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Theoretical comparison of several methods of thrust augmentation for turbojet engines

Description: "A theoretical investigation of tail-pipe burning, water injection at the compressor inlet, combination tail-pipe burning plus water injection, bleedoff, and rocket-assist methods thrust augmentation for turbojet engines was made for an engine representative of those in current use. The effect of augmented liquid ratio on augmented thrust ratio and the effects of altitude and flight Mach number on the performance of various methods were determined. The additional take-off weight involved by the… more
Date: October 27, 1948
Creator: Hall, Eldon W. & Wilcox, E. Clinton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory wind-tunnel investigation at high subsonic and transonic speeds of jet flaps on unswept rectangular wings

Description: Report presenting an investigation in the 7- by 10-foot tunnel by means of the transonic-bump technique to determine the lift augmentation of several jet-flap configurations. The investigation covered a range of Mach numbers. The results indicated that the lift can be increased at any Mach number by blowing downward through a number of closely spaced holes along and near the trailing edge of the wing.
Date: August 1958
Creator: Lockwood, Vernard E. & Vogler, Raymond D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Turbojet thrust augmentation by evaporation of water prior to mechanical compression as determined by use of psychrometric chart

Description: Report presenting an investigation of the thrust augmentation of a turbojet engine resulting from the evaporation of water prior to mechanical compression over a range of flight Mach numbers, altitudes, ambient temperatures, and ambient relative humidities. The amount of thrust augmentation possible from compressor-inlet-air saturation increased with an increase in flight Mach number and decreased as the altitude was increased. Results regarding the psychrometric chart, generalized performance … more
Date: June 1950
Creator: Wilcox, E. Clinton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Jet Propulsion with Special Reference to Thrust Augmenters

Description: An investigation of the possibility of using thrust augmented jets as prime movers was carried out. The augmentation was to be effected by allowing the jet to mix with the surrounding air in the presence of bodies which deflect the air set in motion by the jet. Six augmentation schemes were tested experimentally with compressed air at room temperature at jet speeds up to 1240 feet per second.
Date: January 1933
Creator: Schubauer, G. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests on thrust augmenters for jet propulsion

Description: "This series of tests was undertaken to determine how much the reaction thrust of a jet could be increased by the use of thrust augmenters and thus to give some indication as to the feasibility of jet propulsion for airplanes. The tests were made during the first part of 1927 at the Langley Memorial Aeronautical Laboratory. A compressed air jet was used in connection with a series of annular guides surrounding the jet to act as thrust augmenters. The results show that, although it is possible t… more
Date: September 1932
Creator: Jacobs, Eastman N. & Shoemaker, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analytic Study of Turbojet Engine Thrust Augmentation With Liquid Hydrogen, Pentaborane, Magnesium Slurry, and JP-4 Afterburner Fuels and a 220-Second Impulse Rocket

Description: Memorandum presenting a computation and comparison of the thrust augmentation and accompanying total fuel flow for four afterburner fuels and a rocket. Four turbojet engines burning JP-4 primary fuel and several operating conditions were selected for the analyses.
Date: August 15, 1956
Creator: Morris, James F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Thrust Augmentation of a Turbojet Engine by Water-Alcohol Injection

Description: Memorandum presenting an investigation of thrust augmentation by the injection of water-alcohol mixtures into the compressor inlets of a turbojet engine with a centrifugal-flow-type compressor at altitudes of sea level, 5000 feet, and 10,000 feet. The investigation was made to determine the water-alcohol mixture and the injection rate for optimum thrust augmentation. At a standard NACA altitude of 10,000 feet and an engine speed of 16,000 rpm, the mixture and injection rate for optimum thrust a… more
Date: September 29, 1947
Creator: Ellisman, Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of thrust augmentation of 4000-pound-thrust centrifugal-flow-type turbojet engine by bleedoff

