12 Matching Results

Search Results

Advanced search parameters have been applied.
in creator/contributor: "Creagh, John W. R."  
Results: 1 - 12
open access

An investigation of valve-overlap scavenging over a wide range of inlet and exhaust pressures

Description: Report presenting an investigation conducted to determine the effect on the performance of a two-valve air-cooled aircraft cylinder of increasing the valve overlap from the conventional value of 40 degrees to 130 degrees. Results regarding general performance characteristics, specific air consumption and volumetric efficiencies, charge-air utilization, and effect of increased valve overlap on cylinder temperatures are provided.
Date: November 1947
Creator: Creagh, John W. R.; Hartmann, Melvin J. & Arthur, W. Lewis, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Utilization of external-compression diffusion principle in design of shock-in-rotor supersonic compressor blading

Description: Report presenting the application of the external-compression principle to a cascade of blades in an attempt to achieve a closer approach to isentropic contraction ratios in supersonic compressor blading. Tests of a rotor designed to incorporate the external-compression principle are provided. Results regarding overall performance, performance at design speed and peak efficiency, off-design performance, and some considerations for future designs are provided.
Date: September 11, 1953
Creator: Creagh, John W. R. & Klapproth, John F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance Characteristics of an Axial-Flow Transonic Compressor Operating Up to Tip Relative Inlet Mach Number of 1.34

Description: Performance data are presented for a transonic axial-flow compressor rotor designed to operate at a tip speed of 1300 ft/sec with maximum relative tip Mach number of 1.37. The compressor had an inlet diameter of 16 inches, a hub-tip diameter ratio of 0.5 and design specific weight flow of 31.1 (lb/sec/(sq ft frontal area). Experimental values of relative total-pressure-loss coefficient were considerably higher than the assumed values. This disparity, hub choking, and application of the simple r… more
Date: August 17, 1956
Creator: Creagh, John W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance Investigations of a Large Centrifugal Compressor from an Experimental Turbojet Engine

Description: From Summary: "An investigation was conducted on a large centrifugal compressor from an experimental turbojet engine to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal-type compressors. The results of the research conducted on the compressor indicated that the compressor would not meet the desired engine-design air-flow requirements (78 lb/sec) because of an air-flow restriction in the vaned collecto… more
Date: October 18, 1948
Creator: Ginsburg, Ambrose; Creagh, John W. R. & Ritter, William K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Compressor of XJ-41-V Turbojet Engine V-Performance Analysis of Compressor With Revised Vaned Collector Over Range of Compressor Speeds From 3600 to 11,500 RPM

Description: "An investigation of the XJ-41-V turbojet-engine compressor with a revised vaned collector was conducted to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal compressors of this type. The original vaned collector was revised by increasing the flow area at the vaned collector entrance. A maximum adiabatic efficiency of 0.81 was obtained at a corrected weight flow of 36.5 pounds per second and a pressure… more
Date: January 23, 1948
Creator: Ginsburg, Ambrose; Creagh, John W. R. & Michel, Donald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Compressor of Xj-41-v Turbojet Engine, 3, Compressor Static-Pressure Rise at Equivalent Compressor Speeds of 5000, 7000, 8000, and 9000 RPM

Description: "At the request of the Air Materiel Command, Army Air Forces, an investigation is being conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The static-pressure variation in the direction of flow through the compressor was presented in reference 1 for an equivalent speed of 8000 rpm. An analysis of these pressure indicated that the maximum-flow limitation of the compressor was caused by separation, which reduced the e… more
Date: July 17, 1947
Creator: Creagh, John W. R. & Ginsburg, Ambrose
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Compressor of XJ-41-V Turbojet Engine, 4, Performance Analysis Over Range of Compressor Speeds from 5000 to 10,000 RPM

Description: "An investigation of the XJ-41-V turbojet-engine compressor was conducted to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal-type compressors. The results of the research conducted on the original compressor indicated the compressor would not meet the desired engine-design air-flow requirements because of an air-flow restriction in the vaned collector. The compressor air-flow choking point occurred n… more
Date: January 22, 1948
Creator: Creagh, John W. R. & Ginsburg, Ambrose
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Compressor of XJ-41-V Turbojet Engine 6 - Analysis of Compressor Flow Choking

Description: "An extended analysis was made of the previously reported performance investigation of the original compressor from the XJ-41-V turbojet engine and a similar compressor revised a to obtain a 33-percent increase in the geometric passage area at the vaned-collector entrance. This analysis was based on the concept of the vaned-collector entrance as the throat section of a nozzle. Because of nonuniform air distribution at the vaned-collector entrance, approximately 90 percent of the available flow … more
Date: March 23, 1948
Creator: Creagh, John W. R. & Ginsburg, Ambrose
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of J-33-A-21 Turbojet-Engine Compressor I - Over-All Performance Characteristics at Equivalent Impeller Speeds from 6000 to 13,400 RPM

Description: "The NACA is investigating a series of J-33 turbojet-engine compressors to determine the over-all and component performances and to improve theories of flow through large centrifugal compressors, The production model J-33-A-21 was operated over a range of inlet temperatures from 80 to -40 F and inlet pressures from 14 to 5 inches mercury absolute for equivalent impeller speeds from 6000 to 13,400 rpm. At the equivalent design speed of 11,500 rpm, the compressor had a peak pressure ratio of 3.98… more
Date: March 30, 1948
Creator: Beede, William L.; Kovach, Karl & Creagh, John W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of Compressor XJ-41-V Turbojet Engine 1 - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM

Description: From Summary: "At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The complete compressor was mounted on a collecting chamber having an annular air-flow passage simulating the burner annulus of the engine and was driven by an electric motor. The compressor was extensively instrumented to determine the overall performance of the compress… more
Date: January 17, 1947
Creator: Ginsburg, Ambrose & Creagh, John W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine 2 - Performance of Revised Compressor at Design Equivalent Speed

Description: From Summary: "The compressor from the XT-46 turbine-propeller engine was revised by removing the last two rows of stator blades and by eliminating the interstage leakage paths described in a previous report. With the revised compressor, the flow choking point shifted upstream into the last rotor-blade row but the maximum weight flow was not increased over that of the original compressor. The flow range of the revised compressor was reduced to about two-thirds that obtained with the original co… more
Date: October 27, 1950
Creator: Creagh, John W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine 1 - Preliminary Investigation at 50-,70-, and 100-Percent Design Equivalent Speed

Description: From Summary: "An investigation is being conducted to determine the performance of the 12-stage axial-flow compressor of the XT-46 turbine-propeller engine. This compressor was designed to produce a pressure ratio of 9 at an adiabatic efficiency of 0.86. The design pressure ratios per stage were considerably greater than any employed in current aircraft gas-turbine engines using this type of compressor. The compressor performance was evaluated at two stations."
Date: May 22, 1950
Creator: Creagh, John W. R. & Sandercock, Donald M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen