| Build Up and Operation of an Axial Turbine Driven by a Rotary Detonation Engine |
Mar 2012 |
146 pages |
| Authors:
Jonathan R Tellefsen; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
|
 | Detonation combustors provide advantages over current deflagration combustors due to their pressure gain and simplicity of design. Rotary detonation engines (RDEs) offer advantages over pulsed detonation engines (PDEs) due to a steadier exhaust and fewer total system losses. All previous research on turbine integration with detonation combustors has focused on utilizing PDEs to drive axial and centrifugal turbines. The objective of this thesis was the integration and testing of an ... |
|
| The Effect of Blade Lean on an Axial Turbine Stator Flow Having Various Hub Tip Ratios |
2002 |
17 pages |
| Authors:
Edward M. Bennet; IMPACT TECHNOLOGIES LLC ROCHESTER NY
|
| The effect of simple lean on an axial turbine stator was examined using a three dimensional viscous flow code. A constant section stator with no meridional contouring was chosen to isolate the effect of the lean. Four different lean angles were examined at three hub/tip ratios. |
|
| CFD Validation for Propulsion System Components (la Validation CFD des organes des propulseurs) |
MAY 1998 |
|
| Authors:
J. Dunham; ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)
|
 | Computer codes which solve the Reynolds averaged Navier Stokes equations are now used by manufacturers to design turbomachines, but there is no consensus about which grids and which turbulence models are good enough to provide a reliable basis for design decisions. The AGARD Propulsion and Energetics Panel set up Working Group 26 to help to clarify these issues, by analysing predictions (using as wide a range of codes as possible) ... |
|
| Optimizing the Efficiency of a Multi-Stage Axial-Flow Compressor: An Application of Stage-Wise Optimization |
MAR 98 |
94 pages |
| Authors:
Shawn A. Miller; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING
|
| The development of jet engines has become an integral part of maintaining air superiority. In order to achieve the most advanced engine, research has turned to traditional optimization methods to aid in creating new engine designs. To develop simplified mathematical models representative of the engine, the engine can be separated into its components. A jet engine has three major elements, the compressor, combustion chamber and turbine. This research attempts to ... |
|
| Effects of Stator Indexing on Performance in a Low Speed Multistage Axial Compressor |
AUG 97 |
12 pages |
| Authors:
Wendy S. Barankiewicz; Michael D. Hathaway; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
|
| The results of an experimental investigation to determine the impact of stator row indexing or clocking on multistage axial compressor performance are presented. Testing was conducted in the NASA Lewis Research Center's Four- Stage Axial Compressor Facility. The impact of stator row indexing on both the overall and stator 3 blade element performance is presented for both the peak efficiency and peak pressure operating conditions. The change in overall performance ... |
|
| Adaptation of a Three-Dimensional Numerical Simulation to Represent Gas Turbine Engine Compression Systems |
APR 97 |
86 pages |
| Authors:
Jacqueline C. Chalk; SVERDRUP TECHNOLOGY INC ARNOLD AFS TN
|
| A new three-dimensional compression system simulation was constructed by coupling the three-dimensional Navier Stokes flow solver, NPARC, with source terms that model the effects of turbomachinery components. A stage by stage characteristic technique adapted from the one-dimensional compressor code, DYNTECC, was used to calculate the turbomachinery source terms. This report discusses the development, adaptation, and implementation of the stage characteristic approach for calculating sources used in NPARC. The distribution of ... |
|
| Turbulence Flame Interactions - AASERT |
APR 96 |
8 pages |
| Authors:
D. A. Santavicca; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL ENGINEERING
|
| Two students were supported under the Department of Defense Augmentation Awards for Science and Engineering Research Training (AASERT) program. Mr. Mark McMurray was supported from 15 August 1992 through 14 August 1994, and Mr. Christopher Jones was supported from 15 August 1994 through 14 August 1995. Mark McMurray completed his M.S. degree and accepted employment at Champion Spark Plug Company. Chris Jones expects to complete the requirements for his M. ... |
|
| Laser Anemometry and Viscous Computation of the Flow Through an Annular Turbine Cascade |
MAR 94 |
85 pages |
| Authors:
Joseph D. Spitz; NAVAL POSTGRADUATE SCHOOL MONTEREY CA DEPT OF AERONAUTICS AND ASTRONAUTICS
|
| An annular turbine cascade, designed for laser-Doppler velocimetry , was further modified to provide additional laser and pressure probe access. The purpose of the research was to devise laser anemometry measurement techniques in a confined annulus and improve the ability to compare numerical predictions with experimental results. Flowfield computations were completed using a viscous flow solver, with the numerical exit plane coincident with experimental measurement location. A data reduction program ... |
|
| New Approa;ches in Interferometric SAR Data Processing. |
MAY 1992 |
|
| Authors:
Q. Lin; J. F. Vesecky; H. A. Zebker; STANFORD UNIV CA DEPT OF ELECTRICAL ENGINEERING
|
|
| Optimal Truncation and Optical Efficiency of an Apertured Coherent LIDAR Focused on an Incoherent Backscatter Target. |
MAY 1992 |
|
| Authors:
B. J. Rye; R. G. Frehlich; COLORADO UNIV AT BOULDER
|
|
| Incremental Maneuver Estimation Model for Target Tracking. |
APR 1992 |
|
| Authors:
W. T. Chang; S. A. Lin; NATIONAL CHIAO TUNG UNIV HSINCHU (TAIWAN)
|
|
| Investigation of Hot Streak Migration and Film Cooling Effects on the Heat Transfer in Rotor/Stator Interacting Flows |
15 JUL 91 |
31 pages |
| Authors:
Daniel J. Dorney; Roger L. Davis; UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT THEORETICAL AND COMPUTAT IONAL FLUID DYNAMICS GROUP
|
| The specific objectives of this effort are to extend the three- dimensional rotor/stator interaction code, ROTOR3, to investigate hot streak migration and film cooling effects on the passage flow and blade surface heat transfer for an axial flow turbine stage. These objectives are part of an overall plan to extend the capabilities of this numerical procedure and to determine the potential of this technique to impact the design of future ... |
|
| Investigation of Hot Streak Migration and Film Cooling Effects on the Heat Transfer in Rotor/Stator Interacting Flows |
31 MAR 91 |
|
| Authors:
Daniel J. Dorney; Roger L. Davis; UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT
|
| This effort extended the three-dimensional unsteady rotor/stator interaction code, ROTOR3, to investigate hot streak migration and film cooling effects on the passage flow and blade surface heat transfer for an axial flow turbine stage. These objectives are part of an overall plan to extend the capabilities of this numerical procedure and to determine the potential of this technique to impact the design of future rotating turbomachinery components. The principal benefits ... |
|
| Back-Up Control System for F101 Engine and Its Derivatives. |
03 JAN 1989 |
|
| Authors:
Walter D. Hutto Jr.; William W. Stockton; DEPARTMENT OF THE AIR FORCE WASHINGTON DC
|
| A back-up control system is implemented in a single engine aircraft to provide inactivation of a faulty primary system and engagement of secondary system, and thereby provide a means of maintaining controllable flight sustaining thrust. The aircraft's hydromechanical main engine control and its companion pressure and temperature sensors can develop faults which can result in the inability of the engine to deliver flight sustaining thrust. The electronic control contains logic ... |
|
| Ground Surveillance Radars for the 1990s. |
NOV 1988 |
|
| Authors:
R. Pengelley
|
|
| W-Bank Varactor-Tuned Oscillators with 10 GHz Bandwidth. |
OCT 1988 |
|
| Authors:
|
|
| DC to 20 GHz Monolithic GaAs FET Switches Based on Quarter-Micron Gates. |
AUG 1988 |
|
| Authors:
G. Dawe; D. Bartle; F. Spooner; ALPHA INDUSTRIES INC WOBURN MA
|
|
| Army Expands Requirements for Fiber Optic Guided Missile. |
JUL 1988 |
|
| Authors:
|
|
| NADGE Enhancements Lay Groundwork for ACCS. |
JUL 1988 |
|
| Authors:
T. Hooton
|
|
| The Possum Radar. |
JUL 1988 |
|
| Authors:
M. Hewish
|
|
| Design and Analysis of Slotted Waveguide Antenna Arrays. |
JUN 1988 |
|
| Authors:
P. N. Richardson; H. Y. Yee; TEXAS INSTRUMENTS INC MCKINNEY TX
|
| Slotted waveguide array antennas find application in many microwave communication and radar systems requiring narrow-beam or shaped-beam patterns. They are particularly useful in airborne applications where light weight and small scan volume are important. These antennas may be either resonant or non-resonant arrays of various narrow-wall and broadwall slots. The typical design of a waveguide slot array begins with an examination of the requirements to define the size of the ... |
|
| AGARD Manual on Aeroelasticity in Axial-Flow Turbomachines. Volume 2. Structural Dynamics and Aeroelasticity |
JUN 88 |
|
| Authors:
Max F. Platzer; Franklin O. Carta; ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)
|
| This volume aims to complete the review on the state of the art of unsteady turbomachinery aerodynamics by presenting the state of the art of structural dynamics and of aeroelasticity. The eleven chapters in this second volume give an overview of the subject and reviews of the structural dynamics characteristics and analysis methods applicable to single blades and bladed assemblies. The blade fatigue problem and its assessment methods, and life-time ... |
|
| Visualization of Flows in Turbomachinery |
DEC 87 |
|
| Authors:
I. Ianovici; D. Adler; TECHNION - ISRAEL INST OF TECH HAIFA
|
| A method of gas visualization based on laser induced fluorescence has been theoretically and experimentally investigated. Liquid droplets seeded with fluorescent substance were introduced locally in an air flow. A laser light sheet is used to scan the flow field. The light emitted by fluorescent substance is used to obtain, after filtering the image of a point on specific streamline. The method has been applied to the visualization of streamlines ... |
|
| Visualization of the Flow at the Tip of a High Speed Axial Flow Turbine Rotor Blade - An Assessment of Flow Visualisation Techniques and the Requirement of the Experimental Turbine |
NOV 87 |
|
| Authors:
J. P. Bindon; D. Adler; TECHNION - ISRAEL INST OF TECH HAIFA
|
| The field of flow visualisation has been reviewed and its application to the study of the flow near the tip of an unshrouded axial turbine rotor discussed in detail. The logical conceptualisation of experiments which could lead to a final understanding of the flow structure was developed and how this leads to test turbine design philosophy is suggested. The rotor periodicity shed by the stator requires that particle of pulse ... |
|
| Design and Aerodynamic Performance of a Small Mixed-Flow Gas Generator Turbine, |
SEP 1987 |
|
| Authors:
U. Okapuu; PRATT AND WHITNEY CANADA INC LONGUEUIL (QUEBEC)
|
| Design details and results from aerodynamic rig tests are presented for four variants of a mixed-flow turbine having a design target pressure ratio of 3:1. This experimental turbine, designed to satisfy the aerodynamic requirements of a gas generator turbine in a hypothetical small turboprop engine, demonstrated a design point efficiency substantially in excess of that predicted for a single stage axial turbine of equivalent duty. Design and material implications are ... |
|
| Calculation of the 3-D Viscous Flow at the Endwall Leading Edge Region of an Axial Annular Turbine Cascade |
AUG 1984 |
|
| Authors:
L. Walitt; THERMO MECHANICAL SYSTEMS CO CANOGA PARK CALIF
|
| A three-dimensional viscous computer code (VANS/MD) was employed to calculate the turbulent flow field at the end wall leading edge region of a 20 inch axial annular turbine cascade. The initial boundary layer roll-up and formation of the end wall vortices were computed at the vane leading edge. The calculated flow field was found to be periodic with a frequency of approximately 1600 Hz. The calculated size of the separation ... |
|
| Secondary Flows and Losses in a Turbine Cascade, |
SEP 1983 |
|
| Authors:
D. G. Gregory-Smith; C. P. Graves; DURHAM UNIV (ENGLAND) DEPT OF ENGINEERING
|
| In designing axial flow turbines, one needs relatively simple prediction techniques for the angle variations and losses produced by secondary flows. To improve the physical basis of such techniques, an investigation was made of the flow in a cascade of large scale rotor blades of some 110 deg of turning. The aspect around 0.2 of the span. The flow was traversed in great detailed on ten planes using cobra-type probes ... |
|
| A Viscid Inviscid Interaction Procedure for Two Dimensional Cascades, |
SEP 1983 |
|
| Authors:
P. Janssens; C. Hirsch; VRIJE UNIVERSITEIT BRUSSEL (BELGIUM) DEPT OF FLUID MECHANICS
|
| A viscous inviscid interaction scheme was developed to predict fluid turning and loss coefficients for arbitrary cascade bladings of axial and centrifugal turbomachines. The effects of the blade surface boundary layers, separation of these boundary layers and the wake downstream of the trailing edge are taken into account by the wake displacement body method. The effective separation line between the inviscid outer flow, separated boundary layers and the wake is ... |
|
| APU (Auxiliary Power Unit) in Commercial Airline Operation, |
SEP 1983 |
|
| Authors:
H. W. C. L. Schoevers; A. Booy; KLM ROYAL DUTCH AIRLINES AMSTERDAM (NETHERLANDS)
|
| Knowing that the APU is the most expensive support device, the temptation is strong to entirely remove it from commercial transports. Adverse consequences of such action include: Loss of the APU puts the burden on the ground equipment, of which the maintenance at the line stations sometimes leaves much to be desired; For some stations the removal of the APU could require a sizeable investment of ground support equipment; Loss ... |
|
| Numerical Algorithm for Rapid Integration of Turbulence-Model Equations on Elliptic Regions |
FEB 1982 |
|
| Authors:
David C. Wilcox; DCW INDUSTRIES INC STUDIO CITY CA
|
| A numerical algorithm suitable for rapid numerical solution of advanced turbulence-model equations on elliptic regions has been devised. The algorithm is particularly useful for obtaining accurate solutions when (a) one of the dependent variables is singular approaching a solid boundary, and (b) the number of mesh points available to resolve the flowfield is small. The new algorithm is used in conjunction with the MacCormack semi-implicit scheme for solving the time-averaged ... |
|
| Research on Turbine Rotor-Stator Aerodynamic Interaction and Rotor Negative Incidence Stall |
NOV 1981 |
|
| Authors:
R. P. Dring; H. D. Joslyn; L. W. Hardin; J. H. Wagner; UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT
|
| The aerodynamic interaction between the rotors and stators of a large scale axial turbine stage have been studied experimentally. The data included measurements of the time averaged and instantaneous surface pressures and surface thin film gage output on both the rotor and stator at midspan. The data also included measurement of the stator suction and pressure surface time averaged heat transfer at midspan. The data was acquired with rotor-stator axial ... |
|
| Expendable Gasifier |
MAR 1981 |
|
| Authors:
Al Gabrys; Hans Due; TELEDYNE CAE TOLEDO OH
|
| The expendable gasifier provides, in a single cost-effective configuration, the core for either a jet fuel starter or a thrust engine for remotely piloted vehicles (RPV's). The gasifier is 12.9 inches in diameter, 18.6 inches long, weighs 78 pounds, and consists of a four-stage axial compressor, a reverse-flow annular vaporizer combustor, a single stage axial turbine and a bearing system that supports the main shaft. The expendable gasifier was designed, ... |
|
| Measurement and Analysis of the Periodic Variation of Total Pressure in an Axial-Flow Compressor Stage. |
NOV 1980 |
|
| Authors:
William C. Zierke; Theodore H. Okiishi; IOWA STATE UNIV AMES ENGINEERING RESEARCH INST
|
| A fast-response, total-pressure probe was used with a periodically sampling and averaging data acquisition system to study the unsteady total-pressure field in an axial-flow turbomachine. Periodically unsteady total-pressure data were used to demonstrate some of the ways in which turbomachine blade wake transport and interaction influences the energy transfer involved. Observed trends of periodic variations in local total pressures could be explained in terms of the details of energy transfer ... |
|
| Computer Program for Generating Input for Analysis of Impingement-Cooled, Axial-flow Turbine Blade. |
JAN 1980 |
|
| Authors:
David Rosenbaum; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OHIO LEWIS RESEARCH CENTER
|
| A computer program called TACTGRID has been developed that generates the geometrical input for the TACT1 program, a program that calculates transient and steady-state temperatures, pressures, and cooling flows in an impingement-cooled turbine blade. Using spline curves, the TACTGRID program constructs the blade internal geometry from the previously designed external blade surface and newly selected wall and channel thicknesses. TACTGRID generates the TACT1 calculational grid, calculates arc lengths between grid ... |
|
| Imbedded Longitudinal Vortices in Turbulent Boundary Layers, |
1980 |
|
| Authors:
R. D. Mehta; I. M. M. A. Shabaka; P. Bradshaw; IMPERIAL COLL OF SCIENCE AND TECHNOLOGY LONDON (ENGLAND) DEPT OF AERONAUTICS
|
| Measurements, including all Reynolds stresses and triple products, have been made in three turbulent flows with imbedded longitudinal vortices generated by skewing of the mean flow ('secondary flow of the first kind') (i) flow in an idealized wing-body junction, (ii) an isolated vortex in a two-dimensional boundary layer, and (iii) a vortex pair in a turbulent boundary layer. Selected results are presented: spatial variations of eddy diffusivities and dimensionless modelling ... |
|
| Development of a Viscous Theory of Three-Dimensional Flow in Highly-Loaded Axial Turbomachines. |
JUN 1979 |
|
| Authors:
David C. Wilcox; DCW INDUSTRIES INC STUDIO CITY CA
|
| A computer program is being developed which will be suitable for numerically simulating three-dimensional viscous flow in rotating turbomachines. This report summarizes progress to date and gives projections of work to be accomplished during the next year. (Author) |
