Browse Topic: Turbojet engines

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Electronic Warfare WeaponTBMG-360682/1/2020
MBDA Hertfordshire, UK +44 (0)1438 752000
DRIVE – TYPE XV ENGINE ACCESSORY - DESIGN STANDARD FORAS20005A (Current)7/16/2018
E-25 General Standards for Aerospace and Propulsion Systems
Recommended Ice Bath for Reference JunctionsARP691 (Current)5/3/2018
The ice bath recommended herein is similar to that described in SAE AIR 46.* Some material not presented in AIR 46, including preferred dimensions, has been added.
E-32 Aerospace Propulsion Systems Health Management
Uncertainty of In-Flight Thrust DeterminationAIR1678B (Current)10/22/2016
This document defines and illustrates the process for determination of uncertainty of turbofan and turbojet engine in-flight thrust and other measured in-flight performance parameters. The reasons for requiring this information, as specified in the E-33 Charter, are: determination of high confidence aircraft drag; problem rectification if performance is low; interpolation of measured thrust and aircraft drag over a range of flight conditions by validation and development of high confidence analytical methods; establishment of a baseline for future engine modifications. This document describes systematic and random measurement uncertainties and methods for propagating the uncertainties to the more complicated parameter, in-flight thrust. Methods for combining the uncertainties to obtain given confidence levels are also addressed. Although the primary focus of the document is in-flight thrust, the statistical methods described are applicable to any measurement process. The E-33 Committee
E-33 In Flight Propulsion Measurement Committee
Assessment and Calibration of Semi-Empirical Models for Predicting Pollutant Emissions of the Erica Tiltrotor Turboshaft EngineF-0070-2014-96225/20/2014
In this paper, the most meaningful EINOx and EICO zero-dimensional emission prediction methods from the literature are described and reviewed, while a selection of them are tuned and validated against publicly available experimental data. The equations of these models are implemented in TSHAFT, a proprietary engine simulator developed at the University of Padova which predicts the performance of turbojet engines in both design and off-design operation modes under variable ambient conditions. Then, TSHAFT is set up to predict the emissions of a generic turboshaft engine ranging in power from 1,800 shp to over 5,000 shp, and the results are compared to proprietary experimental data obtained during an aircraft landing and take-off cycle (LTO) at standard sea level conditions. Finally, the emissions of a turboshaft engine of 3000 SHP engine are calculated for two flight conditions (i.e. hover and forward flight cruise) of the ERICA tiltrotor. Finally, the paper presents the results of the
Mas, Lorenzo, Benini, Ernesto, Ponza, Rita
DRIVE - TYPE XV ENGINE ACCESSORY - DESIGN STANDARD FORAS20005 (Historical)11/1/2012
E-25 General Standards for Aerospace and Propulsion Systems
Thermal Mechanical Fatigue Crack Growth TestingTBMG-142988/1/2012
Turbines in aircraft turbojet engines are being subject to increasingly higher temperatures to improve fuel efficiency. High turbine efficiency requires the ability of turbine blades to withstand gas temperature of the order of 1350 to 1550 °C. In polycrystalline materials, these increased temperatures would cause creep strains along grain boundaries that would be unacceptable. Even single-crystal materials must be pushed to their limits to insure that engine performance is maximized. Airfoils in modern gas turbine aircraft use a systems approach for cooling to achieve required component life. There are three basic components to these systems: a cast nickel single-crystal superalloy in combination with thermal barrier coatings, and a sophisticated cooling scheme consisting of intricately designed channels and holes through the core and surface of the airfoil.