Description: Report presenting an experimental investigation of thrust augmentation by bleedoff using a 4000-pound-thrust turbojet engine at zero flight-speed, sea-level conditions. Secondary combustion air was bled off from combustion chambers and discharged from an exhaust nozzle and water was then injected into the combustion chambers to replace the bleed-off air. Results regarding the thrust characteristics, engine power, and augmented thrust ratio are provided.
Date: July 3, 1950
Creator: Jones, William L. & Bogdan, Louis J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Turbojet-engine thrust augmentation at altitude by combined ammonia injection into the compressor inlet and afterburning

Description: Report presenting an experimental investigation in the altitude test chamber on an axial-flow turbojet engine at transonic flight conditions to determine the magnitude of thrust augmentation and to ascertain the operational characteristics of a combined augmentation system. Results regarding the augmented engine performance, influence of coolant on afterburner combustion, performance losses, and operational problems are provided.
Date: February 12, 1953
Creator: Useller, James W.; Harp, James L., Jr. & Fenn, David B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Sea-Level Static Investigation of a Short Afterburner

Description: Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.
Date: May 11, 1954
Creator: Harp, James L., Jr.; Mallett, William E. & Shillito, Thomas B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical Comparison of Several Methods of Thrust Augmentation for Turbojet Engines

Description: "A theoretical investigation has been made of various methods of thrust augmentation for turbojet engines. The method investigated were tail-pipe burning, water injection at the compressor inlet, a combination of tail-pipe burning and water injection, bleedoff in conjunction with water injection at the compressor inlet, and rocket assist. The effect of ratio of augmented-to-normal total liquid consumption, flight conditions, and design compressor pressure ratio on the augmentation produced by e… more
Date: October 27, 1948
Creator: Hall, Eldon W. & Wilcox, E. Clinton
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Thrust Augmentation of a 1600-Pound Thrust Centrifugal-Flow-Type Turbojet Engine by Injection of Refrigerants at Compressor Inlets

Description: Investigations were conducted to determine effectiveness of refrigerants in increasing thrust of turbojet engines. Mixtures of water an alcohol were injected for a range of total flows up to 2.2 lb/sec. Kerosene was injected into inlets covering a range of injected flows up to approximately 30% of normal engine fuel flow. Injection of 2.0 lb/sec of water alone produced an increase in thrust of 35.8% of rate engine conditions and kerosene produced a negligible increase in thrust. Carbon dioxide … more
Date: August 25, 1947
Creator: Jones, William L. & Dowman, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Thrust augmentation of a turbojet engine by the introduction of liquid ammonia into the compressor inlet

Description: Report presenting an experimental investigation to determine the thrust augmentation possible by the injection of liquid ammonia into the compressor inlet of an axial-flow-type turbojet engine. Results regarding the selection of coolant, cooling with liquid ammonia, engine performance, and operating experience are provided.
Date: August 13, 1952
Creator: Harp, James L., Jr.; Useller, James W. & Auble, Carmon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of tail-pipe-burner design variables

Description: Report summarizing several experimental tail-pipe-burner investigations to indicate the effects of tail-pipe-burner design variables on the performance and operating characteristics. Most of the configurations were investigated over a wide range of altitudes and flight Mach numbers. The results indicate the desirable design features of a tail-pipe burner that will operate with high combustion efficiency and exhaust-gas temperature up to an altitude of approximately 50,000 feet.
Date: March 5, 1951
Creator: Fleming, W. A.; Conrad, E. William & Young, W. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical analysis of various thrust-augmentation cycles for turbojet engines

Description: Report presenting the results of analytical studies of tail-pipe-burning, water-injection, and bleedoff methods of thrust augmentation that provide an insight into the operating characteristics and summarize the performance that may be obtained when applied to a typical turbojet engine. Results regarding bleedoff and water-injection rates, performance of the primary engine, and performance of the secondary engine, performance of the complete engine are provided.
Date: May 1950
Creator: Lundin, Bruce T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Exploratory study of ground proximity effects on thrust of annular and circular nozzles

