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Relevant bibliographies by topics / Jet Blast Deflector

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Academic literature on the topic 'Jet Blast Deflector'

Author: Grafiati

Published: 6 September 2023

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Journal articles on the topic "Jet Blast Deflector"

1

Ma, Song, Jianguo Tan, Xiankai Li, and Jiang Hao. "The effect analysis of an engine jet on an aircraft blast deflector." Transactions of the Institute of Measurement and Control 41, no. 4 (March 26, 2018): 990–1001. http://dx.doi.org/10.1177/0142331218755892.

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This paper establishes a novel mathematical model for computing the plume flow field of a carrier-based aircraft engine. Its objective is to study the impact of jet exhaust gases with high temperature, high speed and high pressure on the jet blast deflector. The working condition of the nozzle of a fully powered on engine is first determined. The flow field of the exhaust jet is then numerically simulated at different deflection angle using the three-dimensional Reynolds averaged Navier–Stokes equations and the standard [Formula: see text]-[Formula: see text] turbulence method. Moreover, infra-red temperature tests are further carried out to test the temperature field when the jet blast deflector is at the [Formula: see text] deflection angle. The comparison between the simulation results and the experimental results show that the proposed computation model can perfectly describe the system. There is only 8–10% variation between them. A good verification is achieved. Moreover, the experimental results show that the jet blast deflector plays an outstanding role in driving the high-temperature exhaust gases. It is found that [Formula: see text] may be the best deflection angle to protect the deck and the surrounding equipment effectively. These data results provide a valuable basis for the design and layout optimization of the jet blast deflector and deck.

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2

Worden, Theodore J., Chiang Shih, and Farrukh S. Alvi. "Supersonic Jet Impingement on a Model-Scale Jet Blast Deflector." AIAA Journal 55, no. 8 (June 2017): 2522–36. http://dx.doi.org/10.2514/1.j055664.

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3

Miller, SAE, and Alexander N. Carr. "Theoretical investigation of alteration and radiation of large-scale structures due to jet impingement." International Journal of Aeroacoustics 18, no. 2-3 (December 20, 2018): 231–57. http://dx.doi.org/10.1177/1475472x18812810.

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Jet flows impinge on launch pad structures and aircraft carrier deck blast deflectors. Turbulent structures are deformed and acoustic radiation is reflected by the deflector. The coupling of reflected acoustic waves with the instability waves of the jet turbulence increases their amplitude and causes a feedback loop. Resultant far-field acoustic radiation is amplified. This amplification results in additional tones with significant spectral broadening occurring at frequencies corresponding to the constructive interference. We present a simple prediction methodology in the form of an acoustic analogy. The analogy accounts for reflected acoustic waves through a tailored Green’s function and models the large-scale structures as spatially and temporarily growing and decaying instability waves. The predictions are compared with two experimental datasets. Predictions compare favorably with measured frequencies and spectral broadening in the far-field.

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4

Natarajan, Karthikeyan, and Lakshmi Venkatakrishnan. "Flow and acoustic investigations into the impingement of single and multiple jets onto a jet blast deflector." Journal of the Acoustical Society of America 146, no. 4 (October 2019): 3041. http://dx.doi.org/10.1121/1.5137537.

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5

Bendersky, Leonid Aleksandrovich, Dmitriy Aleksandrovich Lyubimov, and Aleksandra Olegovna Chestnykh. "NUMERICAL INVESTIGATION ON THE INTERACTION OF A PAIR OF HOT OFF-DESIGN SUPERSONIC JETS WITH A JET BLAST DEFLECTOR." TsAGI Science Journal 49, no. 1 (2018): 13–28. http://dx.doi.org/10.1615/tsagiscij.2018026782.

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6

Waghmare, Utkarsh, A. S. Dhoble, Ravindra Taiwade, Jagesvar Verma, and Himanshu Vashishtha. "Prediction of heat affected zone and other mechanical properties of welded joints of HSLA A588-B of jet blast deflector." World Journal of Engineering 16, no. 4 (July 6, 2019): 438–44. http://dx.doi.org/10.1108/wje-08-2018-0281.