Gaseous and Particle Emissions from a Turbo-Jet Engine Operating on Alternative Fuels at Simulated Altitudes2011-01-259710/18/2011
Gaseous and particle emission assessments on a 1.15 kN-thrust turbojet engine were conducted at five altitudes in an altitude chamber with Jet A-1 fuel, pure Fischer Tropsch (FT), and two mixed fuels of JP-8 with FT or Camelina-based hydro-processed jet fuels. In general, lower emissions in CO₂, NOx, and particle number as well as higher emissions in CO and THC were observed at higher altitudes compared to lower altitudes. These observations, which were similar for all test fuels, were attributed to the reduced combustion efficiency and temperature at higher altitudes. The use of alternative fuels resulted in lower CO₂ emissions, ranging from 0.7% to 1.7% for 50% to 100% synthetic fuel in the fuel mixture at various altitudes. In terms of CO, the use of 100% FT fuel resulted in CO reduction up to 9.7% at 1525 m altitude and up to 5.9% at 9145 m altitude. Significant reduction in particle diameter, number and mass emission rates were observed with the use of alternative fuels due to the
Chan, Tak W., Cuddihy, Kevin, Chishty, Wajid, Davison, Craig, McCurdy, Mark, Barton, Peter
Multivariable Aircraft Engine Controller Design Using an Optimal Loop Shaping Approach2011-01-251110/18/2011
The current pressure for fuel burn savings and increasing performance in the commercial aerospace market demands highly complex engine control systems to optimize fuel consumption throughout the engine operating envelope, as well as meet the regulatory requirements in terms of safety and performance. These conflicting objectives normally lead to trade-off solutions that are difficult to precisely estimate. Therefore some decisions to characterize the engine controller still reside on experience from previous designs and, as a result, add subjectivity and increase the potential for wrong parameter selection. This paper proposes an algorithmic approach to design a turbojet engine controller in a multivariable, two-degree-of-freedom configuration, obtaining H-infinity robust stabilization. It introduces an optimized loop shaping design procedure, with the use of a Genetic Algorithm (GA), to further improve the control system performance, as well as bring the experience applied by
Silva, Douglas F R, Barbosa, Joao, Adade Filho, Alberto
Hypersonic possibilities11MOMD0929_0410/1/2011
WHEN IT COMES TO REVIVING HIGH-SPEED AIR TRAVEL, IT ALL COMES DOWN TO PROPULSION, PROPULSION, PROPULSION. OVER THE DECADES, much research in the U.S., Europe, Russia, and Japan has been undertaken on aspects of ultra-high-speed flight, including radical airframe shapes, the use of unconventional materials, and ramjet and hybrid engines. Although Russia developed, and for a brief period in the late 1970s operated, its own Tu-144 supersonic air transport (and used it mostly as a high-speed freight carrier), only the Anglo-French Concorde resulted in scheduled-service supersonic passenger air traval. Work on follow-on supersonic air transports continued in the 1980s but none of it came to anything, as rising fuel prices and environmental concerns killed off enthusiasm for speed. The industry concentrated instead on making conventional aircraft that were quieter and less fuel-thirsty.
Gardner, Richard
Hypersonic possibilities11AERD0907_019/7/2011
When it comes to reviving high-speed air travel, it all comes down to propulsion, propulsion, propulsion. Over the decades, much research in the U.S., Europe, Russia, and Japan has been undertaken on aspects of ultra-high-speed flight, including radical airframe shapes, the use of unconventional materials, and ramjet and hybrid engines. Although Russia developed, and for a brief period in the late 1970s operated, its own Tu-144 supersonic air transport (and used it mostly as a high-speed freight carrier), only the Anglo-French Concorde resulted in scheduled-service supersonic passenger air traval. Work on follow-on supersonic air transports continued in the 1980s but none of it came to anything, as rising fuel prices and environmental concerns killed off enthusiasm for speed. The industry concentrated instead on making conventional aircraft that were quieter and less fuel-thirsty.
Gardner, Richard
Considerations of Aeroacoustics in Turbojet-Engine TestingTBMG-TB-0053296/1/2009
Recommendations for preventing aeroacoustic damage to test cells have been made. A study of the aeroacoustics of a turbojet-engine test cell has been performed as one step in the development of a computational aeroacoustics capability (CAA) that could provide guidance for the design and operation of such cells. Ground testing of turbojet engines in test cells necessarily involves very high acoustic amplitudes, often severe enough to cause damage to test-cell equipment and to engines under test. Heretofore, the acoustic responses of test cells containing energetic jets have been poorly understood and generally unpredictable. The CAA capability is intended to enable prediction of deleterious acoustic events, making it possible to design test cells and choose operating conditions to prevent damage and thereby avoid the costly interruption of test schedules.
Going greenAEROSEP07_039/1/2007
The global aerospace industry gears up for big changes in fuel burn, emissions, and noise. It used to be that environment was on the agenda when aerospace professionals gathered for a symposium. Now environment is the agenda. The new mindset was never more evident than it was this past summer at the Paris Air Show, where exhibitor after exhibitor touted their “green” credentials. One company, CFM International, went so far as to carpet its stand with live green grass.
Rosenberg, Barry
Universal Maintenance & Overhaul Stand for Turbo-Jet (10,000 Lbs. Thrust Class) and Turbo-Prop EnginesARP458 (Current)12/16/2002
AGE-4 Packaging, Handling and Transportability Committee
Small Hybrid Rocket Engines Fabricated via X-Ray LithographyTBMG-298058/1/1999
Small hybrid rocket engines of a proposed type would burn specially shaped hollow cylinders of solid fuel containing slanted oxygen-injection channels, as shown in the figure. These engines would exploit a vortex flow phenomenon associated with the radial inflow of the oxygen in the channels. The fuel/flow-channeler cylinders could be supplied in or as cartridges that could fit into reusable receptacles.
An AJAX Technology Advanced SSTO Design Concept9855279/28/1998
ABSTRACT <jats:p>&lt;div class="htmlview paragraph"&gt;This paper presents an advanced single stage-to-orbit (SSTO) design concept based on our understanding of Russian AJAX technologies. The concept brings together a unique set of subsystem components to enhance the performance of an advanced combined cycle engine powered SSTO design concept. A magnetohydrodynamic (MHD) generator-accelerator energy bypass system is used to maintain subsonic flow in the engine combustion chamber. And, an electromagnetic drag reduction system is used to reduce wave and base drag during ascent and reentry. The performance of the advanced highly reusable SSTO is compared to a reference advanced air-breathing rocket-based combined cycle ejector ram-scramjet powered SSTO design concept. The results indicate an approximate 15% performance increase compared to the reference design.&lt;/div&gt;</jats:p>
Chase, R. L., Boyd, R., Czysz, P., Froning, H. D., Lewis, Mark, McKinney, L. E.
GUIDE FOR DETERMINING ENGINE STARTER DRIVE TORQUE REQUIREMENTSAIR781 (Current)9/1/1994
A general discussion is presented herein, to outline the starter functions which are necessary for a successful engine start. In addition, sample calculations are included to illustrate an accepted method of determining the engine starting time from known data. Further consideration is then given to the relationship between starter torque output and engine pad strength and a generalized formula is presented for calculating the theoretical transient torque peaks for a simplified starter-engine system. Sample calculations for actual tests are included, and the results of these calculations are compared with measured values.
AE-6 Starting Systems and Auxiliary Power Committee
The Pond Racer - An Exercise in the Control of Heat Transfer in a Tight Composite Compartment9301543/1/1993
The POND RACER is an all-Composite, twin boom airplane Figure 1,(1), (2), (3), fitted with two, dual turbocharged automotive engines. The exhaust system, Figure 2, for this six cylinder power plant occupies the rear portion of a compact engine compartment. Initially, no provision was made for moving cooling air through this densely-packed engine compartment. Portions of the exhaust system passed within less than 2.5 cm (1 in.) of the composite cowl enclosing the engine compartment. The temperatures developed could result in failure of the computer,which controls the engine, other components, and the composite cowl in a matter of minutes. Currently-used insulation designs did not appear to provide enough capability to work for this application. A Thermal Protection System was developed, installed, and proven out during test flights. Analysis of the flight data, measured by thermocouples linked into the flight recorder, verified the adequacy of the Thermal Protection System. These
Trelease, Robert B.
Integrated Air Separation and Propulsion System for Aerospace Plane with Atmospheric Oxygen Collection9209744/1/1992
Aerospace plane with atmospheric oxygen collection for oxidizer supplying on rocket part of trajectory is very attractive concept. The key unit of power plant of such plane is an air liquefaction and separation system. It is proposed to accomplish the oxygen extraction on the bank of vortex tubes of special kind. The compressor of low speed turbojet engine would served in oxygen collection phase of flight as pressure generator for air separation system. Poor air after oxygen extraction is supposed to use actively in one of power plant combustion chambers. The configuration of integrated air separation and propulsion system and results of estimation of system using on two stage aerospace plane are discussed.
Balepin, V.V., Tjurikov, E.V.
Prediction of Engine Casing Temperature of Fighter Aircraft for Infrared Signature Studies9209614/1/1992
Prediction of Engine Casing Temperature of Combat Aircraft for various operating conditions needs modeling of convective and radiative heat flow from the jet pipe to the casing. Radiation modeling which implies modeling of multiple reflections and scattering is done here by the radiance-irradiance approach. The engine layout is approximated by three co-axial cylinders and axially discretized. The shape factors (which account for the directional dependence of radiation heat flow) for various configurations needed in radiation modeling are analytically obtained by a sequence of shape factor algebra from standard configurations. The resulting non-linear algebraic equations of combined convection and radiation heat flow are solved by an iterative technique to give the engine casing temperatures which may be used for infrared signature studies.
Mahulikar, Shripad Prabhakar
Propulsion Systems with Air Precooling for Aerospaceplane9111824/1/1991
Using LH2 heat sink capacity for air precooling in turbojets allows to increase specific impulse and in many cases to reduce specific mass (mass-to-sea level thrust ratio). A number of precooled turbojet schemes are considered. Classification of turbojet according to the cooled air amount and depth of cooling is proposed. ATR with extended precooling (Tout=100K) is examined in more detail. For propulsion systems including different types of engines, running simultaneously the concept of LH2 heat sink capacity concentration for turbojet air precooling is proposed.
Rudakov, A.S., Balepin, V.V.
GUIDE TO TEMPERATURE MONITORING IN AIRCRAFT GAS TURBINE ENGINESAIR1900 (Historical)2/7/1991
This Aerospace Information Report (AIR) provides an overview of temperature measurement for engine monitoring systems in various areas of aircraft gas turbine engines while focusing on current usage and methods, systems, selection criteria, and types of hardware. This document emphasizes temperature monitoring for diagnostics and condition monitoring purposes.
E-32 Aerospace Propulsion Systems Health Management
A Canadian Government Look at Airworthiness8809353/1/1988
The paper traces the development of the approach to airworthiness taken by Canadian government authorities from its origin through to current practices. It describes the Aerospace industry, the carriers and general aviation in statistical terms, indicates the impact of economic regulatory reform and suggests the way ahead for Canadian and other authorities lies in the attitude and methodologies practiced by the European authorities in their development of JARs. I SHOULD PERHAPS start this presentation with a short word about authorities. At the conclusion of a speech on safety regulation by Mr. Ronald Ashford of the UK Civil Aviation Authority, reported in Flight International of April 19, 1986, the following quotation from St. Paul to the Romans appeared: “You wish to have no fear of the authorities? Then continue to do right and you will have their approval, for they are God's agents working for your good”. Aprocryphal or not, this would appear to give some divine authority for our
Mew, John F., Torck, James A.