Description: The proximity of the ground to an annular nozzle can result in thrust augmentation of up to 50 percent. The magnitude of thrust augmentation was a function of ground-to-nozzle distance, nozzle configuration, and nozzle pressure ratio. With a conventional circular nozzle a thrust reduction of 15 to 40 percent due to ground effect was obtained. The degree of thrust reduction was primarily a function of nozzle pressure ratio and ground-to-nozzle distance.
Date: April 1957
Creator: von Glahn, Uwe H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical investigation of thrust augmentation of turbojet engines by tail-pipe burning

Description: Report presenting a theoretical analysis of thrust augment of turbojet engines by tail-pipe burning and charts from which the thrust augmentation produced may be evaluated from the normal engine data and performance of the tail-pipe burner. Results regarding general curves and illustrative curves are provided.
Date: January 28, 1947
Creator: Bohanon, H. R. & Wilcox, E. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of thrust augmentation of a turbojet engine at zero ram by means of tail-pipe burning

Description: Report presenting an investigation of the performance of a turbojet engine equipped with a tail-pipe burner at zero ram over a range of rotor speeds and tail-pipe-burner fuel flows. A thrust augmentation of 40 percent was obtained at zero ram for a tail-pipe-burner fuel-air ratio of 0.043 or a total fuel-air ratio of 0.056. Results with an engine with standard tail pipe, engine with tail pipe burner and no afterburning, and engine with tail pipe burner and afterburning are provided.
Date: January 6, 1947
Creator: Lundin, Bruce T.; Dowman, Harry W. & Gabriel, David S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers

Description: Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.
Date: April 13, 1950
Creator: Gabriel, David S.; Dowman, Harry W. & Jones, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical analysis of various thrust-augmentation cycles for turbojet engines

Description: "The results of analytical studies of tail-pipe-burning, water-injection, and bleedoff methods of thrust augmentation are presented that provide an insight into the operating characteristics of these augmentation methods and summarizes the performance that may be obtained when applied to a typical turbojet engine. A brief description of the principles of operation of each augmentation method is given, together with curves that illustrate the effects of the principal design and operating variabl… more
Date: September 2, 1949
Creator: Lundin, Bruce T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

“A Metaphor for the Impossibility of Togetherness”: Expansion Processes in Gubaidulina’s First String Quartet

Description: This thesis illustrates how I hear processes of expansion organizing musical materials in the First String Quartet. By employing a flexible approach to expansion and developing models of wedge and additive expansions beyond the bounds of specific voice-leading or rhythmic augmentation procedures, expansion processes can be understood in each of the varied episodes of the quartet. Gubaidulina’s use of expansion processes, embodied organically in pitch, rhythm, form, and physical space, unifies t… more
Date: August 2012
Creator: Stroud, Cara
Item Type: Refine your search to only Thesis or Dissertation
Partner: UNT Libraries
open access

A study of injection processes for liquid oxygen and gaseous hydrogen in a 200-pound-thrust rocket engine

Description: Characteristic velocities of six single-element injectors that separately varied propellant spreading and mixing were measured over a range of oxidant-fuel weight ratios of 2 to 7. Hydrogen inlet temperature was -320 degrees F. Injectors that both mixed and spread the propellants had the highest characteristic-velocity efficiency. Spreading of either propellant produced about the same increment efficiency. The increase in efficiency due to mixing was relatively small. With similar injectors, ox… more
Date: January 9, 1957
Creator: Auble, Carmon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of thrust augmentation using water-alcohol injection on a 5200-pound-thrust axial-flow-type turbojet engine at static sea-level conditions

Description: Report presenting an investigation to evaluate the thrust augmentation available with various types of water-alcohol injection system on a 5200-pound-thrust axial-flow-type turbojet engine at sea-level, zero-ram conditions. Results regarding engine performance and operational characteristics are provided.
Date: September 4, 1952
Creator: Boman, David S. & Mallett, William E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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