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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
The Combination of Internal-Combustion Engine and Gas Turbine

The Combination of Internal-Combustion Engine and Gas Turbine

Date: April 1, 1947
Creator: Zinner, K.
Description: While the gas turbine by itself has been applied in particular cases for power generation and is in a state of promising development in this field, it has already met with considerable success in two cases when used as an exhaust turbine in connection with a centrifugal compressor, namely, in the supercharging of combustion engines and in the Velox process, which is of particular application for furnaces. In the present paper the most important possibilities of combining a combustion engine with a gas turbine are considered. These "combination engines " are compared with the simple gas turbine on whose state of development a brief review will first be given. The critical evaluation of the possibilities of development and fields of application of the various combustion engine systems, wherever it is not clearly expressed in the publications referred to, represents the opinion of the author. The state of development of the internal-combustion engine is in its main features generally known. It is used predominantly at the present time for the propulsion of aircraft and road vehicles and, except for certain restrictions due to war conditions, has been used to an increasing extent in ships and rail cars and in some fields ...
Contributing Partner: UNT Libraries Government Documents Department
Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5

Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5

Date: September 26, 1958
Creator: Lampkin, Bedford A & Tunnell, Phillips J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine, III, Over-All Performance of Compressor

Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine, III, Over-All Performance of Compressor

Date: January 1, 1949
Creator: Hartmann, Melvin J. & Tysl, Edward R.
Description: An investigation was conducted to determine the performance characteristics of the rotor and inlet guide vanes used in the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. Outlet stators used in the engine were omitted to facilitate study of the supersonic rotor. The extent of the deviation from design performance indicates that the design-shock configuration was not obtained. A maximum pressure ratio of 2.26 was obtained at an equivalent tip speed of 1614 feet per second and an adiabatic efficiency of 0.61. The maximum efficiency obtained was 0.79 at an equivalent tip speed of 801 feet per second and a pressure ratio of 1.29. The performance obtained was considerably below design performance. The effective aerodynamic forces encountered appeared to be large enough to cause considerable damage to the thin aluminum leading edges of the rotor blades.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Date: September 26, 1958
Creator: Mugler, John P , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Stability of Plates and Shells Beyond the Proportional Limit

Stability of Plates and Shells Beyond the Proportional Limit

Date: October 1, 1947
Creator: Ilyushin, A. A.
Description: In the present paper is examined the method of investigating the stability of plates and shells beyond the elastic limit, that proceeds from the generalization of the Hencky-Mises theory of elastico-plastic deformations given in the works of Smirnov-Alyayev, Schmidt, and in our papers.
Contributing Partner: UNT Libraries Government Documents Department
Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine

Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine

Date: July 11, 1957
Creator: Schurn, Harold J.
Description: The multistage turbine from the J73 turbojet engine has previously been investigated with standard and with reduced-chord rotor blading in order to determine the individual performance characteristics of each configuration over a range of over-all pressure ratio and speed. Because both turbine configurations exhibited peak efficiencies of over 90 percent, and because both units had relatively wide efficient operating ranges, it was considered of interest to determine the performance of the first stage of the turbine as a separate component. Accordingly, the standard-bladed multistage turbine was modified by removing the second-stage rotor disk and stator and altering the flow passage so that the first stage of the unit could be operated independently. The modified single-stage turbine was then operated over a range of stage pressure ratio and speed. The single-stage turbine operated at a peak brake internal efficiency of over 90 percent at an over-all stage pressure ratio of 1.4 and at 90 percent of design equivalent speed. Furthermore, the unit operated at high efficiencies over a relatively wide operating range. When the single-stage results were compared with the multistage results at the design operating point, it was found that the first stage produced approximately half the total multistage-turbine work ...
Contributing Partner: UNT Libraries Government Documents Department
Russian Laminar Flow Airfoils 3rd Part: Measurements on the Profile No. 2315 BIS with Ava-Nose Flap

Russian Laminar Flow Airfoils 3rd Part: Measurements on the Profile No. 2315 BIS with Ava-Nose Flap

Date: September 1, 1947
Creator: Riegels, F.
Description: The tests on the Russian airfoil 2315 Bis were continued. This airfoil shows, according to Moscow tests, good laminar flow characteristics. Several tests were prepared in the large wind tunnel at Gottingen; partial results were obtained.
Contributing Partner: UNT Libraries Government Documents Department
Recent Results on High-Pressure Axial Blowers

Recent Results on High-Pressure Axial Blowers

Date: April 1, 1947
Creator: Eckert, B.
Description: Considerable progress has, in recent times, been attained in the development of the high-pressure axial blower by well-planned research. The efforts are directed toward improving the efficiencies, which are already high for the axial blower, and in particular the delivery pressure heads. For high pressures multistage arrangements are used. Of fundamental importance is the careful design of all structural parts of the blower that are subject to the effects of the flow. In the present report, several recent results and experiences are reported, which are based on results of German engine research.
Contributing Partner: UNT Libraries Government Documents Department
Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research              airplane at transonic speeds

Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research airplane at transonic speeds

Date: July 15, 1958
Creator: Keener, Earl R; Mcleod, Norman J & Taillon, Norman V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of First-Stage Blade Design on Performance of Mark 25 Torpedo Power Plant

Effect of First-Stage Blade Design on Performance of Mark 25 Torpedo Power Plant

Date: August 4, 1948
Creator: Schum, Harold J. & Hoyt, Jack W.
Description: The effect of rotor-blade length, inlet angle, and shrouding was investigated with four different nozzles in a single-stage modification of the Mark 25 aerial-torpedo power plant. The results obtained with the five special rotor configurations are compared with those of the standard first-stage rotor with each nozzle. Each nozzle-rotor combination was operated at nominal pressure ratios of 8, 15 (design), and 20 over a range of speeds from 6000 rpm to the design speed of 18,000 rpm. Inlet temperature and pressure conditions of 1OOOo F and 95 pounds per square inch gage, respectively, were maintained constant for all runs.
Contributing Partner: UNT Libraries Government Documents Department