|
| New Concepts in Ship Directional Control, |
14 MAY 1979 |
|
| Authors:
Herman E. Sheets; Tadeusz Kowalski; RHODE ISLAND UNIV KINGSTON DEPT OF OCEAN ENGINEERING
|
| A new propulsion system for ships has been discussed in Sheets (1978). This propulsion system provides a source of pressurized water between the pump and the turbine of the hydraulic transmission and generates a water jet leaving the transmission turbine. The water jet leaving the transmission turbine can be vectored by means of discharge vanes so that it is possible to greatly improve the directional controllability of ships. Several configurations ... |
|
| Multistage Axial-Flow Turbomachine Wake Production Transport and Interaction |
FEB 79 |
9 pages |
| Authors:
Theordore H. Okiishi; IOWA STATE UNIV AMES ENGINEERING RESEARCH INST
|
| Procedures and instrumentation for acquiring time-average (slow response average of continuously sampled data) and periodic-average (electronic and arithmetic average of periodically sampled data) flow field data between blade rows of a research turbomachine were developed. Slow and fast-response total pressure probes and hot-wire anemometry were involved. A special 5 microsec sampling and holding circuit that could be phase locked to reference rotor blade position was designed and built. Two-dimensional time-average ... |
|
| A Streamline Curvature Method of Analyzing Axisymmetric Axial, Mixed and Radial Flow Turbomachinery. |
21 JUL 1977 |
|
| Authors:
M. W. McBride; PENNSYLVANIA STATE UNIV UNIVERSITY PARK APPLIED RESEARCH LAB
|
| A Streamline Curvature Method of through flow analysis for axisymmetric axial, mixed and radial flow turbomachinery has been implemented. The method can be used for either the direct or indirect problem and can solve open flow problems such as flow through a propeller on a body of revolution as well as the more familiar duct flow problems. Computational refinements allow modeling of blade row chordwise and spanwise loading and blockage ... |
|
| Compact Closed Cycle Brayton System Feasibility Study. |
JUL 1977 |
|
| Authors:
R. E. Thompson; G. H. Parker; R. L. Ammon; F. R. Spurrier; B. L. Pierce; WESTINGHOUSE ELECTRIC CORP PITTSBURGH PA ADVANCED ENERGY SYSTEMS DIV
|
| This report presents the feasibility of a closed Brayton cycle power conversion system for compact light weight naval propulsion plants. Reference case requirements have been established, including a unit output of 70,000 horsepower, turbine inlet gas temperature of 1700 F, and use of helium as the working fluid. Critical components such as bearings and compact heat exchangers have been evaluated and shown to have more than one suitable design solution. ... |
|
| Advanced Small Axial Turbine Technology. |
MAY 1977 |
|
| Authors:
H. F. Due Jr.; C. Rogo; C. L. Kosier; G. B. Jasas ; TELEDYNE CAE TOLEDO OHIO
|
| The objective of the program was to provide the advanced technolgoy small axial-flow turbine designer with empirically derived techniques to improve the accuracy of predicting losses, flow condition, velocity triangles and design point matching. The techniques addressed practical mechanical constraints typical of small, highly loaded cooled turbines, such as: (1) cooling system type and injection method or location, (2) blade fabrication, (3) wall thickness and tolerances, (4) engine integration requirements, ... |
|
| Determination of Rotor and Stator Loss Coefficients for an Axial Turbine with Supersonic Stator Exit Conditions. |
JUN 1976 |
|
| Authors:
Edward Franklin Robbins; NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
|
| The results of seven different tests of a single stage axial turbine with converging-diverging stator nozzle are reported. From measurements in a special test rig, losses occurring in the stator and rotor blade rows were separately calculated and the performance of the stage was also determined. The rotor speeds varied from 9,500 to 18,600 r.p.m. and the pressure ratios varied from 1.75 to 3.25. The Mach numbers at the stator ... |
|
| Development of Emissions Measurement Techniques for Afterburning Turbine Engines, Supplement 1 Engine Emissions Test Data. |
OCT 1975 |
|
| Authors:
T. F. Lyon; GENERAL ELECTRIC CO CINCINNATI OHIO AIRCRAFT ENGINE GROUP
|
| Comprehensive emissions test data taken throughout the exhaust plumes of J85-5 and J79-15 afterburning engines. Measurements were obtained on both engines at four power settings (military, minimum A/B, intermediate A/B, and maximum A/B) and five axial stations (0, 3, 6, 12 and 24 nozzle diameters downstream). (Author) |