Propulsion/Aerodynamic Integration in ASTOVL Combat Aircraft87233312/1/1987
The provision of STOVL capability and a Supersonic capability in a small combat aircraft simultaneously introduces design and operational penalties, freedoms and complexities. The respective minimization, exploitation, and simplification of these represents a unique challenge, which must be met in order to maximise overall cost-effectiveness. The key to this lies in the full exploitation of the potential for powerplant/airframe integration of the advanced STOVL aircraft, via the integrated Flight/Powerplant Control System (IFPCS). The overall design philosophy and control strategies of the IFPCS are highlighted and discussed with particular reference to the single-engined vectoring nozzle aircraft. These include: a) controlling the combination of propulsive thrust vector and aerodynamic force vector to achieve optimum aircraft response and optimum aircraft performance. b) controlling the manner in which the powerplant generates the required thrust vector in order to achieve maximum
Appleyard, George M.
Tactical Air-to-Surface Requirements for the 1990s81109810/1/1981
PROJECTIONS OF REQUIREMENTS FOR MANNED, TACTICAL AIR-TO-SURFACE SYSTEMS in the 1990’s must consider a number of complex issues involving future scenarios; threat environment; force mix; emerging technology in weapons, avionics, and airplane design; and operational concepts. The purpose of this paper is to provide a brief overview of some of the future requirements that may change current design approaches and concepts of operation. Parametric trades and design considerations on such issues as range-payload, short takeoff and landing (STOL) requirements, autonomous versus nonautonomous systems, and air-to-air versus air-to-ground requirements are summarized. Airplane design and technology requirements having application to the resulting requirements are identified, and an example of a possible future tactical air-to-surface fighter is described.
Caldwell, A. L.
The Hippies Are Coming ! (How to Apply Hot Isostatic Processing (HIP) in the Automotive Industry)8003112/1/1980
Hot isostatic processing (HIP) is a rapidly expanding manufacturing process which involves treating parts at very high temperatures in an inert gas at very high pressures. HIP-treated parts display dramatic improvements in strength, fatigue resistance, and other important characteristics. Components of aircraft turbine engines, high-speed tool steels, cemented carbides, carbon/carbon composites, titanium, and super-alloys are all commonly HIP'ed today. Castings' characteristics are improved by HIP'ing. HIP's potential value to the automotive industry lies in weight reduction, reliability, safety, and conservation of energy and scarce materials. Smaller, stronger, lighter engine blocks, for example, are a distinct possibility with HIP. HIP/PM gear blanks requiring minimal machining are another possibility. The relatively high cost of HIP has been the principal impediment to its widespread commercialization. With larger capacity systems the economics of HIP are now in the range of
Hanes, Hugh D., Rex, Robert M.
The HiMAT RPRV Propulsion Control System7608872/1/1976
A multimode propulsion control system concept has been developed for the remotely piloted research vehicle of the NASA Highly Maneuverable Aircraft Technology program. The concept is based on the retention of most of the bill-of-materials control hardware, and will allow the implementation of flight/propulsion control coupling, high and normal flow stability margin operating modes, and rapid and normal thrust response modes. Description of the control system, the airborne control components, and the ground generated and displayed signals is given in this paper.
Bayati, Jamal E.
Integrated Engine Inlet Thermal Anti-Icing and Environmental Control System (TAI/ECS)7605172/1/1976
The integrated engine inlet thermal anti-icing and environmental control system (TAI/ECS) for subsonic transport airplanes was conceived primarily for the efficient use of available energy and minimum engine bleed air extraction. The concept employs the engine inlet leading edge as the heat exchanger to provide ice protection for the engine inlet surfaces and to cool bleed air for the environmental control system. The results of a study conducted for a typical wide-body airplane using high bypass ratio engines show that the system concept will result in potential improvements in airplane operation and engine maintenance.
Shah, A. D.
Diesel Exhaust Odor Analysis by Sensory Techniques7402152/1/1974
The odor profile method has been applied to the measurement and analysis of diesel exhaust odor. The human sensory panel has described the odor of diluted exhaust and analytical fractions isolated from the exhaust in terms of total intensity of aroma (TIA), and individual odor character notes. For convenience, diesel exhaust odor can be described in two character groups-oily-kerosene and smoky-burnt odor. The odorous species were determined by detailed chemical analyses supported by comparative data from reference compounds. To achieve reliable quantitative odor intensity measurements, it was necessary to present the odor panel with a series of concentrations (dilutions) of exhaust in air over a wide range. The odor intensity at a given exhaust concentration is computed from a least squares analysis of the entire panel data. The results demonstrate an odor intensity range of slight to moderately strong for diesel exhaust at 1000:1 dilution.
