127 Matching Results

Search Results

Advanced search parameters have been applied.

Friction of compression-ignition engines

Description: "The cost in mean effective pressure of generating air flow in the combustion chambers of single-cylinder compression-ignition engines was determined for the prechamber and the displaced-piston types of combustion chamber. For each type a wide range of air-flow quantities, speeds, and boost pressures was investigated. Supplementary tests were made to determine the effect of lubricating-oil temperature, cooling-water temperature, and compression ratio on the friction mean effective pressure of the single-cylinder test engine" (p. 1).
Date: August 1936
Creator: Moore, Charles S. & Collins, John H., Jr.
Partner: UNT Libraries Government Documents Department

Effects of air-fuel spray and flame formation in a compression-ignition engine

Description: "High-speed motion pictures were taken at the rate of 2,500 frames per second of the fuel spray and flame formation in the combustion chamber of the NACA combustion apparatus. The compression ratio was 13.2 and the speed 1,500 revolutions per minute. An optical indicator was used to record the time-pressure relationship in the combustion chamber. The air-fuel ratio was varied from 10.4 to 365. The results showed that as the air-fuel ratio was increased definite stratification of the charge occurred in the combustion chamber even though moderate air flow existed. The results also showed the rate of vapor diffusion to be relatively slow" (p. 119).
Date: August 26, 1935
Creator: Rothrock, A. M. & Waldron, C. D.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Transverse Oscillations in a Cylindrical Combustion Chamber

Description: Note presenting a study of certain features of transverse resonance in an idealized combustion chamber. Modes of weak oscillation are described with average Mach number neglected but with the effect of axial gradient of mean temperature considered. The nature of finite transverse periodic waves is also analyzed.
Date: October 1954
Creator: Moore, Franklin K. & Maslen, Stephen H.
Partner: UNT Libraries Government Documents Department

Determination of Ram-Jet Combustion-Chamber Temperatures by Means of Total-Pressure Surveys

Description: "A method is described by which the total temperature of the gases at the combustion-chamber outlet of a ram-jet engine may be determined from the loss in total pressure measured across the combustion chamber. A working chart is presented by means of which the ratio of the total temperature of the gases at the combustion-chamber outlet to the total temperature of the gases at the combustion-chamber inlet may be determined from the measured loss of total pressure across the combustion chamber and the known values of air flow, total pressure, and total temperature at the combustion-chamber inlet. Values of total-temperature ratio across the combustion chamber of a 20-inch ram jet were obtained in the Cleveland altitude wind tunnel over a range of pressure altitudes from 6000 to 15,000 feet" (p. 1).
Date: March 3, 1947
Creator: Pinkel, I. Irving
Partner: UNT Libraries Government Documents Department

Determination of Ram-Jet Combustion-Chamber Temperatures by Means of Total-Pressure Surveys

Description: Note presenting a method by which the total temperature of the gases at the combustion-chamber outlet of a ramjet engine may be determined from the loss in total pressure measured across the combustion chamber. Values of total-temperature ratio across the combustion chamber of a 20-inch ram jet were obtained in the altitude wind tunnel over a range of pressure altitudes.
Date: December 1951
Creator: Pinkel, I. Irving
Partner: UNT Libraries Government Documents Department

Engine Knock and Combustion Chamber Form

Description: The present report is confined to the effect of the combustion chamber shape on engine knock from three angles, namely: 1) The uniformity of flame-front movement as affected by chamber design and position of the spark plug; 2) The speed of advance of the flame as affected by turbulence and vibrations; 3) The reaction processes in the residual charge as affected by the walls.
Date: October 1939
Creator: Zinner, Karl
Partner: UNT Libraries Government Documents Department

Altitude-Test-Chamber Investigation of Performance of a 28-Inch Ram-Jet Engine 1: Combustion and Operational Performance of Four Combustion-Chamber Configurations

Description: An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Mach number of approximately 2.0 for altitudes of 40,000 to 50,000 feet was conducted at the NACA Lewis laboratory. Three different flame holders, varying in the number and size of the annular gutters, in conjunction with several fuel-injection systems were investigated. The combustion efficiency for the flame-holder fuel-injection system that provided the best over-all operational fuel-air-ratio range (0.03 to 0.075) was over 0.9 at a fuel-air ratio of about 0.065 for the altitude range investigated.
Date: August 23, 1950
Creator: Jones, W. L.; Shillito, T. B. & Henzel, J. G., Jr.
Partner: UNT Libraries Government Documents Department

