Relevant bibliographies by topics / Ejector Powered Engine Simulators

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  1. Journal articles
  2. Dissertations / Theses
  3. Conference papers

Academic literature on the topic 'Ejector Powered Engine Simulators'

Author: Grafiati
Published: 4 June 2021
Last updated: 18 February 2022

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Journal articles on the topic "Ejector Powered Engine Simulators"

1

Han, Yu, Lixin Guo, Xiaodong Wang, et al. "A Steam Ejector Refrigeration System Powered by Engine Combustion Waste Heat: Part 1. Characterization of the Internal Flow Structure." Applied Sciences 9, no. 20 (2019): 4275. http://dx.doi.org/10.3390/app9204275.

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With the escalating production of automobiles, energy efficiency and environmental friendliness have always been a major concern in the automotive industry. In order to effectively lower the energy consumption of a vehicle, it is essential to develop air-conditioning systems that can make good use of combustion waste heat. Ejector refrigeration systems have become increasingly popular for this purpose due to their energy efficiency and ability to recycle waste heat. In this article, the elements affecting the performance of a typical ejector refrigeration system have been explored using both e
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Zhang, Fan, Huiqiang Zhang, and Bing Wang. "Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 5 (2017): 944–57. http://dx.doi.org/10.1177/0954410017703148.

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The liquid oxygen/methane staged cycle liquid-rocket engine is one of the most potential rocket engines in the future for its higher performance, higher fuel density and reusable capacity. Two working states of this liquid-rocket engine named as full-load state and half-load state are defined in this paper. Based on this liquid-rocket engine, a dual-rocket-based-combined-cycle propulsion system with liquid oxygen /air/methane as propellants is therefore proposed. The dual-rocket-based-combined-cycle system has then five working modes: the hybrid mode, pure ejector mode, ramjet mode, scramjet m
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Han, Yu, Xiaodong Wang, Lixin Guo, et al. "A Steam Ejector Refrigeration System Powered by Engine Combustion Waste Heat: Part 2. Understanding the Nature of the Shock Wave Structure." Applied Sciences 9, no. 20 (2019): 4435. http://dx.doi.org/10.3390/app9204435.

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In general, engine fuel combustion generates 30% waste heat, which is disposed to the environment. The use of the steam ejector refrigeration to recycle the waste heat and transfer them to useful energy source could be an environmentally friendly solution to such an issue. The steam ejector is the main component of the ejector refrigeration system, which can operate at a low-temperature range. In this article, the internal shock wave structure of the ejector is comprehensively studied through the computation fluid dynamics (CFD) approach. The shock wave structure can be subdivided into two reg
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4

Jenista, J. E., and D. S. Bodden. "Configuration E-7 Supersonic Fighter/Attack Technology Program." Journal of Engineering for Gas Turbines and Power 112, no. 2 (1990): 212–16. http://dx.doi.org/10.1115/1.2906164.

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The program covering the design and early technology development of Configuration E-7, a supersonic STOVL Fighter/Attack aircraft, is described. This aircraft uses the ejector principle to augment engine fan air for vertical lift. The initial design objectives selected in 1980 are listed and discussed. Some design considerations applicable to the propulsion concept and the chosen configuration are mentioned. The test program accomplished thus far, including wind tunnel models plus other test articles and activities, is outlined. The program has proceeded without major technological obstacles a
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Yılmaz, Alper, and Arif Emre Aktaş. "Comparative Analysis of Ejector Refrigeration System Powered with Engine Exhaust Heat using R134a and R245fa." European Mechanical Science 3, no. 1 (2019): 13–17. http://dx.doi.org/10.26701/ems.430831.

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Langston, Lee S. "Powering Out of Trouble." Mechanical Engineering 135, no. 12 (2013): 36–41. http://dx.doi.org/10.1115/1.2013-dec-3.

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This article presents a study of Pratt & Whitney’s J58, till date the best and high-powered engine for manufacturing lessons required for the development of F35 Joint Strike Fighter. The J58 Blackbird engine is a variable cycle engine, a turbojet/ramjet combined-cycle engine. It is a conventional afterburning turbojet for take-off and transonic flight, and it approximates a ramjet during high-speed supersonic cruise. The power plant for the Blackbirds is a marvelous development on the part of Pratt & Whitney, as it is the only engine of its kind in the world. The noise and vibration fr
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Sadeghi, Mohsen, S. M. S. Mahmoudi, and R. Khoshbakhti Saray. "Exergoeconomic analysis and multi-objective optimization of an ejector refrigeration cycle powered by an internal combustion (HCCI) engine." Energy Conversion and Management 96 (May 2015): 403–17. http://dx.doi.org/10.1016/j.enconman.2015.02.081.

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8

Park, Hyeong-Uk, Joon Chung, and Ohyun Kwon. "Application of virtual flight test framework with derivative design optimization." Aircraft Engineering and Aerospace Technology 90, no. 9 (2018): 1445–63. http://dx.doi.org/10.1108/aeat-06-2017-0149.

