Study of stator-vane fluctuating pressures in a turbofan engine for static and flight tests

by Arnold W. Mueller

Publisher: National Aeronautics and Space Administration, Scientific and Technical Information Branch, Publisher: For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va

Written in English
Published: Pages: 51 Downloads: 99
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  • Airplanes -- Noise.,
  • Airplanes -- Turbine-propeller engines.
  • Edition Notes

    StatementArnold W. Mueller.
    SeriesNASA technical paper -- 2217.
    ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
    The Physical Object
    Pagination51 p. :
    Number of Pages51
    ID Numbers
    Open LibraryOL18040216M

From takeoff to a flight Mach number of , the transport system is powered by a LARZAC twin spool turbofan engine with a bypass ratio (see Fig. ). The engine genera N thrust, and is provided with a two-stage transonic LP compressor, a four-stage high-pressure compressor, and single-stage high- and low-pressure turbines.   Predicting broadband noise from a stator vane of a gas turbine engine. NASA Technical Reports Server (NTRS) Hanson, Donald B. (Inventor) A computer-implemented model of fan section of a gas turbine engine accounts for the turbulence in the gas flow emanating from the rotor assembly and impinging upon an inlet to the stator vane cascade. The most significant difference between the rotary and the static radial engine is that with the static engine, the crankcase remains stationary and the crankshaft rotates to turn the propeller. Static radial engines have as few as three cylinders and as many as The higher horsepower engines proved most useful. Static pressure is admitted to the pressure head through slots or holes cut into the static casing at 90° to the airflow, whilst pitot pressure enters the head via the pitot input port that faces directly into the airflow. The different pressures are fed to the flight instruments via separate, seamless, and corrosion-resistant metal : Sadcat.

Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats. Some of the most comprehensive tests made of diffuser performance were those of Stevens and Williams () who included traverses of the flow at inlet and at exit as well as careful measurements of the static pressure increase and total pressure loss in low speed tests on annular diffusers. NaG Pagina 1 N A DAGA Rotterdam NAG/DAGA NAG/DAGA – Rotterdam International Conference on Acoustics Rotterdam 23 – 26 March PROGRAM nederlands akoestisch genootschap NAG Program NAG/DAGA 1 NAG/DAGA International Conference on Acoustics, Rotterdam including the Option C. facilitate flight line inspection of engine inlet and compressor areas for defects or FOD. Correct Answer is. prevent engine performance degradation, increased fuel costs, and damage or corrosion to gas path : Kiki_D.

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Study of stator-vane fluctuating pressures in a turbofan engine for static and flight tests by Arnold W. Mueller Download PDF EPUB FB2

NASA Technical Paper 7 April NASA j TP i c.1 i I I Study of Stator-Vane Fluctuating Pressures in a Turbofan Engine for Static and Flight Tests Arnold W. Mueller LOAN COPY: RETURN TO AFWL TECttNlCAL LIBRARY KIRTlAND AFB, N.M.

Study of stator-vane fluctuating pressures in a turbofan engine for static and flight tests. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.: For sale by the National Technical Information Service], (OCoLC) Material Type.

Variable inlet guide vanes and stator vane- installed so angle of attack is changed at low engine speed. Maintains the velocity of the air within acceptable limits for low airflow conditions Dual/twin/split-spool axial flow compressors - allows front rotor to turn at a slower RPM than the rear rotor which allows front rotor to turn without.

Start studying Turbine Engine. Learn vocabulary, terms, and more with flashcards, games, and other study tools. Search. What is the function of the stator vane assembly at the discharge end of a typical axial-flow compressor.

At what stage in. Compressor stator vanes whose angle can be varied. The angle is controlled by the fuel-control unit. Varying the stator-vane angle ensures that the air directed to the first stage of the compressor meets the compressor at an optimum angle and thus minimizes the possibility of a compressor stall.

Turbofan Broadband Noise Prediction using the Lattice Boltzmann Method of a complete turbofan engine noise 6, 5 and full on the stator vane surfaces. Such a study. The design of the static structure in a gas turbine is extremely complex since all the services required to run an engine need to pass through - such things as oil pressure and scavange, seal pressure balance air etc etc Not as obvious.

Aerodynamic loading acting on the stator vane in the variable the engine control management, the engine vibrations, and the flow pulsations on measured values. A comparison independence study to find out the best trade off between the computational time and precision. Japan Airlines said on 13 August that the aircraft engine had apparently taken damage to its turbine blades and stator vanes.

Japan Airlines is to investigate the cause of the accident in cooperation with Pratt & Whitney, reported. Heat Transfer in a Stator Vane Passage Using the v2−f Turbulence Model In this study three-dimensional simulations of a stator vane passage flow have been performed using the v2−f turbulence model.

Both an in-house code (CALC-BFC) and the commercial software FLUENT are used. The main objective is to investigate the v2−f. Stator Vane Geometry. Simulations are carried out with three symmetric vanes and two asymmetric vanes. Vane shapes similar to asymmetric vanes 1 and 2 are commercially in use by turbocharger manufacturers and are used in this work for study purpose only.

