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Performance and Operational Studies of a Full-Scale Jet-Engine Thrust Reverser

Description: Note presenting an axial-flow turbojet engine equipped with a hemispherical target thrust reverser that was pylon-mounted beneath the wing of a cargo airplane. Results regarding the performance of full-depth hemisphere, operational problems, and performance of modified hemisphere are provided.
Date: April 1956
Creator: Kohl, Robert C.
Partner: UNT Libraries Government Documents Department

Investigation of a full-scale, cascade-type thrust reverser

Description: A double set of turning vanes was carried inside the jet tailpipe. To produce reverse thrust, the tailpipe opens into two side sections and the turning vanes move outward to form a V-shaped cascade, which deflects the exhaust-gas flow. Forward and reverse net thrust were measured over a range of engine speeds with the airplane stationary. Taxi tests were made to determine the comparative stopping distances using wheel braking and reverse thrust separately, and a combination of both. The effect of turning-vane spacing on thrust-reverser performance was determined by scale-model tests using unheated air.
Date: April 1957
Creator: Kohl, Robert C. & Algranti, Joseph S.
Partner: UNT Libraries Government Documents Department

Effect of Various Methods of Boundary-Layer Control on Performance of V-1710-93 Engine-Stage Supercharger

Description: "Four methods of boundary-layer control were tried during an investigation to improve the flow in the impeller passages of a V-1710-93 engine-stage supercharger. The boundary layer along the impeller front shroud was removed by suction. In one method the removal was accomplished by recirculation of the air to the impeller inlet; in another method, by external removal. In the other methods, slots were cut through the impeller-blade faces first at 30 percent and then at 30 and 70 percent of the mean-flow-path length measured from leading edges of the rotating inlet guide vanes to introduce air from the high-pressure side of the blades into the region where stagnation and separation were suspected" (p. 1).
Date: January 1947
Creator: Kohl, Robert C. & Diggs, Donald R.
Partner: UNT Libraries Government Documents Department

Performance of 19XB-2A Gas Turbine 1 - Effect of Pressure Ratio and Inlet Pressure on Turbine Performance for an Inlet Temperature of 800 Degrees R

Description: "An investigation of the 19XB-2A gas turbine is being conducted at the Cleveland laboratory to determine the effect on turbine performance of various inlet pressures, inlet temperatures, pressure ratios, and wheel speeds. The engine of which this turbine is a component is designed to operate at an air flow of 30 pounds per second at a compressor rotor speed of 17,000 rpm at sea-level conditions. At these conditions the total-pressure ratio is 2.08 across the turbine and the turbine inlet total temperature is 2000 degrees R" (p. 1).
Date: December 26, 1946
Creator: Kohl, Robert C. & Larkin, Robert G.
Partner: UNT Libraries Government Documents Department

Free-flight performance of a rocket-boosted, air-launched 16-inch-diameter ram-jet engine at Mach numbers up to 2.20

Description: From Summary: "The investigation of air-launched ram-jet engines has been extended to include a study of models with a nominal design free-stream Mach number of 2.40. These models require auxiliary thrust in order to attain a flight speed at which the ram jet becomes self-accelerating. A rocket-boosting technique for providing this auxiliary thrust is described and time histories of two rocket-boosted ram-jet flights are presented. In one flight, the model attained a maximum Mach number of 2.20 before a fuel system failure resulted in the destruction of the engine. Performance data for this model are presented in terms of thrust and drag coefficients, diffuser pressure recovery, mass-flow ratio, combustion efficiency, specific fuel consumption, and over-all engine efficiency."
Date: February 3, 1953
Creator: Disher, John H.; Kohl, Robert C. & Jones, Merle L.
Partner: UNT Libraries Government Documents Department

Effects of Partial Admission on Performance of a Gas Turbine

Description: Report presenting an investigation of the effect of partial admission of the driving fluid on the performance of a representative full-admission, production-type gas turbine. Results regarding losses, full-admission performance, partial-admission performance, partial admission as a means of power control, and a comparison of partial admission with other methods of power control are provided.
Date: February 1949
Creator: Kohl, Robert C.; Herzig, Howard Z. & Whitney, Warren J.
Partner: UNT Libraries Government Documents Department