Topics: DTIC Archive, Lynch, J. F., BATTELLE MEMORIAL INST COLUMBUS OH, *COMBUSTION CHAMBER LINERS,...
X-ray diffraction analysis of the Inconel scale on combustion tube inner liners revealed that it is composed of nickel oxide, the major component, and lesser amounts of chromium oxide and iron oxide. Metallographic examination demonstrated that heavy scale is associated with precipitation, possibly carbides at the grain boundaries, a fact which can explain intergranular corrosion of scaled Inconel in acid solutions. Inconel scale could not be taken off in neutral or alkaline solvents but...
Topics: DTIC Archive, BRYAN, G. M., NORTHROP AIRCRAFT INC HAWTHORNE CA, *CLEANING COMPOUNDS, *TURBOJET...
The effects of fuel and combustion variables on liner temperatures and flame radiation of the J79 combustion chamber were investigated. The operating conditions were extended to higher in let air temperature to show the effect of operation with advanced jet engines. Liner temperatures and flame radiation intensity in a J79 combustion chamber are functions of both the luminometer number and the hydrogen content of the fuel. As liner temperature tends to level out above a luminometer number of...
Topics: DTIC Archive, McClelland, C C, NAVAL AIR ENGINEERING CENTER LAKEHURST NJ AERONAUTICAL ENGINE LAB,...
Presented are the results of a program to de velop, evaluate, and qualify a Kel-F liner for the oxidizer inlet passage of the Mark 4 sustainer turbopump, and to measure turbopump shaft deflection during operation.
Topics: DTIC Archive, ROCKETDYNE CANOGA PARK CA, *PUMPS, *SURFACE TO SURFACE MISSILES, *COMBUSTION CHAMBER...
The objective of this project is to develop a reliable thermal barrier capable of surface temperature operation above 3300 F for use on regeneratively-cooled thrust chambers employing Aerozine-50/N2O4 propellant. Thermal barrier film-coating is a technique for improving liquid rocket engine performance by reducing film-cooling flow rates. During this period the YLR91 AJ-5 thrust chamber has been shipped to test area C to undergo three tests at the planned 17% fuel film cooling flow rate for...
Topics: DTIC Archive, AEROJET-GENERAL CORP SACRAMENTO CA, *FILM COOLING, *COMBUSTION CHAMBER LINERS,...
The report describes an analytical and experimental study of advanced, small, high-temperature combustors. This volume describes the third and final phase of this program which included the design and performance verification tests of a full-scale combustion system. The objectives of the 32- month program were to develop and validate an analytical design technique for small, high-temperature-rise, low-airflow combustors and related components, and to define the limitations associated with these...
Topics: DTIC Archive, Wood, Michael P, AIRESEARCH MFG CO OF ARIZONA PHOENIX, *COMBUSTORS, *GAS TURBINES,...
The development of flexible, solid propellant rocket motor case insulation is discussed. Data are presented for insulation based primarily on butadiene/styrene and butadiene/acrylonitrile copolymers. The oxyacetylene torch test currently being standardized by the Flame Ablation Test Group of Section III-L of ASTM Committee D-20 was the principle screening tool used in the study. Vulcanizates were compounded using a variety of fillers and filler combinations including salts, resins and fr, heat...
Topics: DTIC Archive, Ofner, R E, ROCK ISLAND ARSENAL IL, *ROCKET ENGINE CASES, *COMBUSTION CHAMBER LINERS,...
This paper presents an analytical study of the axial shear vibrations of a long hollow cylinder that is subjected to time dependent body forces in the axial direction. The outer surface of the cylinder is bonded to a rigid case, and the inner radius increases monotonically with time. An expression is determined for the shear stress at the bond-interface. It is shown that the frequency of the shear-bond stress increases, and that its amplitude decreases towards burnout time. The shear stress is...
Topics: DTIC Archive, NORTHWESTERN UNIV EVANSTON IL STRUCTURAL MECHANICS LAB, *SOLID PROPELLANT ROCKET...