Figure 1 shows different vane shapes used for this by: 1. TURBOFAN ENGINES Consist of a multi-bladed ducted propeller driven by a gas turbine engine. Provide a compromise between the best features of the turbojet and the turboprop. Have turbojet-type cruise speed capability, yet retain some of the short-field takeoff capability of a turboprop.

InternationalJournalofRotatingMachinery 1 Normalized isentropic eciency Mesh count, millions F: Grid independence test. The purpose of investigations, which was carried out on real engine was determination influence of incorrect operation of axial compressor inlet guide variable stator vanes control system of gas turbine engine on compressor and engine work parameters.

The object of research is type DR 77 marine gas turbine engine, which is a part of. A 'read' is counted each time someone views a publication summary (such as the title, abstract, and list of authors), clicks on a figure, or views or downloads the full-text. A typical bypass turbofan engine also has a low pressure turbine aft of the gas generator and a forward fan forward of the gas generator.

Where the gas generator is a core engine, a typical bypass turbofan engine adds a low pressure turbine aft of the high pressure turbine and adds a forward fan forward of the high pressure compressor. Library of Congress Cataloging-in-Publication Data (Revised for vol.

8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C. Bruno. Vol. 8 in series: The NASA historical data book series. Includes bibliographical references and indexes. Full text of "ERIC ED Flight Engineer.

Question Book. Expires September 1, " See other formats. How Are The Variable Stator Vanes In A Gas Turbine Controlled The vane actuating apparatus is used to adjust the angle of incidence of a set of variable vanes in the gas turbine engines come with the plurality of the vane actuator levels.

They are attached to one end to a respective vane and at the other end to an actuation arrangement for. Total pressure is static plus dynamic pressure.

A compressor will increase both (total and static pressure) together. Note that the flow speed in the different compressor stages is nearly constant and the flow is only decelerated for combustion after the last compressor stage in an area called diffusor. The flow speed in the compressor is chosen such that you just avoid supersonic flow.

Full text of "NASA Technical Reports Server (NTRS) A cumulative index to the issues of Aeronautical Engineering" See other formats. The dynamic and static pressure distributions around the stator vane and the rotor blade were evaluated. According to the fluid flow analysis, the values of total forces exerted on the rotor by gas (the aerodynamic forces) in x, y and z directions are estimated to be: 0, − and kPa, respectively [16].Cited by: Answer A.

AC A On a dual axial or dual spool turbofan engine, the forward fan is typically bolted to the first compressor making the fan part of the low-pressure compressor. On some turbofan engines, the fan is mounted aft of the turbine wheel but never forward of it.

The discussion of issues related to the introduction and use of flow and noise control technologies on submarines provided a historical overview, the design process, and a small percentage of the operational issues. A parallel discussion of air platforms would highlight many of the same issues, or challenges, for flow and noise control Cited by: Full text of "NASA scientific and technical publications: A catalog of Special Publications, Reference Publications, Conference Publications, and.

EPA/b January ABSTRACTS OF THE UNITED STATES AND FOREIGN OPEN LITERATURE ON NOISE Task Report J Part II by E. Bergmann I. Fieldhouse Contract Project Officer E. Berkau U.S. Environmental Protection Agency Industrial Environmental Research Lab.

Cincinnati, Ohio Prepared for Environmental. NASA Historical Data Book Vol. 8 - Free ebook download as PDF File .pdf), Text File .txt) or read book online for free. NASA earth science and space applications, aeronautics,technology and exploration, tracking and data acquisition/space operations, facilities and 5/5(1).

O Scribd é o maior site social de leitura e publicação do mundo. Gill, “A Text Book of Engineering Drawing”, S.

Kataria and Sons, India 6. Dhawan, “A Text Book of Engineering Drawing”, S. Chand and Company Limited, India Evaluation Scheme: The questions will cover all the chapters in the syllabus.

The evaluation scheme will be as indicated in the table below: Unit Chapter Topics MarksFile Size: 2MB. Patent application title: Gas turbine engine compressor variable stator vane arrangement Inventors: Arthur L.

Rowe (Derby, GB) Marc Pons Perez (Derby, GB) Cerith Davies (Uttoxeter, GB) Assignees: ROLLS-ROYCE PLC IPC8 Class: AF01DFI USPC Class: Class name: Rotary kinetic fluid motors or pumps including means to cause cyclical movement of a.

The stator vane is not spinning itself, but is placed into a rotating flow, such that the flow around it is very similar to that of a wing or a propeller blade. The rotational flow component is transformed into an axial acceleration which in turn is converted into ram pressure by the narrowing flow path in a compressor.

Hot spot detection system for vanes or blades of a combustion turbine. DOEpatents. Twerdochlib, M. This invention includes a detection system that can determine if a turbine component, such as a turbine vane or blade, has exceeded a critical temperature, such as a melting point, along any point along the entire surface of the vane or.

The vane actuating apparatus is used to adjust the angle of incidence of a set of variable vanes in the gas turbine engines come with the plurality of the vane actuator levels.