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Purpose The purpose of this paper is to predict and optimize the width of heat affected zone (HAZ) with better mechanical properties using suitable welding process and parameters for the fabrication of jet blast deflector (JBD) (high strength low alloy material of grade A588-B was used for fabrication) so that the JBD can sustain high exhaust parameters, because there are different welding zones formed due to the rapid cooling of weld metals. Out of the various zones of welding, HAZ remains the weakest zone in the entire weldment. Design/methodology/approach The present work describes the modeling, simulation, Modeling of three-dimensional plate and mess generation process are carried out using ICEM CFD software. FLUENT 16.0 software is used for ANSYS simulation where various models are used for analysis and results are validated with the experimental outcomes. High strength low alloy plates are welded by using shielded metal arc welding and tungsten inert gas (TIG) welding processes with two different electrodes. Optical microscopy and scanning electron microscopy were used for metallurgical study. The mechanical properties were evaluated by tensile strength test, vickers microhardness test and impact test. The corrosion resistance was evaluated by performing the potentiodynamic polarization test. Findings The present study indicated for better mechanical properties and improved corrosion resistance for TIG welded joints with type 308 L filler. Practical implications In aeronautical, defense, space and research organizations. Originality/value It can be shown from the scanning electron microscope technique that sound weld joint is produced with very good mechanical properties and joint also showed better corrosion resistance.

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7

Benderskii, L. A., D. A. Lyubimov, A. O. Chestnykh, B. M. Shabanov, and A. A. Rubakov. "The Use of the RANS/ILES Method to Study the Influence of Coflow Wind on the Flow in a Hot, Nonisobaric, Supersonic Airdrome Jet during Its Interaction with the Jet Blast Deflector." High Temperature 56, no. 2 (March 2018): 247–54. http://dx.doi.org/10.1134/s0018151x18020037.

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8

Gao, Fu-Dong, De-Xin Wang, Hai-Dong Wang, and Ming-Ming Jia. "Numerical Analysis and Verification of the Gas Jet from Aircraft Engines Impacting a Jet Blast Deflector." Chinese Journal of Mechanical Engineering 31, no. 1 (October 11, 2018). http://dx.doi.org/10.1186/s10033-018-0285-7.

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9

Erwin, James P., Neeraj Sinha, and Gregory P. Rodebaugh. "Large Eddy Simulations of Supersonic Impinging Jets." Journal of Engineering for Gas Turbines and Power 134, no. 12 (October 11, 2012). http://dx.doi.org/10.1115/1.4007338.

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Supersonic impinging jet flow fields contain self-sustaining acoustic feedback features that create high levels of tonal noise. These types of flow fields are typically found with short takeoff and landing military aircraft as well as jet blast deflector operations on aircraft carrier decks. The United States Navy has a goal to reduce the noise generated by these impinging jet configurations and is investing in computational aeroacoustics to aid in the development of noise reduction concepts. In this paper, implicit large eddy simulation (LES) of impinging jet flow fields are coupled with a far-field acoustic transformation using the Ffowcs Williams and Hawkings (FW-H) equation method. The LES solves the noise generating regions of the flow and the FW-H transformation is used to predict the far-field noise. The noise prediction methodology is applied to a Mach 1.5 vertically impinging jet at a stand-off distance of five nozzle throat diameters. Both the LES and FW-H acoustic predictions compare favorably with experimental measurements. Time averaged and instantaneous flow fields are shown. A calculation performed previously at a stand-off distance of four nozzle throat diameters is revisited with adjustments to the methodology including a new grid, time integrator, and longer simulation runtime. The calculation exhibited various feedback loops which were not present before and can be attributed to an explicit time marching scheme. In addition, an instability analysis of the heated jets at both stand-off distances is performed. Tonal frequencies and instability modes are identified for the sample problems.

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Conference papers on the topic "Jet Blast Deflector"

1

Jaiswal, Abhijeet, Ashwin S. Dhoble, and D. J. Tidke. "High Compressible Flow Through Jet Blast Deflector." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4699.