Kendall, D. A., Levins, P. L., Leonardos, G.
On-Line Calibration of High-Response Pressure Transducers During Jet-Engine Testing7408252/1/1974
Current jet engine testing is concerned with the effect of inlet pressure and temperature distortions on engine performance and involves the use of numerous miniature pressure transducers. Despite recent improvements in the manufacture of miniature pressure transducers, they still exhibit sensitivity change and zero shift with temperature and time. To obtain meaningful data, a calibration system is needed to determine these changes. A system has been developed which provides for computer selection of appropriate reference pressures selected from nine different sources to provide a two- or three-point calibration. Calibrations are made on command, before and sometimes after each data point. A unique “no leak” matrix valve design is used in the reference-pressure system. Zero-shift corrections are measured and the values are automatically inserted into the data reduction program.
Armentrout, E. C.
Spectrometric Oil Analysis - Use and Interpretation of Data7203032/1/1972
The paper describes a theory that can be used to explain a mathematical statement of the functioning of an oil system. To arrive at this theory, the rates of contamination of the oil circuits of turbojet engines were investigated extensively, by way of spectrometric oil analyses. The details of the phenomena involved are presented, along with the parameters governing the oil system; a chart for interpreting spectrometric oil analysis data is developed, and the mathematical theory is worked out in detail. There is a relation between the rate of wear of the components of an engine and the rate of contamination of its oil system. By indicating metal particle concentration in the oil, spectrometric oil analysis detects rates of wear high enough to constitute risk of accident due to engine failure. The detection method described takes into account the relation between the rate of contamination and the measured concentration of particles, making it possible to set up contamination rate
Lotan, D.
Accuracy in Fuel Management for General Aviation6802092/1/1968
Present fuel flow measuring systems for medium priced aircraft lack the accuracy needed for efficient flight planning and cargo weight scheduling. They also lack the means for totalizing the measurement signal to provide an accurate measure of fuel consumed or fuel remaining. A new fuel management system has been designed to use a turbine meter to measure fuel flow. Since the measuring instrument provides a digital output, flow rate can be totalized by means of a pulse counter. Therefore, in addition to rate indication, the pilot has an accurate total of fuel consumed or fuel remaining at his disposal. This paper discusses the advantages and disadvantages of existing systems and contrasts them with the turbine meter system. It also discusses fuel density changes due to temperature and fuel type and how they affect the measuring system in both piston and turbo-type aircraft.
Wilson, James C.
Low-Speed Characteristics of High-Performance Lift-Engine V/STOL Aircraft6806442/1/1968
Considerable research on large-scale high-performance, lift-engine, V/STOL configurations has been conducted at Ames Research Center. The exhaust gas reingestion characteristics, lift-engine inlet total-pressure recovery and distortion, and engine-airframe induced effects were measured in the 40 × 80 ft wind tunnel both in and out of ground effect over a wide range of transition flight conditions. The results of these investigations show that the lift-engine configurations studied may have severe operational constraints placed upon them during transition.
Barrack, Jerry P., Kirk, Jerry V.
USAF Application of Airborne Recorders for Propulsion Diagnostics6703592/1/1967
The United States Air Force is evaluating the application of an airborne analyzer and digital recording system to assess, diagnose, and predict turbojet engine health on an immediate and long-term basis. This paper presents a brief discussion of the C-141 “Lead-the-Force” System, the C-5A Malfunction Detection, Analysis, and Recording Subsystem, and discusses in detail the Engine Analyzer System (EASY). The EASY discussion includes the design philosophy, hardware, test programs, computer programs, and test results.
