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Inlet And Diffuser Effects On Thrust Augmenting Ejectors
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Book Synopsis Inlet and Diffuser Effects on Thrust Augmenting Ejectors by : S. G. Reznick
Download or read book Inlet and Diffuser Effects on Thrust Augmenting Ejectors written by S. G. Reznick and published by . This book was released on 1982 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: Effects of primary jet inlet nozzle configuration and diffuser geometry on the thrust augmentation of circular and rectangular ejectors are investigated in an experimental study. The rectangular ejector inlet nozzle configurations consist of either one, two, or three slot nozzles. The circular ejector inlet nozzles consist of slot nozzles placed either across the inlet or around the inlet periphery. Diffuser geometry is varied primarily by changing the diffuser area ratio. Effect on thrust performance of the primary flow injection angle relative to the inlet walls is investigated. Effects of side-wall, end-wall, and diffuser blowing on thrust performance and diffuser stall also are considered.
Book Synopsis Workshop on Thrust Augmenting Ejectors by :
Download or read book Workshop on Thrust Augmenting Ejectors written by and published by . This book was released on 1979 with total page 524 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of a Circular Thrust Augmenting Ejector by : Generoso C. Uhuad
Download or read book An Experimental Investigation of a Circular Thrust Augmenting Ejector written by Generoso C. Uhuad and published by . This book was released on 1985 with total page 115 pages. Available in PDF, EPUB and Kindle. Book excerpt: A 4.4 in diameter circular ejector was tested to determine the effect on thrust augmentation ratio of the primary nozzle height and injection angle. Also tested were the effects of alternating primary nozzle injection angles, diffuser blowing and suction, inlet cross flow and low primary nozzle exit velocities on thrust augmentation. The results showed that both the primary nozzle injection angle and height affect the maximum thrust augmentation ratio attainable. A small amount of cross flow at the inlet increased the maximum thrust augmentation. The alternating primary nozzle injection angle arrangement did not increase the maximum thrust augmentation above that which was obtained using uniform primary nozzle injection angles. Diffuser blowing or suction did not provide an improvement in the maximum thrust augmentation above that which was obtained without diffuser boundary layer control. Finally, at low primary nozzle exit velocities, thrust augmentation increase as the nozzles were moved out along the inlet surface. The increase in thrust augmentation is attributed to the ability of the flow to remain attached to the inlet surface at low primary nozzle exit velocities thereby increasing the ejector effective mixing chamber length. (Author).
Book Synopsis Analysis and Design of Ejector Diffuser for Optimum Thrust by : Tsze C. Tai
Download or read book Analysis and Design of Ejector Diffuser for Optimum Thrust written by Tsze C. Tai and published by . This book was released on 1976 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: Recent advances in jet ejectors operating under static conditions have produced high thrust augmentation that is feasible for application to V/STOL flight. However, because of (a) loss in augmentation in duct flow, (b) ramjet effect, and (c) space limitations, high performance and compactness are required in the design of thrust-augmenting ejectors for V/STOL aircraft. An analytical inverse approach is presented in which the pressure distribution along the diffuser wall of an ejector is defined for a given entrance flow condition and the contour of the desired diffuser wall is determined by using a finite difference technique. The prescribed pressure distribution is first optimized by a modified Stratford criterion for incipient separation of turbulent boundary layers; this optimization makes it applicable to compressible two-dimensional and axisymmetric flows.
Book Synopsis An Experimental Study of Rectangular and Circular Thrust Augmenting Ejectors by :
Download or read book An Experimental Study of Rectangular and Circular Thrust Augmenting Ejectors written by and published by . This book was released on 1981 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: A short rectangular ejector and two circular ejectors were tested to determine the effects of primary nozzle configuration and geometry on thrust augmentation. The primary nozzle configurations consisted primarily of slot nozzles which injected fluid parallel to the diffuser walls and achieved Coanda type flow at the throat. Results of the rectangular ejector tests indicate that thin plates installed in the mixing chamber or the diffuser, increase mixing but decrease thrust augmentation. A continuous slot nozzle, modified to create four discrete jets at the inlet, improved mixing and thrust augmentation compared to the original design. Thrust augmentation ratio increased from 1.4 to 1.58. The circular ejector primary nozzles consisted of a continuous slot 'torus' nozzle and individual slot nozzles which could be symmetrically placed around the inlet periphery. A nozzle configuration using 16 slot nozzles on the periphery of the inlet face gave the best performance. A thrust augmentation ratio of 2.0 was achieved.