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Jet blast impact on aerofoil blade of the deflector is studied which redirects the high energy exhaust of jet engine during the ground testing. The geometric model of aerofoils is designed with structured mesh around the aerofoil in rectangular domain generated in ICEM 16 software. The jet blast impact on aerofoil blade of the deflector is numerically simulated with SST k-ω model based on CFD theory. The fluid flow is high-speed compressible flow and flowing fluid air is considered as an ideal gas and also Sutherland’s law viscosity is applied to account for the dependence of molecular viscosity on temperature. Flow is taken as first order upwind and flux type is AUSM (Advection Upstream Splitting Method) to get an exact resolution of contact and shock discontinuities. The distribution of temperature, pressure, velocity and streamline of fluid flow is numerically simulated by FLUENT 16 software and layout of eddies generation behind aerofoil is generated in Tecplot 360 software. The coefficient of lift (Cl) and the coefficient of drag (Cd) are calculated to study the impact on aerofoil blade in horizontal and vertical direction. The result indicates that the method presented in this paper can analyze the fluid behavior on the complicated geometry of aerofoil blade that the flow between two adjacent aerofoil blades obtains a highly reliable simulation result. The value of lift force is negative i.e it holds the deflector towards the ground, so optimum balance between drag force and lifts force is obtained by simulating at a different angle of attack and pitch. Through CFD numerical simulation at a different angle of attack and pitch, the best result is obtained and conductive suggestions can be given for the adaptation of the JBD blade.

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2

Worden, Theodore J., Chiang Shih, and Farrukh S. Alvi. "Supersonic Jet Impingement on a Model-scale Jet Blast Deflector." In 54th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1015.

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3

Alostaz, Yousef, Mark Fantozzi, and Peter Feenstra. "Innovative Jet Blast Deflector System: Analysis and Design." In Structures Congress 2015. Reston, VA: American Society of Civil Engineers, 2015. http://dx.doi.org/10.1061/9780784479117.185.

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4

Tangen, Steven. "Investigating Separated Shear Layers for Passive Jet Blast Deflector Cooling." In 44th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-144.

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5

Erwin, James, Neeraj Sinha, and Gregory Rodebaugh. "Noise predictions of a hot twin-jet impinging on a jet blast deflector." In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-324.

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6

Pilon, Anthony R. "Land- and Aircraft Carrier-Based F-35C Jet Blast Deflector Noise Testing." In 22nd AIAA/CEAS Aeroacoustics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-2730.

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7

Korotaeva, T. A., and A. O. Turchinovich. "Numerical simulation of interaction between chemically active exhaust and a jet blast deflector." In PROCEEDINGS OF THE XXV CONFERENCE ON HIGH-ENERGY PROCESSES IN CONDENSED MATTER (HEPCM 2017): Dedicated to the 60th anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS. Author(s), 2017. http://dx.doi.org/10.1063/1.5007608.

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8

Liu, Junhui, Kailas Kailasanath, Nick Heeb, David Munday, and Ephraim Gutmark. "Impact of Deck and Jet Blast Deflector on the Flow and Acoustic Properties of Imperfectly Expanded Supersonic Jets." In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-323.

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9

Erwin, James P., Neeraj Sinha, and Gregory P. Rodebaugh. "Large Eddy Simulations of Supersonic Impinging Jets." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-70140.

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Supersonic impinging jet flowfields contain self-sustaining acoustic feedback features that create high levels of discrete frequency tonal noise. These types of flowfields are typically found with short takeoff and landing military aircraft as well as jet blast deflector operations on aircraft carrier decks. The US Navy has a goal to reduce the noise generated by these impinging jet configurations and is investing in computational aeroacoustics to aid in the development of noise reduction concepts. In this paper, implicit Large Eddy Simulation (LES) of impinging jet flow-fields are coupled with a far-field acoustic transformation using the Ffowcs Williams and Hawkings (FW-H) equation method. The LES solves the noise generating regions of the flow in the nearfield, and the FW-H transformation is used to predict the far-field noise. The noise prediction methodology is applied to a Mach 1.5 vertically impinging jet at a stand-off distance of five nozzle throat diameters. Both the LES and FW-H acoustic predictions compare favorably with experimental measurements. Time averaged and instantaneous flowfields are shown. A calculation performed previously at a stand-off distance of four nozzle throat diameters is revisited with adjustments to the methodology including a new grid, time integrator, and longer simulation runtime. The calculation exhibited various feedback loops which were not present before and can be attributed to an explicit time marching scheme. In addition, an instability analysis of two heated jets is performed. Tonal frequencies and instability modes are identified for the sample problems.

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