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  • Aircraft Propulsion and Power  (164)
  • 1950-1954  (38)
  • 1945-1949  (126)
  • 1
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    Preliminary Evaluation of Turbine Performance with Variable-Area Turbine Nozzles in a Turbojet Engine (1953)
    In:  CASI
    Details
    Publication Date: 2019-09-20
    Description: The performance of a two-stage turbine with variable-area first-stage turbine nozzles was determined in the NACA Lewis altitude wind tunnel over a range of simulated altitudes from 15,000 to 44,000 feet and engine speeds from 50 to 100 percent of rated speed. The variable-area turbine nozzles used in this investigation were primarily a test device for compressor research purposes and were not necessarily of optimum aerodynamic design. The results of this investigation are indicative of effects of turbine-nozzle-area variation on turbine performance within the operating range allowed by the engine. The variable-area turbine nozzles were found to be mechanically reliable and to have negligible leakage losses. Increasing the turbine-nozzle-throat area from 1.15 to 1.67 square feet increased the corrected turbine gas flow or effective turbine nozzle area about 10 percent. At a given corrected turbine speed and turbine pressure ratio, changing the turbine nozzle area from 1.30 to 1. 67 square feet lowered the turbine efficiency 3 or 4 percent. The effect of increasing the turbine nozzle area from 1.15 to 1.67 square feet (decreasing the turning angle about 7 1/2 degrees) would be to lower the turbine efficiency about 5 or 6 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52J20
    Format: application/pdf
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  • 2
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    Cooling of Gas Turbines (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A theoretical analysis of the radial temperature distribution through the rotor and constant cross sectional area blades near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the rotor and blade temperatures of a specific turbine using a gas flow of 55 pounds per second, a coolant flow of 6.42 pounds per second, and an average coolant temperature of 200 degrees F. The effect of using kerosene, water, and ethylene glycol was determined. The effect of varying blade length and coolant passage lengths with water as the coolant was also determined. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7B11c
    Format: application/pdf
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  • 3
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    Cooling of Gas Turbines (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to -metal heat transfer coefficient, and of the effect of changing the thermal conductivity of the blade metal for a constant cross sectional area blade with two quarter inch diameter coolant passages.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7B11F
    Format: application/pdf
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  • 4
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    Investigation of 10-Stage Axial-Flow X24C-2 Compressor (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 R for the 10-stage axial-flow X24C-2 compressor from the X24C-2 turbojet engine was investigated. the peak adiabatic temperature-rise efficiency for a given speed generally occurred at values of pressure coefficient fairly close to 0.35.For this compressor, the efficiency data at various speeds could be correlated on two converging curves by the use of a polytropic loss factor derived.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7G11
    Format: application/pdf
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  • 5
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    Temperatures and Stresses on Hollow Blades For Gas Turbines (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The present treatise reports on theoretical investigations and test-stand measurements which were carried out in the BMW Flugmotoren GMbH in developing the hollow blade for exhaust gas turbines. As an introduction the temperature variation and the stress on a turbine blade for a gas temperature of 900 degrees and circumferential velocities of 600 meters per second are discussed. The assumptions onthe heat transfer coefficients at the blade profile are supported by tests on an electrically heated blade model. The temperature distribution in the cross section of a blade Is thoroughly investigated and the temperature field determined for a special case. A method for calculation of the thermal stresses in turbine blades for a given temperature distribution is indicated. The effect of the heat radiation on the blade temperature also is dealt with. Test-stand experiments on turbine blades are evaluated, particularly with respect to temperature distribution in the cross section; maximum and minimum temperature in the cross section are ascertained. Finally, the application of the hollow blade for a stationary gas turbine is investigated. Starting from a setup for 550 C gas temperature the improvement of the thermal efficiency and the fuel consumption are considered as well as the increase of the useful power by use of high temperatures. The power required for blade cooling is taken into account.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1183 , Forschungsbericht-1879 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters Berlin-Adlershof
    Format: application/pdf
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  • 6
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    Computed Temperature Distribution and Cooling of Solid Gas-Turbine Blades (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Computations were made to determine the temperature distribution and cooling of solid gas-turbine blades.A range of temperatures was used from 1500 degrees to 2500 degrees F, blade-root temperatures from 100 degrees to 1000 degrees F, blade thermal conductivity from 8 to 220 BTU/(hr)(sq ft)(degrees F/ft), and net gas to metal heat transfer coefficients from 75 to 250 BTU/(hr)(sq ft)(degrees F).
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7B11h
    Format: application/pdf
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  • 7
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    Venturi Tube with Varying Mass Flow (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Measurements on three tubes with flow regulated by suction at the trainling edge of the tube are described. It was possible to vary the mass of air flowing through the tube over a large range. Such tubes could be used for shrouded propellers.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1191 , Zentrale fuer Wissenschaftliches Berichtswesen der Luftfahrtforschung des Generalluftzeugmeisters; 1945
    Format: application/pdf
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  • 8
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    Investigation of X24C-2 10-Stage Axial-Flow Compressor (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Effect of inlet-air pressure and temperature on the performance of the X24-2 10-Stage Axial-Flow Compressor from the X24C-2 turbojet engine was evaluated. Speeds of 80, 89, and 100 percent of equivalent design speed with inlet-air pressures of 6 and 12 inches of mercury absolute and inlet-air temperaures of approximately 538 degrees, 459 degrees,and 419 degrees R ( 79 degrees, 0 degrees, and minus 40 degrees F). Results were compared with prior investigations.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E7H22
    Format: application/pdf
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  • 9
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    The Flow Through Axial Turbine Stages of Large Radial Blade Length (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A calulation of the flow in turbine blading is reported that includes the calculation of effect of centrifugal force. Frictional losses on the stator blades and rotor blades are allowed.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1118 , Forschungsbericht-1750 , Deutsche Luftfahrtforschung; 1-39
    Format: application/pdf
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  • 10
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    Knock-Limited Power Outputs from a CFR Engine Using Internal Coolants (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation of the antiknock effectiveness of various additive-water solutions when used as internal coolants has been conducted at the NACA Cleveland laboratory. Nine compounds have been previously run in a CFR engine and the results are presented. In an effort to find a good anti-knock-coolant additive with more desirable physical properties than those of the nine compounds previously investigated, water solutions of four alkyl amines, three alkanolamines, six amides, and eight heterocyclic compounds were investigated and the results are presented.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E6L05a
    Format: application/pdf
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