|
| Axial Flow Rotor Unsteady Response to Circumferential Inflow Distortions. |
13 AUG 1975 |
|
| Authors:
E. P. Bruce; R. E. Henderson; PENNSYLVANIA STATE UNIV UNIVERSITY PARK APPLIED RESEARCH LAB
|
| The unsteady response of an axial flow fan rotor to steady, circumferential inflow velocity distortions has been evaluated by investigation of the unsteady normal force and pitching moment on a chordwise element of a rotor blade. Experimental measurements of these unsteady characteristics are presented as a function of the geometry of the rotor -- stagger angle, solidity and steady angle of incidence -- for sinusoidally varying circumferential distortions with different ... |
|
| Turbulence in Free Diffusion Flames of Hydrogen-Nitrogen Mixtures Burning in Still Air. |
JUN 1975 |
|
| Authors:
Roger R. Craig; AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
|
| The research undertaken in this report deals with the measurement of time averaged flow variables and turbulence intensities in turbulent diffusion flames. The difficulties encountered in separating the effects of temperature, velocity and species concentration on a hot-film anemometer signal required the use of special techniques for measuring the turbulence in the diffusion flames. Results obtained in an axisymmetric air jet are compared with data obtained from a crossed hot-film ... |
|
| Multimission Aircraft Propulsion Simulator Initial Aero/Mechanical Test Results and Evaluation. |
DEC 1973 |
|
| Authors:
Bobby R. Delaney; Har West; GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP
|
| Initial aero/mechanical tests of the Multi-Mission Aircraft Propulsion Simulator were conducted in the AEDC R2C4 Test Cell of the engine test facility. A total of 38.1 hours of successful operation was completed. The simulator is designed with a compressor, turbine and mixer which result in the capability of simultaneously simulating scaled inlet airflow, nozzle pressure ratio and nozzle flow function which significantly improves scale model simulation. The simulator utilizes mass ... |
|
| Influence of Variable Turbine Geometry on Engine Installation Losses and Cycle Selection. |
JUN 1973 |
|
| Authors:
Robert J. May Jr.; William F. Zavatkay; PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
|
| The trend in military aircraft is toward increasing thrust loading for improved maneuverability coupled with a requirement for extended subsonic cruise range at low power settings. Conventional turbine engines designed to meet these requirements must operate over large ranges of airflow between maximum power and cruise. As a result, the inlets and nozzles designed for these engines cannot perform efficiently with the low airflow rates typical of subsonic cruise operation. ... |
|
| Generalized Performance Limits for Propellers, Windmills and Lifting Rotors with Axes Parallel to the Undisturbed Flow. |
DEC 1972 |
|
| Authors:
Theodore H. Gawain; NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
|
| The report generalizes the classical momentum theory as usually applied to propellers, windmills and lifting rotors into a single unified treatment. It also extends the analysis to include the regime in which flow through part or all of the actuator disc is reversed with respect to the remote flow field. Dimensional analysis is used in a systematic manner to reduce the final results to their simplest and most significant forms. ... |
|
| Three-Dimensional, Inviscid Flow Analysis, Phase II. |
MAY 1972 |
|
| Authors:
H. F. Creveling; GENERAL MOTORS CORP INDIANAPOLIS IND DETROIT DIESEL ALLISON DIV
|
| A report is made on flow analysis efforts dedicated to the development of analytical prediction techniques for fluid flow in turbomachinery based upon the controlling physical phenomena and verified by key critical experiments. These efforts offer a new approach to aerodynamic design that significantly reduces expensive hardware testing. |
|
| Feasibility Study for a Practical High Rotor Tip Clearance Turbine. |
29 FEB 1972 |
|
| Authors:
Dennis C. Evans; Timothy C. Prince; GENERAL ELECTRIC CO CINCINNATI OH AIRCRAFT ENGINE BUSINESS GROUP
|
| Turbine tip clearance loss prediction methods were investigated analytically. Vector diagram variations, flow path wall curvature, and stator tangential lean and axial sweep affect the magnitude of this loss for given turbine design requirements and tip clearance. For a model core turbine, a potential 30% reduction in clearance loss relative to an equivalent free vortex turbine is predicted for a practical application of these variations. A follow-on investigation is proposed. ... |
|
Reports by Keyword(s)
AXIAL FLOW TURBINES