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781731496843 Total Pages :170 pages Book Rating :4.4/5 (968 download)
Book Synopsis A Control-Volume Method for Analysis of Unsteady Thrust Augmenting Ejector Flows by : National Aeronautics and Space Adm Nasa
Download or read book A Control-Volume Method for Analysis of Unsteady Thrust Augmenting Ejector Flows written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-21 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method for predicting transient thrust augmenting ejector characteristics is presented. The analysis blends classic self-similar turbulent jet descriptions with a control volume mixing region discretization to solicit transient effects in a new way. Division of the ejector into an inlet, diffuser, and mixing region corresponds with the assumption of viscous-dominated phenomenon in the latter. Inlet and diffuser analyses are simplified by a quasi-steady analysis, justified by the assumptions that pressure is the forcing function in those regions. Details of the theoretical foundation, the solution algorithm, and sample calculations are given. Drummond, Colin K. COMPUTATIONAL FLUID DYNAMICS; COMPUTERIZED SIMULATION; EJECTORS; FINITE VOLUME METHOD; MATHEMATICAL MODELS; THRUST AUGMENTATION; TURBULENT JETS; UNSTEADY FLOW; ALGORITHMS; INLET FLOW; PREDICTION ANALYSIS TECHNIQUES; REAL TIME OPERATION...
Book Synopsis Applicability of Thrust Augmenting Ejectors in a Supersonic Cruise Configuration by : Wendell S. Hertzelle
Download or read book Applicability of Thrust Augmenting Ejectors in a Supersonic Cruise Configuration written by Wendell S. Hertzelle and published by . This book was released on 1997-04-01 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: Thrust augmenting ejectors were analyzed by the author in an attempt to see if they could be used to provide a significant thrust increase over the baseline thrust of a primary core. This was done for the purpose of determining if leaving the ejectors open in the cruise configuration of the High Speed Civil Transport would lead to a thrust increase that would at least offset the weight of the ejectors themselves. If this was found to be true then the fuel economy of the HSCT might be improved by leaving them open and not closing them during cruise. In analyzing the ejectors, no assumptions were made regarding inlet nor outlet configurations, so an attempt was made to find the point of optimal thrust augmentation by varying secondary stream bypass Mach number and the amount of flow entrainment. Two solutions were found to each mixing scenario, one subsonic and the other supersonic. These two solutions were each analyzed and ones not satisfying the Second Law of Thermodynamics were eliminated. Analytic diffuser and bleed losses were also explored in the analysis of the ejector flow. Within the limitations of the assumptions discussed in this paper, appreciable thrust augmentations have been discovered over a large range of bypass Mach numbers and entrained mass flows. This lead the author to the conclusion that ejectors warrant further research beyond a first order analysis, and serious thought should be put into leaving them open in cruise.
Book Synopsis Performance of Thrust Augmenting Ejectors by : Paul Allen Van
Download or read book Performance of Thrust Augmenting Ejectors written by Paul Allen Van and published by . This book was released on 1971 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of Thrust Augmenting Ejectors by :
Download or read book An Experimental Study of Thrust Augmenting Ejectors written by and published by . This book was released on 1983 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: An automated thrust augmentation data acquisition facility was designed and constructed. The facility provides the capability of measuring thrust augmentation ratio and mass flow augmentation ratio. A three dimensional graphics plot of exit flow is provided for flow analysis. Tests were conducted on a 4.4 in. diameter circular ejector, with eight primary nozzles mounted symmetrically along the perimeter of the inlet. A fixed ejector geometry was used. The ratio of mixing chamber area to diffuser exit area was 1.88. The fluid injection angle, measured from a line perpendicular to the ejector centerline, was varied and the thrust augmentation and mass flow augmentation ratios calculated. Both thrust augmentation and mass flow augmentation increased with fluid injection angle to the stall point where both decreased. Axial flow symmetry of primary air was found to affect stall along diffuser walls.
Book Synopsis Steady Flow Ejector Research Program by : Lockheed-Georgia Company
Download or read book Steady Flow Ejector Research Program written by Lockheed-Georgia Company and published by . This book was released on 1961 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted to determine the jet thrust augmentation under static conditions for rectangular parallel-divergent wall ejector configurations with multiple primary nozzles. The effect of various geometrical and flow parameters were investigated in order to provide design information. Parameters investigated included the ratio of the ejector exit area to the primary nozzle area, the diffuser angle, the mixing section length, the primary nozzle position, the entrance radius, the number of primary nozzle rows, and the primary nozzle pressure ratio and temperature ratio. The test results are generalized to obtain curves relating the augmentation factor to ejector geometry and flow parameters over a wide range of ejector exit to primary nozzle area ratios. (Author).
Book Synopsis An Experimental Study of Static Thrust Augmentation Using a 2-D Variable Ejector by : Eli Kedem
Download or read book An Experimental Study of Static Thrust Augmentation Using a 2-D Variable Ejector written by Eli Kedem and published by . This book was released on 1979 with total page 97 pages. Available in PDF, EPUB and Kindle. Book excerpt: A short rectangular throat ejector was constructed and tested to determine the effects of a number of variables on thrust augmentation and mass augmentation. The variables included those associated with geometry (e.g., diffuser length/throat length, diffuser area ratio, diffuser sidewall angle, nozzle angles and positions) and those due to differences in primary mass flow rate distributions among the nozzles. There were two kinds of thrust augmentation that were calculated; the free thrust augmenting ratio and the isentropic thrust augmenting ratio. The free thrust augmenting ratio is the ratio of the ejector's measured thrust to the sum of the nozzles' measured thrust, if each of them were discharged separately to ambient pressure. The isentropic thrust augmenting ratio is the ratio of the ejector's measured thrust to the calculated thrust of the nozzles if discharged isentropically to the ambient pressure. A free thrust augmentating ratio as high as 1.63 and an isentropic thrust augmenting ratio of up to 1.29 were obtained. Mass augmentation which is the ratio of secondary flow to primary flow was in the range of 3.5 to 5. Some conclusions concerning design aspects were drawn also. They include the necessity of 3-D shrouding for the ejector's inlet and exit and the prevention of blowing high velocity air (primary and BLC flow) tangential to the ejector walls. (AUthor).