Influence of Combustion-chamber Length on Afterburner Performance

Description: Memorandum presenting an investigation of the influence of combustion-chamber length on afterburner performance under conditions simulating altitude flight. Results regarding afterburner-inlet conditions, operational limits, and structural cooling requirements are provided.
Date: August 27, 1954
Creator: Useller, James W.; Braithwaite, Willis M. & Rudey, Carl J.
Partner: UNT Libraries Government Documents Department

The Performance of Several Combustion Chambers Designed for Aircraft Oil Engines

Description: "Several investigations have been made on single-cylinder test engines to determine the performance characteristics of four types of combustion chambers designed for aircraft oil engines. Two of the combustion chambers studied were bulb-type precombustion chambers, the connecting orifice of one having been designed to produce high turbulence by tangential air flow in both the precombustion chamber and the cylinder. The other two were integral combustion chambers, one being dome-shaped and the other pent-roof shaped" (p. 501).
Date: 1928
Creator: Joachim, William F. & Kemper, Carlton
Partner: UNT Libraries Government Documents Department

Preliminary Investigation of a Ceramic Lining for a Combustion Chamber for Gas-Turbine Use

Description: Combustion chamber liners for gas turbines and experimental set-ups were tested for failure. A ceramic-lined test chamber was operated at fuel/air ratios up to 0.050. Thermal-shock evaluation indicated that a ceramic lining, which expands after firing, would crack but would not fall apart during operation. Refractoriness of the lining and the resistance to mechanical shock were adequate. In general, shell temperature reductions of approximately 400 deg F were effected by the use of this lining at fuel/air ratios of 0.016 and 0.050. The mechanism of failure of the ceramic lining was induced by sudden heating and cooling during operation.
Date: April 12, 1948
Creator: Woodward, William H. & Bobrowsky, A. R.
Partner: UNT Libraries Government Documents Department

Experimental investigation of a lightweight rocket chamber

Description: From Summary: "Experiments have been conducted with a jacketed rocket combustion chamber that was fabricated by hydraulic forming from sheet metal. Rocket combustion chambers made by this method have been used successfully. Runs with these combustion chambers have been made at overall heat-transfer rates of 2.5 Btu per square inch per second with water cooling and also with ammonia as a regenerative coolant."
Date: October 1956
Creator: Dalgleish, John E. & Tischler, Adelbert O.
Partner: UNT Libraries Government Documents Department

Analytical and experimental performance of an explosion-cycle combustion chamber for a jet-propulsion engine

Description: From Introduction: "The results of analytical and experimental investigations conducted at the NACA Cleveland laboratory to determine the performance of an explosion-cycle combustion chamber with a timed inlet valve and several fixed-area exhaust nozzles are presented herein. These values are compared with theoretical values obtained from an analysis of an ideal constant-volume cycle and an approximate constant-volume cycle, which is presented."
Date: September 1948
Creator: Zipkin, Morris A. & Lewis, George W., Jr.
Partner: UNT Libraries Government Documents Department

Analysis of Jet-Propulsion-Engine Combustion-Chamber Pressure Losses

Description: From Summary: "The development and the use of a chart for estimating the pressure losses in jet-engine combustion chambers are described. By means of the chart, the pressure losses due to fluid friction and to momentum changes in the air flow accompanying combustion can be separately evaluated. The over-all pressure losses computed from the pressure-loss chart are within 7 percent of the experimental values for the three types of combustion chambers considered herein."
Date: July 31, 1946
Creator: Pinkel, I. Irving & Shames, Harold
Partner: UNT Libraries Government Documents Department

A Preliminary Investigation of Combustion With Rotating Flow in an Annular Combustion Chamber

Description: Memorandum presenting a preliminary investigation of flame-stability and flame-extinction characteristics of a propane-air mixture in an annular combustion chamber conducted with both straight and rotational flow. The rotating mixture burned at higher axial-inlet stream velocities and with more stable flames than could be obtained with straight-flow burning.
Date: September 18, 1951
Creator: Schwartz, Ira R.
Partner: UNT Libraries Government Documents Department