It is shown that it is possible to have a circumferential turbine inlet temperature variation in excess of 90 C in a correctly assembled T56 Series III engine. A significant part of this variation is due to differences in airflow into the liner caused by the variations in airflow area associated with manufacturing tolerances. A simple technique is described that will enable matched sets of liners to be selected to build engines and thus avoid excessive temperature maldistributions. Preliminary...
Topics: DTIC Archive, Skidmore, F W, AERONAUTICAL RESEARCH LABS MELBOURNE (AUSTRALIA), *COMBUSTION CHAMBER...
Topics: DTIC Archive, NORGREN, CARL T., CHILDS, J. H., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION...
The report presents the results of a program that was conducted to provide design information applicable to future Army aircraft relative to crash sensors, ignition-source suppression systems, and circuitry for the automatic activation of the suppression systems. The program involved a comprehensive literature search, the development of requirements for the initiating subsystem of the overall ignition source control system, and the consideration and comparison of several illustrative activating...
Topics: DTIC Archive, Drummond, John K, DYNAMIC SCIENCE INC PHOENIX AZ AVSER FACILITY, *AIRCRAFT FIRES,...
The reaction between high-density tungsten and H2O vapor has been studied from 1900 to 2800 K in the induction-heated stagnation-flow reactor at H2O partial pressures from 25 to 155 torr. The reaction is linear with time at all pressures and temperatures studied. All isobars show apparent activation energies that decrease with temperature, indicating that gas-phase diffusion limits the reaction rates at the higher temperature. Furthermore, the rates are dependent on the gas flow rate at the...
Topics: DTIC Archive, Aspinall, S R, UNION CARBIDE RESEARCH INST TARRYTOWN NY, *CORROSION INHIBITION,...
Prototype melt pour explosive loading equipment was procured and installed in support of load, assemble, and pack modernization program at various Army Ammunition Plants around the United States. This equipment uses a new and different approach to control the cooling process of melt poured munitions that is currently not used by facilities within the United States industrial base. The equipment purchased consists of a probing unit to control the cooling of molten explosive filled projectiles,...
Topics: DTIC Archive, Spicer, Daniel, ARMY ARMAMENT RESEARCH DEVELOPMENT AND ENGINEERING CENTER PICATINNY...
Design studies and an experimental test program were conducted to provide basic technology and preliminary flight-weight designs for a small (2-5 lb/sec total engine airflow) high temperature rise combustor with a 3000F exit temperature, as a first step towards demonstration in an advanced engine. Tests were conducted to evaluate the combustor design parameters developed in the initial design study phase of the program pertaining to liner cooling techniques, primary-diluent air mixing, fuel...
Topics: DTIC Archive, Andersen, Richard H, CURTISS-WRIGHT CORP WOOD-RIDGE NJ, *COMBUSTION CHAMBERS, *GAS...
Developing stress intensity solutions for thermal strain inducing cracking in hot spots is the chief goal of this research. Using finite element analysis (FEA) to model the stress state and crack stress intensities resulting from thermal gradients, a model is needed to represent and predict this cracking and eventual crack arrest in combustor liners in turbine engines. In determining the number of cycles until the crack arrests, the model estimates the number of cycles within 5 when compared to...
Topics: DTIC Archive, Rhymer, Donald W, GEORGIA TECH RESEARCH CORP ATLANTA, *FINITE ELEMENT ANALYSIS,...
The objective of this eighteen-month program were to further develop two low-emission combustors-the prechamber combustor and the modified conventional combustor to install them in a Detroit Diesel Allison Model 250-C20B engine, and to evaluate their performance in an engine environment. The combustors were to retain the 50% overall reduction in gas turbine mass emissions with no increase in any individual pollutant when tested over a typical Army light observation helicopter (LOH) duty cycle.
Topics: DTIC Archive, Troth,D L, GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV,...
A study way made to evaluate the capabilities of nondestructive test methods best suited to the detection of critical defects in large solid- propellant motors. A critical defect may be defined as an imperfection in a motor which will impair the success of an assigned mission. Two general types of defects are classified as critical regardless of their size. These are a case- insulation unbond exposed to propellant gases, and any defect which tends to propagate without limit. Analytical studies...
Topics: DTIC Archive, Harris, Charles, UNITED TECHNOLOGY CENTER SUNNYVALE CA, *SOLID PROPELLANT ROCKET...
Two shrink-fitted, compound sleeve assemblies have been designed to supply required support for use of solid ceramic, ceramic-coated metal, and elevated temperature metal extrusion liners, at stem pressures of 180,000 psi. Liner and sleeve machining and shrink-fitting data are supplied. The first assembly develops required support for ceramic liners and other materials which have high compressive strength and low tensile strength. The second assembly provides required support for materials...
Topics: DTIC Archive, Spachner, S A, ARMOUR RESEARCH FOUNDATION CHICAGO IL, *MANUFACTURING, *PROCESSING,...
The report describes an analytical and experimental study of advanced, small, high-temperature combustors. The objectives of the 32-month program were (a) to develop and validate an analytical design technique for small, high-temperature-rise, low-airflow combustors and related components, and (b) to define the limitations associated with these small combustors and related components and the effects of these limitations on the cycle and the configuration of advanced-technology engines....
Topics: DTIC Archive, Hunter, S C, AIRESEARCH MFG CO OF ARIZONA PHOENIX, *COMBUSTORS, *GAS TURBINES,...
A novel low temperature chemical vapor deposition (CVD) process has been developed for the co-deposition of Ir and Re. The codeposit was dense and consisted of both Re and Ir with crystallites ranging from 30 A and 1000 A in size. A reactive vapor phase was formed between 205 deg C and 220 deg C, and deposition was carried out onto quartz, graphite and rhenium substrates at between 410 deg C and 425 deg C. Changes to the processing parameters resulted in an increase in the deposition rate up to...
Topics: DTIC Archive, He, Shanjin, CERAMIC COMPOSITES INC MILLERSVILLE MD, *CHEMICAL VAPOR DEPOSITION,...
As part of the Advanced Lightweight Chamber and Nozzle (ALCAN) program, over 50 hot fire tests were run in the Mojave desert over a wide range of pressures and mixture ratios in February and March. These proof-of-concept engines are designed to perhaps one day produce a booster-sized engine weighing half as much as the SSME, with increased performance. The first round of tests, conducted at Polaris Propulsion's Mojave Test Area, were intended to prove the viability of the concept, according to...
Topics: DTIC Archive, Unkeless, Susie, BOEING NORTH AMERICAN INC CANOGA PARK CA ROCKETDYNE DIV, *COMBUSTION...
Identify, demonstrate, and develop a method of forming a liquid rocket engine thrust chamber structural jacket that is less expensive than electrodeposition and capable of applying nanostructured materials. Document and demonstrate cost and/or weight advantages over conventional electrodeposition of nickel.
Topics: DTIC Archive, Shelley, J S, AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST,...
Computations based upon the geometry of a rocket motor and the x-ray absorption coefficients of the materials indicated the feasibility of detecting interface separations in rocket motors even when the radial dimension of the unbonded area is as small as 0.001 in. These conclusions were amply verified by experiments. Tangential radiography of interface areas in rocket motors thus provides a basis upon which to develop an in-process and end-product inspection.
Topics: DTIC Archive, BUJES, J I, BUREAU OF NAVAL WEAPONS WASHINGTON DC, *BONDING, *COMBUSTION CHAMBER...
Contents: Coated metajlic thrust chambers; Ex pandable nozzles; Combustion instability scaling concepts; and Ablative thrust chambers.
Topics: DTIC Archive, AEROJET-GENERAL CORP SACRAMENTO CA, *ROCKET NOZZLES, *COMBUSTION CHAMBER LINERS,...
Storage of H2O2 in sealed storage containers was studied. Four grades of Becco H2O2 were evaluated: Commercial 90% by weight H2O2, propulsion 90% by weight H2O2, Commercial 98% by weight H2O2, and propulsion 98% by weight H2O2, in 1 gal capacity TFE Teflon bladders contained in mild steel test tanks at 70-72 F for 5 months, 120 F for 7 days, and 165 F for 72 hr. The bladders were not as compatible as desired due to bleaching and crack development experienced with this dispersion-type Teflon....
Topics: DTIC Archive, McCormick, J C, FOOD MACHINERY AND CHEMICAL CORP BUFFALO NY BECCO CHEMICAL DIV,...
An important Air Force objective is to develop technology to allow the utilization of aviation fuels with a broader range of properties including lower hydrogen content and higher aromaticity. The objectives of this program are to develop a data base and modeling capabilities to relate vaporization, pyrolysis, and soot formation to the properties of the fuel, the atomizer and combustion conditions. The benefits of reduced soot in jet engines are significant: increased life, improved reliability...
Topics: DTIC Archive, Solomon, Peter R., ADVANCED FUEL RESEARCH INC EAST HARTFORD CT, *COMBUSTION,...
A nomogram called Cavitation Damage Intensity Estimator is presented for estimating cavitation damage intensities of field installations. This simple approach is based on an earlier definition of cavitation damage intensity as the power absorbed per unit area of the eroded material. Using this estimator and the data published for field installations, the damage intensity is estimated for ships' appendages, ships' propellers, valves, Diesel engine cylinder liners, hydraulic turbine runners and...
Topics: DTIC Archive, Thiruvengadam, A, HYDRONAUTICS INC LAUREL MD, *HYDRODYNAMICS, *STRUCTURAL COMPONENTS,...
As part of a study of the chemical corrosion of rocket liner materials, many computations were made of the chemical equilibria between rocket liner materials and corrosive gaseous or condensed materials. As a convenience to readers, who may be interested in the thermodynamic properties for their own sake, all the properties developed during the contract period are collected in this single volume. For each species considered, the literature was searched to uncover whatever data were available;...
Topics: DTIC Archive, Sprague, R W, PHILCO NEWPORT BEACH CA AERONUTRONIC DIV, *CORROSION, *THERMODYNAMICS,...
Absorbing liners or 'screech' liners are commonly used in the augmentors currently being proposed and developed can experience low frequency instabilities for which liners of conventional design are an impractical solution because of the unacceptably large volumes required for the linear resonator cavity. The objective of this program was to develop practical augmentor acoustic devices for controlling low frequency combustion instabilities. Analysis, supported by cold flow impedance...
Topics: DTIC Archive, Garrison, Gary D, PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FL FLORIDA RESEARCH AND...
A preliminary investigation limited to stress freezing materials was undertaken in order to develop a test method for estimating the stress intensity factor (SIF) distribution along the border of cracks in the bond line of a bi-material specimen. It was desired to measure the influence of residual stress and mixed mode effects for such specimens. A single edge notched specimen was selected, and a test procedure was devised for isolating the residual stress effect at the bond line for Mode I....
Topics: DTIC Archive, Smith, C. W., VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF ENGINEERING...
An investigation was made to determine experimentally the effect of film-cooling a rocket engine nozzle with a reactant gas. Coolant quantities, injection velocities and angles, and axial injection location were varied to determine the conditions under which adequate film cooling could be achieved. Five basic coolant configurations consisting of three De Laval type nozzles and three coolant chamber liners provided coolant injection at the nozzle entrance and/or near the nozzle throat....
Topics: DTIC Archive, Alser, Donald J, AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH, *ROCKET NOZZLES,...
Convective heat transfer is important for maintaining life and reliability of the main combustion chamber in liquid rocket engines. Enhancing the regenerative cooling circuit's ability to maintain wall temperature with minimal pressure losses improves engine life and has the potential to reduce the turbopump output pressure. High aspect ratio coolant channels have been shown to reduce wall temperature with little pressure increase. Additionally, rocket engine cooling circuits are curved and the...
Topics: DTIC Archive, AIR FORCE RESEARCH LAB EDWARDS AFB CA LIQUID ROCKET ENGINES BRANCH (AFRL/PRSE),...
Thiokol Chemical Corporation/Wasatch Division uses MAPO in the production of UF-2121 liner. Thiokol changed MAPO vendors and, therefore, qualification of the new source MAPO was required. Thiokol prepared specimens from the new source and also specimens from the original source which are to be used as the control material in the 10 year surveillance testing program. The specimens were transferred to Ogden ALC for testing and reporting of the data obtained. This report includes the test results...
Topics: DTIC Archive, Thompson, John A., OGDEN AIR LOGISTICS CENTER HILL AFB UT PROPELLANT ANALYSIS LAB,...
Successful high energy rate forging of unwrought refractory materials is highly dependent upon the forging configuration and die design. Good forgings are possible when working stresses are compressive in nature. Tensile and shear stresses during forging generally result in fracturing of the billet if the refractory metals have received little or no plastic work. Data for forging conditions and results of metallurgical examinations are presented.
Topics: DTIC Archive, Palsulich, J M, WESTERN GEAR CORP LYNWOOD CA, *FORGING, *TUNGSTEN, *HIGH ENERGY RATE...
Topics: DTIC Archive, ANDERSON, S E, ROHM AND HAAS CO HUNTSVILLE AL, *COMBUSTION CHAMBER LINERS, ALKANES,...
Combustor research relating to the development of fuel efficient small gas turbine engines capable of meeting future commercial and military aviation needs is currently underway at NASA Lewis. As part of this combustor research, a basic reverse-flow combustor has been used to investigate advanced liner wall cooling techniques. Liner temperature, performance, and exhaust emissions of the experimental combustor utilizing compliant metal/ceramic liners were determined and compared with three...
Topics: DTIC Archive, Acosta, Waldo A., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS...
Thiokol Chemical Corporation/Wasatch Division used MAPO in the production of UF-2121 liner. Thiokol changed MAPO vendors and, therefore, qualification of the new source MAPO was required. Thiokol prepared specimens from the new source and also specimens from the original source which were used as the control material in the qualification testing. The specimens were transferred to Ogden ALC for testing and reporting of the data obtained. This report includes the test results for the first,...
Topics: DTIC Archive, Thompson,John A, OGDEN AIR LOGISTICS CENTER HILL AFB UTAH PROPELLANT LAB SECTION,...
This report describes the 37-month program for the development of analytical models applicable to small gas turbine combustors. Six analytical models were developed and validated with element tests. The inputs and correlations obtained from the element tests along with basic developments to the models and the numerics provided analytical models when used in judicious conjunction with traditional empirical design and development of two different advanced reverse flow annular combustor concepts....
Topics: DTIC Archive, Bruce, T. W., AIRESEARCH MFG CO OF ARIZONA PHOENIX, *MATHEMATICAL MODELS,...
The objective of the study was to develop criteria for use in the design of aircraft gas turbine combustion chambers to minimize nitrogen oxide emissions. The approach adopted involved the development of a mathematical model of NOx emission from aircraft engine combustors; a parametric analysis, using the model, to determine the sensitivity of NOx emissions to variations of model parameters and engine design variables; evaluation of critical model parameters by means of experimental...
Topics: DTIC Archive, Fletcher, Ronald S, NORTHERN RESEARCH AND ENGINEERING CORP WOBURN MA, *AIR POLLUTION,...
Advanced commercial and military gas turbine engines may operate at combustor outlet temperatures in excess of 1920 K (3000 K). At these temperatures combustors liners experience extreme convective and radiative heat fluxes. The ability of plasma sprayed ceramic coating to reduce liner metal temperature has been recognized. However, the brittleness of the ceramic layer and the difference in thermal expansion with the metal substrate has caused cracking, spalling and some separation of the...
Topics: DTIC Archive, Ercegovic,D B, NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS...
Topics: DTIC Archive, Hanna, Stephen G, AIR FORCE RESEARCH LAB EDWARDS AFB CA MOTOR BRANCH, *BOOSTER ROCKET...
The flexibilization of epoxy, melamine, phenolic, urethane, and furan resins for use as thermal insulation binders in end-burning, solid-propellant rocket motors is described. The effect of aging on the mechanical properties of two externally plasticized epoxy resins was determined. For several resins, asbestos fibers, potassium oxalate, and magnesium carbonate fillers were evaluated in the oxyacetylene-torch test and static-motor firings. The char rates (from motor firings) and densities for...