Carlson, Robert J.
Estimating Maintenance Man-Hours Per Flight Hour for Business Turbojet Airplanes6702282/1/1967
A new method has been developed for estimating the man-hours of labor per flight hour that will be required to maintain many of today's turbojet/fan business airplanes. This method consists of establishing a base manhour per flight hour depending on an airplane's empty weight completely equipped. Then the effect of certain factors that influence this base manhour can be calculated, and the base manhour appropriately adjusted to reflect the total number of man-hours per flight hour. In addition, material costs are estimated. This procedure offers a planned, systematic means by which the maintenance costs of most airplanes in this class can be estimated on an objective basis.
Kysor, Harley D., Bingham, Tayler H.
A Comparison of Fixed Wing Reusable Booster Concepts6703842/1/1967
Eight fixed-wing reusable horizontal landing booster point design concepts are presented and compared on the basis of weight, cost, technical difficulty, and availability date. The eight vehicle types considered are all basically two-stage systems with a lifting body reusable second stage, with all vehicles normalized to place 40,000 lbs. payload in orbit. All flight vehicles are fully recoverable and capable of flying back and landing at the launch site. Vehicle types discussed are vertical take-off horizontal landing rockets, sled launched horizontal take-off rockets, runway launched horizontal take-off rockets, air breathing first stages, combined air breathing and rocket first stages, oxidizer collection concepts, supersonic combustion ramjets, and in-flight refueling vehicles. Each of these vehicle types is depicted in the paper and its design and performance characteristics are discussed. System non-recurring costs tend to be proportional to the inert weight of the vehicle, and
Nau, Richard A.
New Advances in Nondestructive Testing Techniques6703392/1/1967
New developments in nondestructive testing for turbojet engines and aircraft are illustrated and current problem areas are outlined. Development work now underway in this field is described. Future requirements, related to such aircraft as the 747 and SST and their engines are anticipated.
Bogart, H. G.
Landing and Taxiing Lights - Design Criteria for InstallationARP693A (Historical)2/1/1967
This document includes requirements of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a) single engine personal and/or liaison type; b) light twin engine; c) large multiengine propeller; d) large multiengine turbojet; e) military high performance fighter and attack; and f) helicopter. The purpose of this document is to provide certain basic considerations and design criteria for installation of landing and taxiing light systems for night operation.
A-20B Exterior Lighting Committee
Lubricants for High Performance Turbine Engines6600712/1/1966
Several lubricants now available have the requisite performance characteristics for use in the high temperature environments predicted for the Mach 2.0-4.0 turbojet engines. Based upon bench and rig evaluations, these lubricants promise levels of safety, reliability, and economy in the high Mach number engines equivalent to current commercial lubricant powerplant systems. Performance data comparing existing commercial aviation lubricants with the advanced Type 3 and Type 4 lubricants are reported and discussed.
McHugh, Kenneth L.
Operational Experience with the Trident Aircraft6403311/1/1964
British European Airways was the pioneer in introducing turbine-engined aircraft into passenger service. Engineering work on the aircraft, which became the Viscount, was commenced by Mr. R. C. Morgan in November 1945, leading finally to the introduction of the Viscount 701 (Rolls-Royce Dart engines) into service in April 1953, preceded by the passenger service of the Viscount 630 in July 1950. A Viscount was flown by BEA in the New Zealand Air Race in October 1953. In April 1960 BEA introduced the Comet 4B medium range jet with Rolls-Royce Avon engines into service and the following February the Vanguard with Rolls-Royce Tyne engines was introduced into service. With four years experience of the Comet 4B and on the background of the propeller-turbine experience, BEA introduced the Hawker Siddeley Trident (Rolls-Royce Spey engines) into service in March 1964. This unique combination of medium range jet operating experience is reviewed. The Comet 4B is a very successful, popular and
Morgan, R. C.