Experimental Study of Ignition by Hot Spot in Internal Combustion Engines

Description: "In order to carry out the contemplated study, it was first necessary to provide hot spots in the combustion chamber, which could be measured and whose temperature could be changed. It seemed difficult to realize both conditions working solely on the temperature of the cooling water in a way so as to produce hot spots on the cylinder wall capable of provoking autoignition. Moreover, in the majority of practical cases, autoignition is produced by the spark plug, one of the least cooled parts in the engine. The first procedure therefore did not resemble that which most generally occurs in actual engine operation" (p. 1).
Date: August 1938
Creator: Serruys, Max
Partner: UNT Libraries Government Documents Department

Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine 5 - Combustion-Chamber Characteristics

Description: "An investigation to determine the performance and operational characteristics of the TG-1OOA gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet rm-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and corrected horsepower" (p. 1).
Date: December 31, 1947
Creator: Gensenheyner, Robert M. & Berdysz, Joseph J.
Partner: UNT Libraries Government Documents Department

Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine 5 - Combustion-Chamber Characterisitcs

Description: "An investigation to determine the performance and operational characteristics of an axial-flow gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet ram-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and corrected horsepower" (p. 1).
Date: August 6, 1948
Creator: Geisenheyner, Robert M. & Berdysz, Joseph J.
Partner: UNT Libraries Government Documents Department

Considerations of air flow in combustion chambers of high-speed compression-ignition engines

Description: The air flow in combustion chambers is divided into three fundamental classes - induced, forced, and residual. A generalized resume is given of the present status of air flow investigations and of the work done at this and other laboratories to determine the direction and velocity of air movement in auxiliary and integral combustion chambers. The effects of air flow on engine performance are mentioned to show that although air flow improves the combustion efficiency, considerable induction, friction, and thermal losses must be guarded against.
Date: April 1932
Creator: Spanogle, J. A. & Moore, C. S.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine 6: Combustion-Chamber Performance

Description: "An analysis of the performance of the types A, B, and C combustion chambers of the 4000-pound-thrust axial-flow turbojet engine is presented. The data were obtained from investigations of the complete engine over a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.00 to 1.86. The combustion-chamber pressure losses, the effect of the losses on cycle efficiency, and the combustion efficiency are discussed" (p. 1).
Date: August 4, 1948
Creator: Pinkel, I. Irving & Shames, Harold
Partner: UNT Libraries Government Documents Department

A Polar-Coordinate Survey Method for Determining Jet-Engine Combustion-Chamber Performance

Description: Note describing the use of an automatic polar-coordinate traversing system for determining jet-engine combustor performance. This method furnishes complete temperature, pressure, and flow profiles with a single probe. It provides a means of calculating mass-weighted or area-average mean temperatures and pressure for evaluating combustion efficiency and pressure loss.
Date: September 1955
Creator: Friedman, Robert & Carlson, Edward R.
Partner: UNT Libraries Government Documents Department

Combustion-Chamber Performance Characteristics of a Python Turbine-Propeller Engine Investigated in Altitude Wind Tunnel

Description: Combustion-chamber performance characteristics of a Python turbine-propeller engine were determined from investigation of a complete engine over a range of engine speeds and shaft horsepowers at simulated altitudes. Results indicated the effect of engine operating conditions and altitude on combustion efficiency and combustion-chamber total pressure losses. Performance of this vaporizing type combustion chamber was also compared with several atomizing type combustion chambers.
Date: November 16, 1951
Creator: Campbell, Carl E.
Partner: UNT Libraries Government Documents Department

Effect of Inlet-Air Parameters on Combustion Limit and Flame Length in 8-Inch-Diameter Ram-Jet Combustion Chamber

Description: Report presenting an investigation with a ram-jet combustion chamber to determine the effect of fuel-air ratio and the inlet-air parameters of pressure, temperature, and velocity on combustion limit, combustion efficiency, and flame length.
Date: July 22, 1948
Creator: Cervenka, A. J. & Miller, R. C.
Partner: UNT Libraries Government Documents Department