Topics: DTIC Archive, Vasileff, N, ATLANTIC RESEARCH CORP ALEXANDRIA VA, *ROCKET ENGINES, *COMBUSTION...
A detailed experimental investigation was made of time-resolved pressure histories at the focus of combustion-driven implosions in the UTIAS 20 cm diam Implosion Chamber. Gaseous mixtures of stoichiometric hydrogen and oxygen were used in the initial pressure range 1.7 atm (25 psi) to 6.8 atm (100 psi). The gaseous mixtures were detonated using exploding wires. Extended records from a PCB 119M08, 6.3 mm diam piezoelectric pressure transducer gave detailed (averaged) pressure-time histories of...
Topics: DTIC Archive, Vasudevan,B, TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES, *COMBUSTION,...
A mathematical design model has been developed for the prediction of insulation requirements in the aft-closure of a solid propellant rocket motor. This model and the associated calculation technique represent only a first approximation to the exact solution of a problem concerned with various complex phenomena. The behavior of ablative elastomeric insulation materials in such an application is considered. The choice of the assumptions used to calculate the forced convective and radiative heat...
Topics: DTIC Archive, KUBY, W C , Jr, PHILCO NEWPORT BEACH CA AERONUTRONIC DIV, *ROCKET ENGINES,...
Topics: DTIC Archive, WALTON, T R, ATLANTIC RESEARCH CORP ALEXANDRIA VA, *COMBUSTION CHAMBER LINERS, *HEAT...
These Conference Proceedings contain 39 papers presented at the 50th Meeting of the AGARD Propulsion and Energetics Panel, held at Ankara, Turkey on 19-23 September 1977. The papers were grouped into eight sessions on motivation and survey, turbine cooling techniques, combustors, afterburners and nozzles, materials and coatings, mechanical problems, effect of cooling on aerodynamic performance, measuring techniques, and on prediction methods. The purpose of this meeting was to review and...
Topics: DTIC Archive, ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE),...
The fourth bimonthly period continued the study of the effects of sulfur in jet fuels on the durability of jet engine hot section components. The effort involved evaluation of the tensile strengths of Udimet 500, Waspalloy, Haynes Alloy 25, Hastelloy R-235 and Rene 41 simulated turbine inlet guide vanes following 12 hours exposure to sulfur-free exhaust gases at 2000F in the Phillips 2-Inch Research Combustor. Recent literature on the oxidation of SO2 to SO3 indicates that: (1) very little SO2...
Topics: DTIC Archive, STREETS, W L, PHILLIPS PETROLEUM CO BARTLESVILLE OK, *GAS TURBINES, *JET ENGINE...
A review was made of published reports and literature on insulation materials for sold rocket motors to establish the state of the art in theory, formulation, testing, and processing to establish the type of design data available and to provide an analysis of the available data. A major effort was made to obtain information on internal insulation materials. Performance data of internal insulation material from torch screening tests, plasma generators, subscale propellant test motors and full...
Topics: DTIC Archive, AEROJET-GENERAL CORP SACRAMENTO CA, *ABLATION, *MATERIALS, *ROCKET ENGINE CASES,...
This is the first of a series of reports describing the results of test firings conducted to determine the performance of low-cost ablative materials which are candidates for use as thrust chamber and nozzle liners for MCD (Minimum Cost Design) Booster engines. This report describes the test of Haveg 41, an ablative composed of phenolic resin and asbestos fibers.
Topics: DTIC Archive, Hintz, James A, AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA, *BOOSTER ROCKET...
These proceedings contain 36 papers presented at the Symposium. A technical evaluation report is included at the beginning of the Proceedings. The Symposium was arranged in seven sessions: Fuel Research (3); Fuel Effects in Main Burners (6); Fuel Preparation (8); Kinetics and Soot Formation (5); Liner Cooling and Traverse Quality (4); Combustion Model Elements (4); and Modelling for Main Burners(6).
Topics: DTIC Archive, ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE),...
