NASA Glenn Research Facilities - Compressor Test Facilities

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	With over 60 test rigs, most aspects of engine development can be studied in the Engine Research Building (ERB).

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UEET Proof of Concept Compressor, W-7 bearing housing shaft, simulated rotor wire guide hardware

UEET W-7 2-Stage Proof of Concept Compressor - Blade Tip Clearance Sensor Calibration

The facilities listed below are located in the Engine Research Building (ERB). They provide fundamental and applied research to advance compressor and turbine component technology for aeronautical gas turbine engines.

W-1A - Low Speed Compressor Facility
W-7 - Multistage Compressor Facility
W-8 - Single-Stage Axial Compressor Facility
CE-18 - Small Engine Components Compressor Test Facility

The chart below shows the facility names across the top row and the various operating parameters along the left-hand column. For more information, please visit the ERB site pages.

	W-1A	W-7	W-8	CE-18
Inlet Air Pressure	Atmospheric	Atm to 20 psig	5-20 psia	Atm to 40 psig
Inet Air Temp.	Ambient	-30° - 100°F	Ambient	-20 to Ambient
Inlet Airflow (lb/s)	66/32	95	100 max	60 max
Atmos. Exhaust (psid)	.8 (blowers)	.8 (blowers)	.8 (blowers)	14.7
Altitude Exhaust (in. Hg)	20-26	26	26	20-26
Rotor Speed (r/min)	1920/1050	18,700	20,600 max	60,000 max
Rotor Size (in.)	60/48	20-22	22 max	8-20
Drive Motor (hp)	1,500	15,000	7,000 max	6,000




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	+ Freedom of Information Act + NASA Web Privacy Policy and Important Notices		Editor: Sharon Maier, SGT Inc. NASA Official: Linda C. Elonen-Wright + Web Curator + Contact NASA Glenn + Contact NASA Last Updated: December 12, 2011