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High-temperature combustor liner tests in structural component response test facility
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Moorhead, Paul E. |
| Copyright Year | 1988 |
| Description | Jet engine combustor liners were tested in the structural component response facility at NASA Lewis. In this facility combustor liners were thermally cycled to simulate a flight envelope of takeoff, cruise, and return to idle. Temperatures were measured with both thermocouples and an infrared thermal imaging system. A conventional stacked-ring louvered combustor liner developed a crack at 1603 cycles. This test was discontinued after 1728 cycles because of distortion of the liner. A segmented or float wall combustor liner tested at the same heat flux showed no significant change after 1600 cycles. Changes are being made in the facility to allow higher temperatures. |
| File Size | 7542003 |
| Page Count | 9 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880012999 |
| Archival Resource Key | ark:/13960/t11p3076f |
| Language | English |
| Publisher Date | 1988-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Cracks Test Facilities Cyclic Loads Linings Structural Design Criteria Engine Tests Combustion Chambers Thermal Stresses Jet Engines Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
