasis of the current study is on the midspan region of the blade. The flow is in the low Mach number (incompressible) regime. The suction (convex) side has simple angled cylindrical film-cooling holes; the pressure (concave) side has compound angled cylindrical film-cooling holes. The blade also has radial shower-head leading edge film-cooling holes. Strouhal numbers studied range from 0 to 0.36; the exit Reynolds number based on the axial chord is 530,000. Blowing ratios range from 0.5 to 2.0 on the suction side and 0.5 to 4.0 on the pressure side. Density ratios studied range from 1.0 to 2.5, to simulate actual engine conditions. The convex suction surface experiences film-cooling jet lift-off at higher blowing ratios, resulting in low effectiveness values. The film coolant is found to reattach downstream on the concave pressure surface, increasing effectiveness at higher blowing ratios. Results show deterioration in film-cooling effectiveness due to increased local turbulence caused by the unsteady wake, especially on the suction side. Results also show a monotonic increase in film-cooling effectiveness on increasing the coolant to mainstream density ratio.

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