WorldCat Identities

Aircraft Engine Research Laboratory

Overview
Works: 292 works in 343 publications in 1 language and 878 library holdings
Classifications: TL501,
Publication Timeline
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Most widely held works by Aircraft Engine Research Laboratory
Knock-limited performance of pure hydrocarbons blended with a base fuel in a full-scale aircraft engine cylinder. 1 - Eight paraffins, two olefins by Anthony W Jones( Book )

2 editions published in 1944 in English and held by 5 WorldCat member libraries worldwide

The object of this report was to determine the knock-limited performance of a full-scale aircraft-engine cylinder of leaded blends of 10 pure hydrocarbons and a base fuel
The performance of a single-stage impulse turbine having an 11.0-inch pitch-line diameter wheel with cast airfoil-shaped and bent sheet-metal nozzle blades by David S Gabriel( Book )

3 editions published in 1945 in English and held by 5 WorldCat member libraries worldwide

Efficiency tests have been made on a single-stage gas turbine having an 11.0-inch pitch-line diameter wheel and a nozzle diaphragm with cast airfoil-shaped nozzle blades using atmospheric air as the driving fluid. A comparison of these tests with previous tests made on the same turbine but with a nozzle diaphragm having fabricated bent sheet-metal blades is given
Heat-transfer tests of a steel cylinder barrel with aluminum fins of optimum proportions by Herman H Ellerbrock( Book )

2 editions published in 1940 in English and held by 4 WorldCat member libraries worldwide

The present report presents the results of tests made on two more engine cylinder barrels with aluminum fins. The method of attaching the fins to the steel for these barrels is similar to that of the barrel described in reference 1. The two barrels, the results for which are to be presented herein, were manufactured by a method to be used in the factory production of large numbers of engine barrels. The purpose of the tests was to determine the heat-transfer coefficients and the excellence of the bonds between the aluminum fins and the aluminum bases and the between the aluminum base and the steel of the two barrels when manufactured by a large-volume production method
Operating temperatures of a sodium-cooled exhaust valve as measured by a thermocouple by Julio Sanders( Book )

2 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide

A thermocouple was installed in the crown of a sodium-cooled exhaust valve. The valve was then tested in an air-cooled engine cylinder and valve temperatures under various engine operating conditions were determined. A temperature of 1337 degrees F was observed at a fuel-air ratio of 0.064, a brake mean effective pressure of 179 pounds per square inch, and an engine speed of 2000 rpm. Fuel-air ratio was found to have a large influence on valve temperature, but cooling-air pressure and variation in spark advance had little effect. An increase in engine power by change of speed or mean effective pressure increased the valve temperature. It was found that the temperature of the rear spark-plug bushing was not a satisfactory indication of the temperature of the exhaust valve
Heat-transfer tests of aqueous ethylene glycol solutions in an electrically heated tube by Everett Bernardo( Book )

2 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide

As part of an investigation of the cooling characteristics of liquid-cooled engines, tests were conducted with an electrically heated single-tube heat exchanger to determine the heat-transfer characteristics of AN-E-2 ethylene glycol and other ethylene glycol-water mixtures for a range of conditions
A preliminary investigation of the icing characteristics of a large rectangular-throat pressure-type carburetor by Gilbert E Chapman( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

A rectangular-throat pressure-type carburetor was investigated to determine the icing characteristics of this part of a large four-engine bomber induction system. Runs of 15-minute duration were made at a simulated low-cruising power condition over a range of carburetor-air temperatures from 12 to 100 degrees F with varied moisture contents to establish the limiting conditions for the formation of visible and serious icing. The investigation included icing tests made with a standard nozzle bar and an impinging-jets nozzle bar
End-zone water injection as a means of suppressing knock in a spark-ignition engine by Rinaldo J Brun( Book )

3 editions published between 1944 and 1945 in English and held by 3 WorldCat member libraries worldwide

The engine operating conditions of the tests did not simulate those encountered in flight, especially with regard to the operating speed of 570 rpm. For this reason the results should only be regarded as of theoretical importance until further investigation has been made
Relation between spark-ignition engine knock, detonation waves, and autoignition as shown by high-speed photography by Cearcy D Miller( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

