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Cooling Characteristics of a Transpiration-Cooled Afterburner With a Porous Wall of Brazed and Rolled Wire Cloth

Description: Memorandum presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratio of cooling air to combustion gas, and pressure altitudes. Maximum wall temperatures based on the cooling correlation were determined for a porous wall of uniform permeability at sea-level takeoff and for several flight Mach numbers. Results regarding typical data, cooling correlation, transpirati… more
Date: August 19, 1954
Creator: Koffel, William K.
Item Type: Refine your search to only Report
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Cooling characteristics of a transpiration-cooled afterburner with a porous wall of brazed and rolled wire cloth

Description: Report presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratios of cooling air to combustion gas, and pressure altitudes. Results regarding typical data, cooling correlation, transpiration-cooling performance, comparison of transpiration and forced-convection cooling, and pressure environment of the wire cloth are provided.
Date: August 19, 1954
Creator: Koffel, William K.
Item Type: Refine your search to only Report
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Preliminary experimental investigation of transpiration cooling for an afterburner with a sintered, porous stainless-steel combustion-chamber wall

Description: Report presenting an experimental investigation of the application of transpiration air-cooling to the combustion-chamber wall of an afterburner. Results regarding the typical temperature and pressure profiles, correlation of wall temperatures, distribution of cooling-air flux density, longitudinal distribution of cooling air, longitudinal distribution of wall temperature, effect of permeability on cooling-air requirements, and fabricating and operating problems are provided.
Date: June 8, 1953
Creator: Koffel, William K.
Item Type: Refine your search to only Report
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A unit laboratory engine oil system providing for a remote indication of oil flow and oil consumption together with blow-by measurement

Description: From Summary: "A unit oil system and oil-weighing device designed for laboratory engine tests to permit the remote measurement of oil-flow rate and oil consumption is described. The system regulates the oil pressure and temperature and is closed to make possible the accurate measurement of blow-by gas. The oil is weighed by a self-contained diaphragm and pilot-valve assembly, which uses compressed air as the transmitting medium. Several of those unit systems have given satisfactory service for … more
Date: September 1944
Creator: Koffel, William K. & Biermann, Arnold E.
Item Type: Refine your search to only Report
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Cooling characteristics of an experimental tail-pipe burner with an annular cooling-air passage

Description: The effects of tail-pipe fuel-air ratio (exhaust-gas temperatures from approximately 3060 degrees to 3825 degrees R), radial distribution of tail-pipe fuel flow, and mass flow of combustion gas and the inside wall were determined for an experimental tail-pipe burner cooled by air flowing through and insulated cooling-air to combustion gas mass flow from 0.066 to 0.192 were also determined. Results regarding the reproducibility of combustion-gas temperature profiles, effect of variables on avera… more
Date: February 26, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Item Type: Refine your search to only Report
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Empirical Cooling Correlation for an Experimental Afterburner With an Annular Cooling Passage

Description: Memorandum presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation relates the average combustion-chamber wall temperature at a station near the combustion-chamber outlet to the temperatures of the cooling air and combustion gas, and to the mass flows of the cooling air and combustion gas.
Date: June 26, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Item Type: Refine your search to only Report
open access

Empirical cooling correlation for an experimental afterburner with an annular cooling passage

Description: Report presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation equation is useful for shortening the experimental investigation of afterburner cooling characteristics inasmuch as it provides a method for interpolating the critical wall temperatures for other combinations of operating variables.
Date: June 26, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Item Type: Refine your search to only Report
open access

Investigation of heat-transfer coefficients in an afterburner

Description: Report presenting an evaluation of the relative importance of heat-transfer modes in an experimental afterburner. The convective heat-transfer coefficients near the combustion-chamber outlet were determined and the effects of three radial distributions of afterburner fuel across the turbine-outlet annulus on the convective heat-transfer coefficient were examined.
Date: June 27, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Item Type: Refine your search to only Report
open access

Some screeching-combustion characteristics of a transpiration-cooled afterburner having a porous wall of wire cloth

Description: Report presenting an investigation of the screeching characteristics of two flame-holder configurations in a full-scale transpiration-cooled afterburner. The investigation indicated that a porous wall of wire cloth may be effective in eliminating or reducing the tendency to screech in some high-performance afterburners, but further testing is required. Results regarding the diametrical V-gutter, single-ring V-gutter, and durability of wire cloth are provided.
Date: November 29, 1954
Creator: Koffel, William K.; Harp, James L., Jr. & Bryant, Lively
Item Type: Refine your search to only Report
open access

Cooling of ram jets and tail-pipe burners: analytical method for determining temperatures of combustion chamber having annular cooling passage

Description: Report presenting an analytical method for calculating the maximum wall temperature of a tail-pipe burner or a ramjet combustion chamber cooled by air or gas flowing through a surrounding annular passage.
Date: March 21, 1950
Creator: Koffel, William K.; Stamper, Eugene & Sanders, Newell D.
Item Type: Refine your search to only Report
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Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 4: rotor loss patterns as determined by hot-wire anemometers with rotor operating in a circumferentially uniform inlet flow field

Description: Report discussing the use of hot-wire anemometers to measure circumferential traces of specific-mass-flow variation for various radial positions at the rotor exit. Results regarding the rotor blade-wake traces, relative total-pressure ratio, and centrifuging of low-momentum fluid are provided.
Date: May 20, 1958
Creator: Kofskey, Milton G. & Allen, Hubert W.
Item Type: Refine your search to only Report
open access

Smoke study of nozzle secondary flows in a low-speed turbine

Description: Still and motion pictures were made of boundary-layer and wake secondary-flow phenomena visualized by smoke. Two annular cascades of turbine nozzles were used, both designed for constant discharge angle but differing in blade shape and suction-surface velocity distribution. Flows were similar to those obtained with pressure and angle measurements at near-sonic airspeeds. Boundary-layer cross-channel and trailing-edge radial flows caused vortices and an accumulation of low-momentum air at the hu… more
Date: November 1954
Creator: Kofskey, Milton G. & Allen, Hubert W.
Item Type: Refine your search to only Report
open access

Visualization of rotor tip secondary flows with blade tip air discharge and suction in a low-speed turbine

Description: Smoke was used to visualize outer-wall secondary flows in a low-speed turbine utilizing rotor tip air discharge and suction. Photographs as well as visual observations of the effect of tip air discharge and suction were made by independently varying the direction and quantity of the tip air discharge and suction, and varying tip clearance, and main-stream air speed. In addition, the cross-sectional area of the hollow blade discharge opening was varied for the case of tip air discharge.
Date: August 17, 1956
Creator: Kofskey, Milton G. & Allen, Hubert W.
Item Type: Refine your search to only Report
open access

Experimental investigation of flow in an annular cascade of turbine nozzle blades of constant discharge angle

Description: The experimental performance of turbine nozzle blades designed for a constant discharge angle was investigated at discharge hub Mach numbers of 1.18, 1.31, and 1.41. Flow characteristics are presented in terms of energy losses, angle gradients, and secondary flow effects. Blade efficiency decreased from 0.983 to 0.978 with increasing Mach number in the range investigated while angle variations in the loss regions became very large, indicating poorer blade performance than efficiency implies.
Date: March 3, 1952
Creator: Kofskey, Milton G.; Rohlik, Harold E. & Monroe, Daniel E.
Item Type: Refine your search to only Report
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Development of Direct Contact Condensation Multistage Flash Distillation Process: Phase 3A

Description: Report investigating the feasibility of the Atomics International Direct Contact Condensation Multistage Flash (DCC-MSF) Distillation process using "analytical and experimental studies on a direct contact condensation module and a plastic film heat exchanger. (p. iii) Contains further studies and evaluations of the direct-contact condensation unit and plastic film heat exchanger.
Date: January 1971
Creator: Kohl, A. L.; Shimazaki, T. T.; Suratt, W. B. & Westerman, S.
Item Type: Refine your search to only Report
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Development of Direct Contact Condensation Multistage Flash Distillation Process: Phase 1

Description: Report investigating the feasibility of the Atomics International Direct Contact Condensation Multistage Flash (DCC-MSF) Distillation process using "analytical and experimental studies on a direct contact condensation module and a plastic film heat exchanger. (p. iii)
Date: September 1969
Creator: Kohl, A. L.; Shimazaki, T. T.; Wetch, J. R. & Bienvenue, L. L.
Item Type: Refine your search to only Report
open access

Development of Direct Contact Condensation Multistage Flash Distillation Process: Phase 2

Description: Report investigating the feasibility of the Atomics International Direct Contact Condensation Multistage Flash (DCC-MSF) Distillation process using "analytical and experimental studies on a direct contact condensation module and a plastic film heat exchanger. (p. iii) Contains further studies and evaluations of the direct-contact condensation unit and plastic film heat exchanger.
Date: May 1970
Creator: Kohl, A. L.; Shimazaki, T. T.; Wetch, J. R. & Suratt, W. B.
Item Type: Refine your search to only Report
open access

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 … more
Date: April 1957
Creator: Kohl, Robert C. & Algranti, Joseph S.
Item Type: Refine your search to only Report
open access

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 m… more
Date: January 1947
Creator: Kohl, Robert C. & Diggs, Donald R.
Item Type: Refine your search to only Report
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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 … more
Date: December 26, 1946
Creator: Kohl, Robert C. & Larkin, Robert G.
Item Type: Refine your search to only Report
open access

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.
Item Type: Refine your search to only Report
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