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Altitude-wind-tunnel investigation of operational characteristics of J47 turbojet engine

Description: Report presenting an investigation in the altitude wind tunnel to determine the operational characteristics of a J47 turbojet engine over a wide range of simulated flight conditions at a range of altitudes. Operational characteristics investigated include operating range, starting, altitude and airspeed compensation of the fuel regulator, and acceleration.
Date: August 3, 1950
Creator: Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Experimental results of an investigation of two methods of inflight thrust measurement applicable to afterburning turbojet engines with ejectors

Description: Report presenting an investigation in an altitude test chamber using a turbojet engine equipped with an afterburner and ejector to compare directly two techniques of determining thrust that are both applicable to flight installations. One method uses a swinging uncooled rake at the ejector outlet while the other requires extensive instrumentation to measure the momentum forces of systems and the force on the internal surface of the ejector nozzle. Results regarding the swinging-rake technique and internal-pressure technique are provided.
Date: May 2, 1958
Creator: Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Preliminary Altitude Performance Characteristics of the J57-P-1 Turbojet Engine with Fixed-Area Exhaust Nozzle

Description: An investigation to determine the altitude performance of the J57-P-1 turbojet engine and components was conducted at the NACA Lewis altitude wind tunnel. Data were obtained over a corrected inboard rotor speed range from 56 to 106 percent of rated speed, with intercompressor bleeds both open and closed, at altitudes from 15,000 to 50,000 feet and at a flight Mach number of 0.81. The corresponding range of Reynolds number indices was from 0.858 to 0.213. All data presented were obtained with a fixed-area exhaust nozzle sized according to the manufacturer's specification. Over-all engine performance parameters are presented as functions of inboard rotor speed corrected on the basis of engine inlet temperature. Component parameters are presented as functions of their respective corrected rotor speeds. A tabulation of all performance data is included in addition to the graphical presentation. Corrected net thrust is unusually sensitive to changes in corrected inboard rotor speed in the high speed region. A change of 1 percent in speed, at sated speed, produced a change of 6 percent in corrected net thrust . At rated engine speed, increasing the altitude from 15,000 to 50,000 feet at a constant flight Mach number of 0.81 increased the specific fuel consumption 13 percent but did not affect corrected net thrust.
Date: April 30, 1954
Creator: Bloomer, Harry E. & Miller, Robert R.
Partner: UNT Libraries Government Documents Department

Preliminary internal performance data for a variable-ejector assembly on the XJ79-GE-1 turbojet engine, 1: Nonafterburning configurations

Description: Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in a representative nonafterburning position. Jet-thrust and air-handling data were obtained in quiescent air for 11 selected ejector configurations over a wide range of operation. Additional data, at specific operating conditions, were obtained which indicate the ejector diameter ratio for peak jet-thrust performance. The experimental ejector data are presented in both graphical and tabulated form.
Date: August 30, 1956
Creator: Greathouse, William K. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, Part 5, Performance and Windmilling Drag Characteristics

Description: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet" (p. 1).
Date: August 23, 1948
Creator: Meyer, Carl L. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Experimental investigation of several afterburner configurations on a J79 turbojet engine

Description: Report presenting an investigation in the altitude test chamber to evaluate several afterburner configurations on the XJ79 engine. Data were obtained from nine configurations which show the effect on burner performance of increased burner diameter and modifications to the flameholder, fuel system, and flow swirl.
Date: September 23, 1957
Creator: Bloomer, Harry E. & Campbell, Carl E.
Partner: UNT Libraries Government Documents Department

Investigation of altitude starting and acceleration characteristics of J47 turbojet engine

Description: An investigation was conducted on an axial-flow-compressor type turbojet engine in the NACA Lewis altitude wind tunnel to determine the operational characteristics of several ignition systems, cross-fire tube configurations and fuel systems over a range of simulated flight conditions. The opposite-polarity-type spark plug provided the most satisfactory ignition. Increasing the cross-fire-tube diameter improved intercombustor flame propagation. At high windmilling speeds, accelerations to approximately 6200 rpm could be made at a preset constant throttle position. The use of a variable-area nozzle reduced acceleration time.
Date: January 10, 1951
Creator: Golladay, Richard L. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine

Description: An investigation of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel with a full-scale turbojet engine and an 29-inch-diameter tail-pipe burner. Effects of fuel distribution and number and arrangement of stages on performance and operational characteristics of several fuel-cooled flame holders are presented and discussed. Operation with a three-stage flame holder having the large stage upstream was the most efficient. Combustion efficiency was slightly increased at high altitudes by injecting fuel upstream of the flame holder.
Date: April 28, 1950
Creator: Golladay, Richard L. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Preliminary Internal Performance Data for a Variable-Ejector Assembly on the XJ79-GE-1 Turbojet Engine, 2, Afterburning Configurations

Description: Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in two representative after-burning positions. Jet-thrust and air-handling data were obtained in quiescent air for 4 selected ejector configurations over a wide range of secondary to primary airflow ratios and primary-nozzle pressure ratios. The experimental ejector data are presented in both graphical and tabulated form.
Date: July 30, 1957
Creator: Bloomer, Harry E. & Groesbeck, Donald E.
Partner: UNT Libraries Government Documents Department

Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine. 5 - Performance of Modified Engine

Description: From Summary: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance characteristics of a modified X24C-4B turbojet engine over a range of simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.25 to 1.07, and engine speeds from 4000 to 12,500 rpm. The engine was modified by the manufacturer to improve the velocity and temperature profiles within the engine. Performance data are graphically presented to show the effect of altitude at a flight Mach number of 0.25 and the effect of flight Mach number at an altitude of 25,000 feet."
Date: 1947
Creator: Prince, William R. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Altitude Performance and Operational Characteristics of YJ71-A-7 Turbojet Engine

Description: Altitude performance of a YJ71-A-7 turbojet engine, with afterburner inoperative, was determined in the NACA Lewis altitude wind tunnel over a wide range of flight conditions. Engine speed and exhaust-nozzle area were controlled independently during this investigation. The variation of corrected values of air flow, net thrust, and fuel flow with corrected engine speed was not defined by a single curve with changes in altitude at given flight Mach number. Changes in altitude had very little effect on minimum specific fuel consumption at altitudes up to 45,000 feet. There is one exhaust-nozzle schedule that is nearly optimum for all flight conditions. Performance calculated from pumping characteristics agreed with experimental values and can therefore be used to extend engine performance data.
Date: June 16, 1953
Creator: Smith, Ivan D.; Leonard, Charles V. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Altitude investigation of XJ34-WE-32 engine performance without electronic control

Description: From Introduction: "As a part of the comprehensive investigation of the XJ34-WE-32 engine conducted in the NACA Lewis altitude wind tunnel, the over-all-performance was determined over a range of altitudes and flight Mach numbers. Other phases of the investigation are reported in reference 1. The results are given in tables and also in graphical form to show the trends of engine performance associated with changes of altitude, flight Mach number, and exhaust-nozzle area."
Date: May 29, 1953
Creator: Bloomer, Harry E.; Walker, William J. & Pantages, George L.
Partner: UNT Libraries Government Documents Department

Performance of a turbojet engine with adjustable first-stage turbine stator and variable-area exhaust nozzle

Description: The performance of a turbojet engine with a two-stage turbine, an adjustable first-stage turbine stator, and a variable-area exhaust nozzle was investigated at selected constant engine speeds and two simulated flight conditions. For the particular component characteristics of the engine investigated, little improvement in thrust levels of interest by use of an adjustable rather than an optimum fixed first-stage turbine stator.
Date: August 14, 1953
Creator: Meyer, Carl L.; Smith, Ivan D. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Evaluation of an automatic inlet-pressure control valve for study of transient engine performance characteristics

Description: Report presenting an evaluation of data obtained with an automatic constant inlet-pressure control valve designed to facilitate the study of transient engine performance characteristics in the altitude wind tunnel. The engine characteristics obtained by use of the pressure valve were compared with those obtained with a bellmouth inlet operating in simulated free-stream conditions.
Date: April 6, 1956
Creator: Wallner, Lewis E.; Lubick, Robert J. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Preliminary Results of Altitude-Wind-Tunnel Investigation of X24C-4B Turbojet Engine 2 - Engine Performance

Description: An investigation was conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance characteristics of the X24C-4B turbojet engine over a range of simulated altitudes from 5000 to 45,000 feet,simulated flight Mach numbers from 0 to 1.08, and engine speeds from 4000 to 12,500 rpm. Performance data are presented to show graphically the effects of altitude at a flight Mach number of 0.25 and of flight Mach number at an altitude of 25,000 feet. The performance data are generalized to show the applicability of methods used to determine performance at any altitude from data obtained at a given altitude. A complete tabulation of performance data, as well as lubrication- and fuel- system data, is presented.
Date: December 1948
Creator: Meyer, Carl L. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Preliminary performance data for the J57-P-1 turbojet engine at altitudes up to 65,000 feet

Description: Report presenting an investigation to determine the high altitude performance of the J57-P-1 turbojet engine and components conducted at the NACA Lewis altitude wind tunnel. Four conditions were tested: engine operation with both the compressor bleed ports closed, with the large compressor bleed port open, with both compressor bleed ports open, and normal engine operation with the automatic control.
Date: June 15, 1954
Creator: Miller, Robert R. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department

Altitude operational characteristics of a prototype model of the J47D (RX1-1 and RX1-3) turbojet engines with integrated electronic control

Description: Report presenting an investigation of the altitude operational characteristics of a prototype model of the J47D turbojet engines, which includes an afterburner, a variable-area exhaust nozzle, and an integrated electronic control in an altitude wind tunnel. Results regarding compressor stall, compressor unstall, combustor blow-out during acceleration, stall and blow-out protection, acceleration characteristics, deceleration characteristics, and altitude starting characteristics, afterburner operational characteristics are provided.
Date: January 8, 1952
Creator: Bloomer, Harry E.; Conrad, E. William & Sobolewski, Adam E.
Partner: UNT Libraries Government Documents Department