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At least 181 records · Page 10

Effect of Operating Conditions and Design on Afterburner Performance

Afterburners for turbojet engines have, within the past decade, found increasing application in service aircraft. Practically all engines manufactured today are equipped with some form of afterburner, and its use has increased from what was originally a short-period thrust-augmentation application to an essential feature of the turbojet propulsion system for flight at supersonic speeds. The design of these afterburners has been based on extensive research and development effort in expanded laboratory facilities by both the NACA and the American engine industry. Most of the work of the engine industry, however, has either not been published or is not generally available owing to its proprietary nature. Consequently, the main bulk of research information available for summary and discussion is of NACA origin. However, because industrial afterburner development has closely followed NACA research, the omission is more one of technical detail than method or concept. One principal difficulty encountered in summarizing the work in this field is that sufficient knowledge does not yet exist to rationally or directly integrate the available background of basic combustion principles into combustor design. A further difficulty is that most of the experimental investigations that have been conducted were directed chiefly toward the development of specific afterburners for various engines rather than to the accumulation of systematic data. This work has, nonetheless, provided not only substantial improvements in the performance of afterburners but also a large fund of experimental data and an extensive background of experience in the field. Consequently, it is the purpose of the present chapter to summarize the many, and frequently unrelated, experimental investigations that have been conducted rather than to formulate a set of design rules. In the treatment of this material an effort has been made, however, to convey to the reader the "know how" acquired by research engineers in the course of afterburner studies.

Fleming, W. A.↗

The Delta and Thor/Agena launch vehicles for scientific and applications satellites.

Description of the Delta Model 904 and the Thor/Agena Model 9A4 scientific and applications satellite launch vehicles, with projections of future growth and launch costs. These launch vehicles are shown to offer scientific and applications satellite mission planners a broad spectrum in performance capabilities together with unprecedented mission flexibility. Depending on the mission, these two medium class launch vehicles can be configured on the new universal boattail (UBT) Thor booster in either two or three stages with thrust augmentation of the UBT ranging from three to nine strap-on solid propellant motors. Both vehicles incorporate strapdown inertial guidance systems that allow flexible mission programming by computer so ftware changes rather than by adjustments.

Gunn, C. R.↗

The Delta launch vehicle Model 2914 series

Description of a new, medium-class Delta launch-vehicle configuration, the three-stage Model 2914. The first stage of this vehicle is composed of a liquid-propellant core which is thrust-augmented with up to nine strap-on solid-propellant motors. The second stage, recently uprated with a strap-down inertial guidance system, is now being modified to adapt the liquid-propellant descent engine from the Apollo Lunar Excursion Module. The third stage is a spin-stabilized solid-propellant motor. The Model 2914 is capable of injecting 2040 kg into low earth orbit, 705 kg into geosynchronous transfer orbit, or 455 kg into an escape trajectory.

Gunn, C. R.↗

Reversed cowl flap inlet thrust augmentor

An adjustable airfoil is described for varying the geometry of a jet inlet and an ejector inlet in a jet engine for providing thrust augmentation and noise reduction. The airfoil comprises essentially a plurality of segments which are extended radially outward and retracted relative to the longitudinal axis of the engine as a function of a change in the pressure differential between the upstream and downstream surfaces of the airfoil. A servo mechanism responsive to the change in the pressure differential is coupled to the airfoil to extend and retract the airfoil segments to maintain the pressure at a maximum on the downstream side of the airfoil relative to the pressure on the upstream side of the airfoil. At low speeds, such as at take-offs and landings, the airfoil is fully extended while at high speeds it is fully retracted.

Cheng, D. Y.↗

Prediction methods for jet V/STOL propulsion aerodynamics

The current status of prediction methods for propulsive flows and propulsion-induced effects which occur on jet V/STOL aircraft is reviewed. Among the major topics studied are flows in propulsive ducts, propulsion-induced ground and thermal effects, aerodynamic loads induced during V/STOL and transition flight, flow vectoring devices, and thrust augmented ejector and lift-fan studies. The current predictive capability in jet V/STOL propulsion aerodynamics is assessed. Future research needs are identified, with particular reference to activities that can improve the usefulness of prediction methods for jet V/STOL aircraft.