Book Synopsis Experimental Investigation of High Performance, Short, Thrust Augmenting Ejectors by :
Download or read book Experimental Investigation of High Performance, Short, Thrust Augmenting Ejectors written by and published by . This book was released on 1983 with total page 69 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an experimental investigation concerning the design and testing of air-to-air thrust augmenting ejectors utilizing short curved-wall diffusers are presented. These ejectors were designed primarily according to the procedure established in an analytical research effort sponsored by DTNSRDC from 1980-1981. Two of the three ejectors tested have identical mixing chambers. The mixing chamber inlet area to the primary nozzle area ratio lambda was 40. The overall ejector length-to-mixing chamber diameter ratios L/D(overall) were 6.09 and 6.16; diffuser area ratios AR(diff) were 1.33 and 1.46, respectively. The third ejector had an L/D(overall) of 6.02, a lambda of 20 and an AR(diff) of 1. 26. The best observed thrust augmentation ratio phi and the modified thrust augmentation ratio phi sub 2 were 2.11 and 1.91 respectively for a sonic primary jet. The modified thrust augmentation ratio phi sub 2 accounts for the penalty of suction in preventing flow separation in the diffuser. These levels of thrust ratio were derived from velocity measurements at the ejector exit. Independent thrust measurements obtained with strain gages on the mixing chamber agree with the force calculated from the momentum data. The experimentally observed ejector performance data correlated well with the predicted values. (Author).
Download or read book Proceedings written by R. P. Braden and published by . This book was released on 1982 with total page 1094 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Coanda Inlet/Jet Flap Diffuser Ejector by :
Download or read book A Coanda Inlet/Jet Flap Diffuser Ejector written by and published by . This book was released on 1972 with total page 77 pages. Available in PDF, EPUB and Kindle. Book excerpt: The combination of a Coanda inlet and jet flap diffusion, for the achievement of high performance, low volume, thrust augmentation, has been investigated in a two-dimesnional experiment. The use of jet flap diffusion provides a mechanism for the achievement of large control forces, through the use of variable jet flap angles, or through the application of incremental power to the jet flap. Vectoring of the total thrust force is achievable through the use of the fluidic effect, which can be utilized to detach the flow from one side of the jet flap, by decreasing the plenum pressure of that side relative to the plenum pressure of the other side.
Book Synopsis Thrust Augmentation Study of High Performance Ejectors by : John E. Minardi
Download or read book Thrust Augmentation Study of High Performance Ejectors written by John E. Minardi and published by . This book was released on 1983 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: A technique is developed for determining a representative value of the maximum efficiency that can be achieved with high performance ejectors when operating on the supersonic solution branch of an ejector. These efficiencies are used to calculate thrust augmentation for an ejector over a wide range of parameters including operation with a hypothetical engine. Reasonable values of thrust augmentation can be achieved at low subsonic flight mach numbers. However, at flight Mach numbers near one, little or not thrust augmentation was found. At supersonic flight Mach numbers, thrust augmentation was achieved. Basic studies indicated that the effects of temperature was opposite at subsonic and supersonic flight Mach numbers. Thrust augmentation decreased with increasing temperature at subsonic Mach number sand increased with increasing temperature at supersonic Mach numbers.
Book Synopsis Analytical Investigation of High Performance, Short, Thrust Augmenting Ejectors by : Tah-Teh Yang
Download or read book Analytical Investigation of High Performance, Short, Thrust Augmenting Ejectors written by Tah-Teh Yang and published by . This book was released on 1982 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: A procedure for analyzing thrust augmenting ejectors having a short, curved-wall diffuser is presented. In this type of diffuser a shear flow is admitted at the inlet and a set of auxiliary ejectors is used to provide the necessary boundary layer control. Several computer programs are used in the analytical procedure. These computer programs are either outlined or referenced in the open literature. A user's manual is provided in the Appendices of this report. A discussion of the geometries and performances, including thrust augmentation ratios, of two sample ejectors determined by use of this analytical procedure with mixing chamber contraction as an optimization parameter is presented. Use of the mixing chamber length as an optimization parameter is also discussed. (Author).
Book Synopsis Jet-diffuser Ejector - Attached Nozzle Design by :
Download or read book Jet-diffuser Ejector - Attached Nozzle Design written by and published by . This book was released on 1980 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
