Biography. Widen Tabakoff Professor of Aerospace Engineering & Engineering Mechanics

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1 Biography Widen Tabakoff Professor of Aerospace Engineering & Engineering Mechanics Director, Erosion and Turbomachinery Performance Deterioration Laboratory Fellow of the AIAA, ASME and University of Cincinnati Degree PhD (Dr.Ing.), 1945, University of Berlin Contact 745 Baldwin Hall P.O. Box Cincinnati, OH Phone: (513) Fax: (513)

2 Clients Associated with the University of Cincinnati s Turbomachinery Erosion Laboratory General Electric Allison Rolls-Royce Siemens Westinghouse Pratt & Whitney Honeywell United Air Lines Lufthansa Sulzer Metco Ferguson Exxon Mobil Corning Sermatech PraxAir Surmet Chromalloy Ingersoll Rand Texaco Dupont US Navy Air US Air Force US Army US Department of Energy NASA Argonne National Laboratory

3 Highlights of Gas Turbine Erosion Research at the University of Cincinnati Theoretical Flow & particle dynamics modeling Blade surface erosion predictions Performance Loss Performance Retention Experimental Particle surface interactions Blade & seal material erosion Particle restitution characteristics (LDV) Coating life evaluation Turbomachinery performance loss Instantaneous Permanent (erosion)

4 Engine Performance Deterioration The particles may be from an environment such as volcanic ash, sand, and chemical substances such as particles formed by fuel combustion. The particles contained in the flow through the engine can be erosive or non-erosive. Both will affect turbomachinery performance during ingestion; however, the non-erosive particle influence will be temporary, whereas the erosive particle influence will produce permanent engine performance loss.

5 JT9D 9th Stage HPC Rotor Comparison

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7 Erosion Wind Tunnel The high temperature erosion tests were conducted in the UC erosion rig, which was designed to provide erosion data in the range of operating temperatures experienced in compressors and turbines. In addition to temperature, the facility properly simulates all the erosion parameters which were determined to have an impact on aerodynamics, including particle velocity, angle of impact, particle size, particle concentration, and sample size. Particle Rebound Wind Tunnel

8 Facilities Hot Erosion Wind Tunnel Cascade Erosion Tunnel Compressor Test Facility Turbine Test Facility

9 Schematic of Erosion Test Facility

10 Rebound Test Facility

11 Hot Erosion Wind Tunnel UC s high temperature erosion tunnel rig simulates particle surface interactions at operating conditions in compressors and turbines Temperatures (ambient 2000 o F) Impact velocities ( ft/sec) Impingement angles (0 o 90 o ) Particles and target materials (various) Particle loading (various)

12 UC s T-53 G Compressor Compressor rotor Compressor stator Multistage compressor UC s T-53 G Compressor

13 Schematic of Compressor Test Facility

14 Schematic of Turbine Test Facility

15 Schematic of specimen and holder

16 Test conditions Test Conditions: T=1300 F, V=1000ft/sec Particle: Arizona Test Dust (20 microns) Samples: (TiN) coating Sample ID Angle/Deg Wi/(g) Wf/(g) del W/(mg) Qp/(g) Erosion/(mg/g) 1TiN TiN TiN TiN TiN W i = initial weight (g) W = W W i f (mg) W f = sample weight after testing (g) Q p = particle weight impacting the tested sample (g)

17 The erosion rate (ε) was determined for each test sample from the following relation ε w = Erosion rate by weight = change in mass of sample = mass of impacting particles mg g 2 area ε v = Erosion rate by volume = change in volume = mass of impacting particles cm 3 g area 2

18 Erosion rate prediction Subtract the tested sample weight after erosion from the initial sample weight to obtain W = weight loss. To convert the weight loss W in volume loss V, divide W by the density ρ of the coating: V 3 or εv = = cm / g Qp Q p = total dose on the specimen impact. W εw = = mg / g Qp

19 Effect of impingement angle on erosion rate variation on M-246 substrate and RT22B coatings (T=815 o C, V p =366 m/s, Fly Ash particles)

20 Compressor cascade

21 Erosion weight loss for compressor blades.

22 Compressor rotor and graphs