Platzer, M. F.↗

Altitude test of several afterburner configurations on a turbofan engine with a hydrogen heater to simulate an elevated turbine discharge temperature

A performance test of several experimental afterburner configurations was conducted with a mixed-flow turbofan engine in an altitude facility. The simulated flight conditions were for Mach 1.4 at two altitudes, 12,190 and 14,630 meters. Turbine discharge temperatures of 889 and 1056 K were used. A production afterburner was tested for comparison. The research afterburners included partial forced mixers with V-gutter flameholders, a carburetted V-gutter flameholder, and a triple ring V-gutter flameholder with four swirl-can fuel mixers. Fuel injection variations were included. Performance data shown include augmented thrust ratio, thrust specific fuel consumption, combustion efficiency, and total pressure drop across the afterburner.

Johnsen, R. L.↗

Space Shuttle - Now and later

The Space Shuttle System consisting of four major elements, the orbiter, three main engines, an expendable external tank, and solid rocket boosters is examined. Dimensions, thrust and payload capacity are observed, noting cost reduction through recovery and subsequent reuse of some components. Return of the solid rocket boosters (SRB's) via parachute and recovery from the ocean for refurbishment is covered. Objectives for the first mission scheduled for November 1979 include achieving a 150 nautical mile orbit and carrying a payload consisting of development flight instrumentation (DFI), the induced environment contamination monitor (IECM), and the aerodynamic coefficients identification package (ACIP). A section devoted to performance enhancement, discusses weight reduction on the orbiter, external tanks and thrust augmentation through the use of strap on solid motors (SOSM).

Malkin, M. S.↗

A computational model for three-dimensional incompressible wall jets with large cross flow

A computational model for the flow field of three dimensional incompressible wall jets prototypic of thrust augmenting ejectors with large cross flow is presented. The formulation employs boundary layer equations in an orthogonal curvilinear coordinate system. Simulation of laminar as well as turbulen wall jets is reported. Quantification of jet spreading, jet growth, nominal separation, and jet shrink effects due to corss flow are discussed.

Murphy, W. D.↗

Shuttle integration status

The paper examines systems certification methodology for the Space Shuttle. Attention is then given to recent activities that will enhance the capability of the Shuttle during the operational period; structural dynamics, main propulsion, and thrust augmentation are considered.

Morris, O. G.↗

A study of a VTOL thrusting ejector in low speed flight, volume 2

An experimental investigation of V/STOL thrust augmenter wings in flight at slow forward speeds is reported. Two rectangular planforms of differing relative chord lengths were tested. The augmenters were positioned in the aft portion of the wing to produce increases in circulation lift. Two blown flap configurations were tested for comparison. Surface pressures as well as total forces and moments were obtained on the semispan models at two flap deflections and a range of momentum coefficients. Tabulations of surveys at the pressure augmenter exit, downwash surveys downstream of the wing, and force and moment data are included.

Stewart, V. R.↗

Space Shuttle main engine performance assessment - Columbia's first flight

Design features and performance of the Shuttle main engines first flight are presented. Each of the three engines produces 470,000 lb of thrust, operates at 3,012 psia, and has a 77.5 to 1 nozzle expansion ratio. The engines are designed for a 7.5 hr operational life, and will be tested at 109% capacity in future Shuttle flights. The developmental program is outlined, and includes 127,000 sec of operational testing on 19 engines. Engine operations and components are described, noting 100% burning of the hydrogen and oxidizer, high pressure fuel turbopumps, the controller assembly, etc.; details of solutions to fatigue failures and subsequent certification are provided. The nine minute first flight firing revealed a radiant heating of a control sensor transducer, which was shielded for succeeding flights. Alternatives are given for thrust augmentation, for which each 1% yields an additional 800 lb payload increase capability, and can be implemented by 1987.

Thompson, J. R., Jr.↗

NASA's laser-propulsion project

Design concepts, study results, and research directions toward development of CW laser heating of remotely flying spacecraft fuels to provide high impulse thrust are presented. The incident laser radiation would be absorbed by hydrogen through a medium of a laser-supported plasma. The laser energy could be furnished from an orbiting solar-powered laser platform and used to drive the engines of an orbital transfer vehicle (OTV) at costs less than with a chemical propulsion system. The OTV propulsion chamber would be reduced in size comparable to the volume addition of the incident laser energy absorber. The temperatures in the hydrogen-fueled system could reach 5000-15,000 K, and studies have been done to examine the feasibility of ion-electron recombination. Kinetic performance, temperature field, and power necessary to sustain a laser thrust augmented system modeling results are discussed, along with near-term 30 kW CO2 laser system tests.

Jones, L. W.↗

Radiation from a double layer jet

The aerodynamic radiation caused by two acoustic point sources located symmetrically on the sides of a double layer jet which produces a velocity discontinuity was examined, with attention given to the effect on the sound by the stream. Basic equations were defined in terms of wave propagation in the fluid in motion and a Fourier transformation. It was found that the radiation due to a point source on one side of the jet is enhanced by the presence of sound transmitted from the other side. The effect is expressed as a function of the reflection coefficient, wherein the reflections take place at the vortex interfaces separating the fluid in motion from the fluid at rest. The intensity patterns were determined to be kidney-shaped, lung-shaped, and heart-shaped, and characterized by a deep valley in the directivity pattern. The significance of the findings for STOL aircraft ejector thrust augmentation is mentioned.

Dash, R.↗

A design study of a reaction control system for a V/STOL fighter/attack aircraft

Attention is given to a short takeoff vertical landing (STOVL) aircraft reaction control system (RCS) design study. The STOVL fighter/attack aircraft employs an existing turbofan engine, and its hover requirement places a premium on weight reduction, which eliminates prospective nonairbreathing RCSs. A simple engine compressor bleed RCS degrades overall performance to an unacceptable degree, and the supersonic requirement precludes the large volume alternatives of thermal or ejector thrust augmentation systems as well as the ducting of engine exhaust gases and the use of a dedicated turbojet. The only system which addressed performance criteria without requiring major engine modifications was a dedicated load compressor driven by an auxilliary power unit.

Beard, B. B.↗

Study of aerodynamic technology for single-cruise-engine V/STOL fighter/attack aircraft

Conceptual designs and analyses were conducted on two V/STOL supersonic fighter/attack aircraft. These aircraft feature low footprint temperature and pressure thrust augmenting ejectors in the wings for vertical lift, combined with a low wing loading, low wave drag airframe for outstanding cruise and supersonic performance. Aerodynamic, propulsion, performance, and mass properties were determined and are presented for each aircraft. Aerodynamic and Aero/Propulsion characteristics having the most significant effect on the success of the up and away flight mode were identified, and the certainty with which they could be predicted was defined. A wind tunnel model and test program are recommended to resolve the identified uncertainties.

Mark, L.↗

High angle-of-attack aerodynamics of a strake-canard-wing V/STOL fighter configuration

High angle-of-attack aerodynamic data are analyzed for a strake-canard-wing V/STOL fighter configuration. The configuration represents a twin-engine supersonic V/STOL fighter aircraft which uses four longitudinal thrust-augmenting ejectors to provide vertical lift. The data were obtained in tests of a 9.39 percent scale model of the configuration in the NASA Ames 12-Foot Pressure Wind Tunnel, at a Mach number of 0.2. Trimmed aerodynamic characteristics, longitudinal control power, longitudinal and lateral/directional stability, and effects of alternate strake and canard configurations are analyzed. The configuration could not be trimmed (power-off) above 12 deg angle of attack because of the limited pitch control power and the high degree of longitudinal instability (28 percent) at this Mach number. Aerodynamic center location was found to be controllable by varying strake size and canard location without significantly affecting lift and drag. These configuration variations had relatively little effect on the lateral/directional stability up to 10 deg angle of attack.

Durston, D. A.↗

Propelling AMPTE into orbit

Three types of propulsion - liquid, solid and cold gas - were used to get the three AMPTE (Active Magnetospheric Particle Tracer Explorers) spacecraft into their operational orbits. The booster, a thrust-augmented DELTA, placed the 1028 kg (2267 lb) international payload into a 555 km x 8.78 Re x 28.7 deg transfer orbit. Solids carried aloft by two of the spacecraft were then fired to tilt one orbit and elevate the other. Cold gas provided two of the spacecraft with torquing capabilities for attitude maneuvering. All told, it took 12 solid, 2 liquid and 2 cold gas propulsion units to get the three AMPTE spacecraft off the ground and into their operational orbits. The relationships between all of them and the manner in which they were utilized on August 16, 1984 the day of the launch - are discussed here.

Smola, J. F.↗

Analysis of interacting dual lifting ejector systems

An analytical treatment is presented for a flowfield generated by a pair of interacting, two-dimensional parallel jets, representative of the two exhaust streams issuing from the thrust augmentor nozzles of dual lifting jet VTOL aircraft propulsion systems. Predictions of the analysis for the ratio of primary to secondary velocity are in close agreement with experimentally observed values, if the spreading rate parameter is allowed to assume a value greater than that which applies to a free jet. Theoretical results are combined with existing experimental data for unventilated jets, in order to arrive at an estimate of the thrust augmentation produced by a jet pair with an arbitrary degree of ventilation.

Lund, T. S.↗