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Purpose The purpose of this paper is a development of a virtual flight test framework with derivative design optimization. Aircraft manufactures and engineers have been putting significant effort into the design process to lower the cost of development and time to a minimum. In terms of flight tests and aircraft certification, implementing simulation and virtual test techniques may be a sufficient method in achieving these goals. In addition to simulation and virtual test, a derivative design can be implemented to satisfy different market demands and technical changes while reducing developmen
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"Viability of Using Engine Room Simulators for Evaluation Machinery Performance and Energy Management Onboard Ships." International Journal of Maritime Engineering 161, A3 (2019). http://dx.doi.org/10.3940/rina.ijme.2019.a3.545.

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The maritime institutions aim at contributing to reducing the adverse effects arising from the ships, machinery operation through the possibilities exit in the engine room simulators. The current paper explains the importance of engine room simulators in maritime education in general and focuses on their use in the field of evaluation and management of machinery within the engine room space. As a case study, an electric powered passenger ship and an oil tanker ship are investigated regarding applying ship energy management onboard. This investigation could be achieved using the possibilities a
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Dissertations / Theses on the topic "Ejector Powered Engine Simulators"

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Allenstein, Jacob T. "An Investigation of Jet Engine Test Cell Exhaust Stack Aerodynamics and Performance through Scale Model Test Studies and Computational Fluid Dynamics Results." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1586515794023938.

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Conference papers on the topic "Ejector Powered Engine Simulators"

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Tanaka, S., and Z. Spakovszky. "A Thermal Mixing Scheme for Portable Gas Turbines." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-22530.

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To meet the increasing demand for advanced portable power units, for example for use in personal electronics and robotics, a number of studies have recently focused on small gas turbine units in the 500 W to 1 kW range. The majority of the work to date is concerned with the design of efficient high-speed rotating machinery and electric components. An important aspect, especially critical for portable operation, is the cooling of the gas turbine and the exhaust gas. This is the focus of the present paper. The compact and small-scale architecture of such gas turbine engines poses major challenge
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2

Jenista, John E., and David S. Bodden. "Configuration E-7 Supersonic Fighter/Attack Technology Program." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-308.

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The program covering the design and early technology development of Configuration E-7, a supersonic STOVL Fighter/Attack aircraft is described. This aircraft uses the ejector principle to augment engine fan air for vertical lift. The initial design objectives selected in 1980 are listed and discussed. Some design considerations applicable to the propulsion concept and the chosen configuration are mentioned. The test program accomplished thus far, including wind tunnel models plus other test articles and activities is outlined. The program has proceeded without major technological obstacles and
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3

Ochs, M., A. Schulz, and H. J. Bauer. "Investigation of the Influence of Trailing Edge Shock Waves on Film Cooling Performance of Gas Turbine Airfoils." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27482.

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Transonic turbine stage flows are strongly influenced by shock waves. The oblique trailing edge shock generated at the pressure side impinges on the suction side of the neighboring airfoil leading to a significant alteration of the Mach number distribution. On film cooled turbine airfoils this shock interacts with the local cooling film. The present study deals with the investigation of this kind of shock wave – film cooling interaction. Experiments are conducted in a high pressure high temperature transonic test rig which allows setting engine realistic Reynolds numbers and Mach numbers, as w
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Hildebrandt, Thomas, Wolfgang Ganzert, and Leonhard Fottner. "Systematic Experimental and Numerical Investigations on the Aerothermodynamics of a Film Cooled Turbine Cascade With Variation of the Cooling Hole Shape: Part II — Numerical Approach." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0298.

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An extensive numerical study was accomplished in order to accompany an experimental research program. The present work is focussed on the influence of the shape and the inclination of film cooling holes on the aerodynamic of the turbine cooling flow. Four different cooling hole geometries located on the suction side of a large scale turbine cascade were modelled and numerically simulated over the entire range of practically applicable blowing ratios. The thermodynamic conditions chosen, were in order to simulate comparable engine conditions. Having computer limitations in mind, former simulati
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Krueckels, Joerg, Michael Gritsch, and Martin Schnieder. "Design Considerations and Validation of Trailing Edge Pressure Side Bleed Cooling." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-59161.

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One important design measure, which allows achieving a higher efficiency in heavy-duty gas turbines, is reducing the trailing edge thickness of the turbine vanes and blades. A common approach to achieve an efficient cooling of thin trailing edges is pressure side coolant ejection. As the trailing edge is one of the areas of the vanes and blades with the highest heat load, a careful design and validation approach is required. First, the most important design parameters were identified for the design of pressure side bleed. In the present investigation, focus is given to the blockage of the inte
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Parbat, Sarwesh, Li Yang, Minking Chyu, Sin Chien Siw, and Ching-Pang Lee. "Numerical Study of Heat Transfer in Novel Wavy Trailing Edge Design for Gas Turbine Airfoils." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91123.

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Abstract The strive to achieve increasingly higher efficiencies in gas turbine power generation has led to a continued rise in the turbine inlet temperature. As a result, novel cooling approaches for gas turbine blades are necessary to maintain them within the material’s thermal mechanical performance envelope. Various internal and external cooling technologies are used in different parts of the blade airfoil to provide the desired levels of cooling. Among the different regions of the blade profile, the trailing edge (TE) presents additional cooling challenges due to the thin cross section and
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