NASA - National Aeronautics and Space Administration
  Follow this link to skip to the main content + Contact NASA
Go

+ GRC Home
+ GRC Facilities Home
8'x6' Supersonic Wind Tunnel
8x6 Home
Quick Facts
Capabilities
Testing Information
Contact Information
Gallery
Layout diagram of the ERB CE-5B-2 Combustor Facility Test Stand
Facility Capabilities
Engine Research Building (ERB):
Combustor Facilities - CE-5B-2
Flametube Combustor Studies Test Facility

CE-5B-2 Facility Description
CE-5B-2 is one of the two test stands in the CE-5B facility and can be configured to study lean-premixed-prevaporized (LPP) and Lean-direct-injection (LDI) concepts for developing a low NOx combustor for high speed research and advanced subsonic applications. The non-windowed combustion flametube can use a three inch square cross-section or a three inch diameter round section and has six ports available for gas sampling probes. The windowed combustion flametube takes advantage of the flat walls on a three inch square cross-section to install optical windows for non-intrusive measurements. Tests are conducted with combustion air inlet pressure ranging from 10 to 15 atmospheres with preheater and exhaust conditions described for CE-5B-1.

CE-5B-2 Special Features
The same laser based non- intrusive diagnostics of reacting and non-reacting flowfields described for test position CE-5B-1 are available to this test section. A typical data acquisition system, is used for both test positions in CE-5B; in addition, most of the optical diagnostic instruments have their own data acquisition systems.

CE-5B Facility Capabilities
(typical of both rigs)
Paramter Operating Value
Inlet air supply pressure 450 psig
Inlet air temperature 100°F, preheated to 350-1350°F
Inlet airflow
   Stand 1
   Stand 2
20 lb/s (available)
0.5 to 12.0 pps
0.5 to 5.0 pps
Exhaust Atm or 20-26 in. Hg
Rig pressure without windows
   Stand 1
   Stand 2

275 psig
400 psig
Rig pressure with windows
   Stand 1
   Stand 2

250 psig
275 psig
Rig Fuel (JP-8) flow 7 gpm @ 400-900 psig
(three legs per stand)
Window cooling GN2 (4 legs) 0.125 to 0.5 pps (each leg)
Cooling water 150 gpm @ 460 psig
250 gpm @ 395 psig
50 gpm @ 350 psig
15 gpm @ 55 psig
Further Information
Engine Research Building
A large complex with 60 test rigs supporting engine research and development.
+ View the fact sheet (PDF)

Get Adobe Acrobat Reader
 








USA.gov - Your First Click to the US Government

+ Freedom of Information Act
+ NASA Web Privacy Policy and Important Notices

NASA - National Aeronautics and Space Administration
Editor: Sharon Maier, SGT Inc.
NASA Official: Susan Kevdzija
+ Web Curator
+ Contact NASA Glenn
+ Contact NASA
Last Updated: January 24, 2007