A critical review of literature bearing on the autoignition and detonation-wave theories of spark-ignition engine knock and on the nature of gas vibrations associated with combustion and knock results in the conclusion that neither the autoignition theory nor the detonation-wave theory is an adequate explanation of spark-ignition engine knock. A knock theory is proposed, combining the autoignition and detonation-wave theories, introducing the idea that the detonation wave develops in autoignited or afterburning gases, and ascribing comparatively low-pitched heavy knocks to autoignition but high-pitched pinging knocks to detonation waves with the possibility of combinations of the two types of knock
Air-flow and performance characteristics of engine-stage supercharger of a double-row radial aircraft engine. 2 - Effect of design variables by Edmund J Baas( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

An investigation has been conducted to determine the effect of the location of the diffuser vanes with respect to the supercharger outlets and the effect of flow conditions at the impeller inlet on the air-flow distribution in the outlets of the engine-state supercharger of an 18-cylinder double-row radial aircraft engine. The standard 13-vane diffuser rotated 180 degrees from its original position and an NACA designed 18-vane diffuser were used to determine the effect of the diffuser-vane location with respect to the supercharger outlets. The 18 vanes of the diffuser correspond to the 18 outlets of the supercharger. The effect of flow conditions at the impeller inlet was investigated by distorting the flow at the inlet and noting the effect in the supercharger outlets. An NACA vaneless diffuser was used in this investigation to eliminate the diffuser-vane effect
The effect of increase in combustion-air inlet temperature from 80 to 130 degrees F on the sea-level performance of a 22-inch-diameter pulse-jet engine by Michael F Valerino( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

Data from a sea-level investigation of a 22-inch-diameter pulse-jet engine installed on a thrust stand were analyzed to determine the effect on the engine performance of a change in combustion-air temperature from approximately 80 to 130 degrees F. The tests at both combustion-air temperatures covered a range of simulated ram pressures from 19 to 58 inches of water for the fuel-flow range of resonant operation
The NACA balanced-diaphragm dynamometer-torque indicator by Charles S Moore( Book )

2 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide

A balanced-diaphragm device for measuring dynamometer torque of single-cylinder or multi-cylinder engines is described. This device, which was developed for laboratory use, has proved to be accurate, reliable, and adaptable. Compressed air, automatically controlled, is used as the balancing and the transmitting fluid; thus, a simple method of obtaining torque measurement at a remote position is provided
Nitrided-steel piston rings for engines of high specific power by John H Collins( Book )

2 editions published in 1944 in English and held by 3 WorldCat member libraries worldwide

Several designs of nitrided-steel piston rings were performance-tested under variable conditions of output. The necessity of good surface finish and conformity of the ring to the bore was indicated in the first tests. Nitrided-steel rings of the same dimensions as cast-iron rings operating on the original piston were not satisfactory. The final design was a lighter, rectangular, thin face-width ring used on a piston having a maximum cross-head area and the proper skirt shape. Results were obtained from tests of single-cylinder and multicylinder engines
Knock-limited performance of pure hydrocarbons blended with a base fuel in a ful-scale, aircraft-engine cylinder. 3 - Four aromatics, six ethers by Anthony W Jones( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

Knock-limited performance tests of leaded blends of four pure aromatic hydrocarbons and six pure ethers with a base fuel were conducted in a full-scale aircraft-engine cylinder at two operating conditions to determine the antiknock effectiveness of additions of pure compounds to aviation fuels
The knock-limited performance of fuel blends containing aromatics. 5 - n-propylbenzene, n-butylbenzene, isobutylbenzene, m-xylene, and 1-isopropyl-4-methylbenzene by Carl L Meyer( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

Results are reported of knock-limited tests of five aromatics, each individually blended with selected base fuels and tested with and without TEL, using 17.6, F-4, and F-3 small-scale engines. The five aromatics rated in the following order of decreasing antiknock effectiveness at fuel/air ratio 0.10: m-xylene, 1-isopropyl-4-methylbenzene, n-propylbenzene, isobutylbenzene, and n-butylbenzene
Knocking tendency of an air-cooled aircraft-engine cylinder with one and with two spark plugs by R. C Spencer( Book )