A Model for Time Varying and Interfering Stress-Strength Probability Density Distributions with Consideration for Failure Incidence and Property Degradation6406161/1/1964
The Reliability prediction approaches which are commonly used to estimate the Reliability of complex electronic devices are shown not to apply to the structural elements of the highly stressed parts of such mechanical devices as turbojet engines. The paper introduces the fundamental relationships of computing the probability of failure from interfering and compatible stress-strength probability functions as the most promising approach to the Reliability analysis of structural elements. The changes of the probability density functions with time as a result of failure incidence probability and strength degradation are analyzed and described. The effect of these changes on the probability of failure in the sense of a force of mortality function are introduced and a digital computer approach to the solution of the analytical complexities is described. Preliminary results from this computerized approach to structural Reliability analysis are given.
Bratt, M. J., Reethof, G., Weber, G. W.
Operational Experiences Of Jet Transports6304451/1/1963
Operational experiences of jet transports as determined from NASA VGH records collected during routine airline operations are discussed. The information presented relates to the flight loads, airspeed operating practices, and landing contact conditions. The load sources considered are gusts, maneuver, autopilot, and landing impact. The discussion of airspeeds covers the normal operating speeds, speeds in rough air, and overspeeds. Implications of the data as regards supersonic transport operations are indicated.
Hunter, Paul A., Coleman, Thomas L.
Landing and Taxiing Lights - Design Criteria for InstallationARP693 (Historical)6/1/1961
This document includes requirements of installations of adequate landing and taxiing lighting systems in aircraft of the following categories: a) single engine personal and/or liaison type; b) light twin engine; c) large multiengine propeller; d) large multiengine turbojet; e) military high performance fighter and attack; and f) helicopter. The purpose of this document is to provide certain basic considerations and design criteria for installation of landing and taxiing light systems for night operation.
A-20B Exterior Lighting Committee
A Consideration of Powerplants for Supersonic Transport Aircraft6103421/1/1961
Sens, W. H., Slaiby, T. G.
A DESIGN PROCEDURE FOR THERMOCOUPLE PROBES6002151/1/1960
An analytical procedure for the design of thermocouple probes for the accurate measurement of gas temperatures under steady state conditions is presented. Basic heat transfer concepts are used in the design of the probe envelope to provide an environment for the junction which is conducive to accurate gas temperature measurement. The procedure is illustrated by the design of a probe for measuring gas temperature in the range of 100°F with an error limit of 0.2°F at Mach numbers ranging from 0.2 to 1.0. Test results from this probe show a maximum error of 0.18°F, substantiating the design procedures.
HAIG, LAURENCE B.
THE JT12 PRATT & WHITNEY AIRCRAFT'S 3000 LB. THRUST TURBOJET ENGINE5903491/1/1959
PHINNEY, DAVIS G.
FACTORS INFLUENCING VARIABLE INLET CONTROL DESIGNS5801011/1/1958
WILCOX, FRED A.
DB'S AND DESIGN — THE ENGINE MANUFACTURER'S POINT OF VIEW5803731/1/1958
NOZICK, HARVEY J.
Thrust Measurement for Jet Transport Operation5800371/1/1958
Saari, M. J.
SYSTEMS ANALYSIS APPROACH TO FIREBEE FLIGHT CONTROL SYSTEMS DEVELOPMENT5701521/1/1957
The evolution of the Fire bee flight control system began with a delineation of both the performance requirements and the limitations imposed on the system. A detailed preliminary analysis of the desired performance characteristics, coupled with the objectives of simplicity, low cost, reliability and use of state-of-the-art system components led directly to system block diagrams showing several basic configurations capable of meeting guidance requirements. Analog and physical simulation using actual autopilot components resulted in a final system design which, in flight, proved capable of meeting the drone system objectives. In 1947, the Air Force requested manufacturers to develop a transonic, high altitude, remotely controlled drone missile to serve as a target for air defense systems. In response to this request the Fire bee * Drone Missile System was conceived and developed. During the last three years the Fire bee has been in volume production.
CORDEN, C. D., HANSEN, H. J.
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