BiographyWiden TabakoffProfessor of Aerospace Engineering
& Engineering Mechanics
Director, Erosion and Turbomachinery Performance Deterioration Laboratory
Fellow of the AIAA, ASME and University of Cincinnati
DegreePhD (Dr.Ing.), 1945, University of Berlin
Contact745 Baldwin HallP.O. Box 210070Cincinnati, OH 45221-0070Phone: (513) 556-3226Fax: (513) 556-5038Email: [email protected]
Clients Associated with the University of Cincinnati’s Turbomachinery Erosion Laboratory
General ElectricAllison Rolls-RoyceSiemens WestinghousePratt & WhitneyHoneywellUnited Air LinesLufthansaSulzer MetcoFergusonExxon MobilCorningSermatechPraxAir
SurmetChromalloyIngersoll RandTexacoDupontUS Navy AirUS Air ForceUS ArmyUS Department of EnergyNASAArgonne National Laboratory
Highlights of Gas Turbine Erosion Research at the University of Cincinnati
TheoreticalFlow & 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)
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.
JT9D 9th Stage HPC Rotor Comparison
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
Facilities
Hot Erosion Wind Tunnel
Cascade Erosion TunnelCompressor Test Facility
Turbine Test Facility
Schematic of Erosion Test Facility
Rebound Test Facility
Hot Erosion Wind Tunnel
UC’s high temperature erosion tunnel rig simulates particle surface interactions at operating conditions in compressors and turbines
– Temperatures (ambient – 2000oF)
– Impact velocities (60-1800 ft/sec)
– Impingement angles (0o – 90o)
– Particles and target materials (various)
– Particle loading (various)
UC’s T-53 G Compressor
Compressor rotor Compressor stator
Multistage compressor
UC’s T-53 G Compressor
Schematic of Compressor Test Facility
Schematic of Turbine Test Facility
Schematic of specimen and holder
Sample ID Angle/Deg Wi/(g) Wf/(g) del W/(mg) Qp/(g) Erosion/(mg/g)
1 TiN 15 4.8353 4.8351 0.0002 10 0.02
2 TiN 30 4.814 4.814 0.0004 10 0.04
3 TiN 45 5.037 5.0364 0.0006 10 0.06
4 TiN 60 4.4569 4.4554 0.0014 10 0.14
5 TiN 90 4.8489 4.8469 0.002 10 0.2
Wi = initial weight (g) ∆W = Wi – Wf (mg) 0.000
Wf = sample weight after testing (g) Qp = particle weight impacting the tested sample (g)
Test conditionsTest Conditions: T=1300 F, V=1000ft/sec
Particle: Arizona Test Dust (20 microns)Samples: (TiN) coating
The erosion rate (ε) was determined for each test sample from the following relation
εw = Erosion rate by weight = change in mass of sample =
mass of impacting particles
εv = Erosion rate by volume = change in volume =
mass of impacting particles
2areagmg
2
3
areagcm
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: or
Qp = total dose on the specimen impact.
gcmQ
V
pv /3=∆=ε gmg
Q
W
pw /=∆=ε
Effect of impingement angle on erosion rate variation on M-246 substrate and RT22B coatings (T=815oC, Vp=366 m/s, Fly Ash particles)
Compressor cascade
Erosion weight loss for compressor blades.
Compressor rotor and graphs