2 editions published in 1943 in English and held by 3 WorldCat member libraries worldwide

Tests have been conducted with an air-cooled aircraft-engine cylinder to determine the effect on the knocking tendency of cutting out one spark plug when the engine is operating at or near the knock point with two spark plugs firing
Determination of gas temperatures from the frequency of knock-induced gas vibrations in an internal-combustion engine by W. E Moeckel( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

The object of this report was to develop a method of obtaining gas temperatures from the frequency of knock-induced gas vibrations in and internal combustion engine cylinder
Knock-limited performance tests of 2,2,3,4-tetramethylpentane, 2,3,3,4-tetramethylpentane, 3,4,4-trimethyl-2-pentene, and 2,3,4-trimethyl-2-pentene in small-scale and full-scale cylinders by Edmund R Jonash( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

Knock-limited tests were conducted with F-4, F-3, and 17.6 small-scale engines and with a full-scale cylinder on blends containing the following purified hydrocarbons: 2,2,3,4-tetramethylpentane, 2,3,3,4-tetramethylpentane, 3,4,4-trimethyl-2-pentene, and 2,3,4-trimethyl-2-pentene
The effect of inlet temperature and pressure on the efficiency of a single-stage impulse turbine having a 13.2-inch pitch-line diameter wheel by Ernest R Chanes( Book )

2 editions published in 1945 in English and held by 3 WorldCat member libraries worldwide

Efficiency tests have been conducted on a single-stage impulse turbine having a 13.2-inch pitch-line diameter wheel and a cast nozzle diaphragm over a range of turbine speeds from 3000 to 17,000 rpm pressure ratios from 1.5 to 5.0, inlet total temperatures from 1200 to 2000 degrees R, and inlet total pressures from 18 to 59 inches of mercury absolute. The effect of inlet temperature and pressure on turbine efficiency for constant pressure ratio and blade-to-jet speed ratio is correlated against a factor derived from the equation for Reynolds number. The degree of correlation indicates that the change in turbine efficiency with inlet temperature and pressure for constant pressure ratio and blade-to-jet speed ratio is principally a Reynolds number test
A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine - 2 by Henry E Alquist( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

The knock-limited performance of nine fuels, comprising isolated members of four classes of hydrocarbons, paraffins, cycloparaffins, and olefins), is presented in the form of three-dimensional plots of fuel-air ratio, compression temperature, and compression-air density. The plots are based on a correlation that is shown to apply for these fuels over a wide range of compression that is shown to apply for these fuels over a wide range of compression ratios and inlet-air temperatures. The significance of the term "temperature sensitivity" is sketched, and it is emphasized that no generalized number such as octane number can be applied even to members of a given class of hydrocarbons when broad ranges of engine severity are encountered
Analysis of spark-ignition engine knock as seen in photographs taken at 200,000 frames a second by Cearcy D Miller( Book )

2 editions published in 1946 in English and held by 3 WorldCat member libraries worldwide

A motion-picture of the development of knock in a spark-ignition engine is presented, which consists of 20 photographs taken at intervals of 5 microseconds, or at a rate of 200,000 photographs a second, with an equivalent wide-open exposure time of 6.4 microseconds for each photograph. A motion picture of a complete combustion process, including the development of knock, taken at the rate of 40,000 photographs a second is also presented to assist the reader in orienting the photographs of the knock development taken at 200,000 frames per second are analyzed and the conclusion is made that the type of knock in the spark-ignition engine involving violent gas vibration originates as a self-propagating disturbance starting at a point in the burning or autoigniting gases and spreading out from that point through the incompletely burned gases at a rate as high as 6800 feet per second, or about twice the speed of sound in the burned gases. Apparent formation of free carbon particles in both the burning and the burned gas is observed within 10 microseconds after passage of the knock disturbance through the gases
 
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Alternative Names

controlled identityFlight Propulsion Research Laboratory

controlled identityUnited States. National Advisory Committee for Aeronautics

AERL (Aircraft Engine Research Laboratory)

NACA Aircraft Engine Research Laboratory

United States. National Advisory Committee for Aeronautics. Aircraft Engine Research Laboratory

Languages
English (45)