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US 5,396,793 AGranted
Altitude gas turbine engine test cell
AssigneeUnited Technologies Corporation
InventorWilliam D. Colletti
Life of this patent
Estimating the term…
Abstract
The test cell has a pressure recovery pipe (26) receiving air from the tested engine (14). Excess air is inherently induced into the pipe. A source flow path for this excess air is provided from within the pipe (36) back to the entrance the pipe passing through a perforated bulkhead (30). High local velocities of the recirculating air, resulting variable static pressures on the engine and uncertainty in the thrust measurement are avoided.
Claims4
A test cell for thrust testing for a gas turbine engine at simulated altitude conditions, comprising:
- a wall or plurality of walls defining an airflow duct;
- a support for supporting a gas turbine engine within said airflow duct;
- means for guiding substantially all the inlet air into the gas turbine engine;
- a pressure recovery pipe coaxial with and downstream of the gas turbine engine;
- an exhaust compressor located to draw air from said pressure recovery pipe;
- and
- a perforated bulkhead between said pressure recovery pipe and said walls of said airflow duct, dividing said airflow duct into a low pressure chamber in direct communication with the inlet of said pressure recovery pipe, and a high pressure chamber in fluid communication with the interior of said pressure recovery pipe.
4 more elements
Dependencies are inferred from the claim text.