Relevant bibliographies by topics / Airplanes – Turbojet engines – Blades

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  2. Dissertations / Theses
  3. Books
  4. Conference papers

Academic literature on the topic 'Airplanes – Turbojet engines – Blades'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Airplanes – Turbojet engines – Blades"

1

OPARA, Tadeusz. "History and future of turbine aircraft engines." Combustion Engines 127, no. 4 (2006): 3–18. http://dx.doi.org/10.19206/ce-117335.

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This paper discusses stages of development of air propulsion from piston engines up to three-rotor turbine ones. Limitations in speed and altitude of flight, caused by traditional system of a piston engine and an airscrew, became an impulse to conduct research on jet propulsion. Accomplishments of the designers of the first jet-propelled engines: F. Whitle and H. von Ohain are a reflection of rivalry in this field. In the second half of the 20th centur y turbine propulsion (turbojet, turboprop and helicopter engines) dominated air force and civil aviation. In 1960 the age of turbofans began, o
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2

Sturm, W., H. Scheugenpflug, and L. Fottner. "Performance Improvements of Compressor Cascades by Controlling the Profile and Sidewall Boundary Layers." Journal of Turbomachinery 114, no. 3 (1992): 477–86. http://dx.doi.org/10.1115/1.2929168.

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For increasing the thrust-to-weight ratio of modern turbojet engines, the number of stages of the turbo components or at least the number of blades per stage must be minimized. This inevitably forces a higher loading of the remaining blades, for which, especially in the compressor, even the use of modern controlled diffusion airfoil concepts is limited due to the danger of flow separation. Therefore, boundary layer control can be taken into consideration. The use of blowing proves to be most obvious for applications in turbojet engines, because the required pressurized air is, due to the worki
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3

Trazzi, P. E. "DESIGN AND DEVELOPMENT OF A 70 N THRUST CLASS TURBOJET ENGINE." Revista de Engenharia Térmica 3, no. 1 (2004): 09. http://dx.doi.org/10.5380/reterm.v3i1.3484.

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Small turbojet engines are being used for propulsion of radio-controlled
model airplanes. The design and development of the model 505 small jet
engine are reviewed. Small size gas turbines present special design and
construction difficulties, some of which are addressed; design choices
leading to the final configuration are discussed. Aero-thermodynamic
aspects are covered along with experimental data when available. The unit
is comprised of a radial compressor, an annular combustion chamber, and
an axial turbine plus accessories; details on these components
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4

Abdullah, Bestoon, Vadim Varsegov, and Adolf Limansky. "CENTRIFUGAL COMPRESSOR HEAD CHARACTERISTIC OF A MICRO TURBOJET ENGINE BASED ON NUMERICAL SIMULATION." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 62 (2020): 5–11. http://dx.doi.org/10.15593/2224-9982/2020.62.01.

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Shown the possibility of using the standard ANSYS CFX hydrodynamic software package for calculating the gasdynamic characteristics of the centrifugal compressor impeller of micro turbojet engines with different options for profiling blades which based on physical and numerical modeling. Presented a methodology for designing the impeller of a centrifugal compressor based on solving the inverse problem of gas dynamics. As a result of a numerical study, the head coefficient of various forms of the impeller was obtained and presented the dependences of the head coefficient and efficiency on the bl
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5

Huang, Jingjing, and Longxi Zheng. "Noise analysis of the turbojet and turbofan engine tests." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 228, no. 13 (2013): 2414–23. http://dx.doi.org/10.1177/0954410013518035.

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Aerogine noise leads to environment pollution largely when aerogine is tested. In this paper, the power spectrum analysis method of the aeroengine test noise was discussed, and the noise measurement and analysis experiments of a turbojet engine and a turbofan engine tests were carried out. The noise level, main noise resource, and noise characteristics of the two turbojet and turbofan engines were analyzed. Meanwhile, the indoor noise and far-field noise of the turbojet engine were both measured, the noise spread characteristics were analyzed and the noise reduction performance of the test ben
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Лось, Александр Васильевич. "ОСОБЛИВОСТІ ОЦІНКИ ПАЛИВНОЇ ЕФЕКТИВНОСТІ МОДИФІКАЦІЙ ЛІТАКІВ З БАГАТОДВИГУНОВИМИ СИЛОВИМИ УСТАНОВКАМИ". Open Information and Computer Integrated Technologies, № 86 (14 лютого 2020): 117–26. http://dx.doi.org/10.32620/oikit.2019.86.08.

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When creating modifications of transport category airplanes, fuel efficiency appears in the structure of their parameters.This indicator is very important, since operating costs largely depend on the amount of fuel consumed per unit of work.The problem of evaluating the fuel efficiency of modifications of transport aircraft with multi-engine power plants is considered. It is noted that multi-engine power plants, used mainly on medium and heavy aircraft, contribute to solving a number of problematic issues:– expanding the ability to operate in hot climates and highlands;– improving operational
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7

Hasuda, Yuichi, Asahi Handa, Yuki Kobori, Shinichi Kinebuchi, Toshiaki Furusawa, and Yasuo Harigaya. "Grinding of Super-Alloys Using Metal-Bonded CBN Wheel." Key Engineering Materials 523-524 (November 2012): 143–48. http://dx.doi.org/10.4028/www.scientific.net/kem.523-524.143.

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Superalloys, used for turbine blades and jet engines for airplanes, have low heat conduction and high strength at elevated temperature. These properties make it very difficult to obtain effective grinding processes with high accuracy. Superalloys with fine performance under high temperature circumstances attract great attention to be used as the material for turbine blades. It has been expected to establish reliable efficient grinding of superalloys at the final grinding process. In this study, the influence of wheel wear, grinding ratio, and surface roughness, with the grinding process of sup
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Batcho, P. F., J. C. Moller, C. Padova, and M. G. Dunn. "Interpretation of Gas Turbine Response Due to Dust Ingestion." Journal of Engineering for Gas Turbines and Power 109, no. 3 (1987): 344–52. http://dx.doi.org/10.1115/1.3240046.

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A measurement program currently underway at Arvin/Calspan Advanced Technology Center has been used in the evaluation of observed engine behavior during dust ingestion. The Pratt and Whitney TF33 turbofan and J57 turbojet were used in the investigation. Solid particle ingestion was found to erode the compressor blades and result in substantial performance deterioration. The engines were found to have increased susceptibility to surge at low power settings. The roles that anti-ice and intercompressor bleed airplay in surge avoidance are discussed. A discussion of the fuel controller behavior in
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Chervonyuk, V. V., and B. B. Korovin. "Ensuring permissible level of gas turbine dynamic loading in operation by means of standard engine control devices." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 2 (2019): 112–20. http://dx.doi.org/10.18287/2541-7533-2019-18-2-112-120.

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To solve the fatigue resistance problems of gas turbine engine elements using the existing principles of regulation based on the use of safe load factors for various loading schemes we suggest exercising controlled influence upon the loading sources in operation using a system of automatic control and standard devices for engine monitoring. The article discusses the use of this approach to minimize the dynamic loading of the LPC (low pressure compressor) blades of afterburning turbojet engines installed on supersonic aircraft, as well as to combat oscillatory combustion in combustion chambers
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Przysowa, Radoslaw, and Peter Russhard. "Non-Contact Measurement of Blade Vibration in an Axial Compressor." Sensors 20, no. 1 (2019): 68. http://dx.doi.org/10.3390/s20010068.

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Complex blade responses such as a rotating stall or simultaneous resonances are common in modern engines and their observation can be a challenge even for state-of-the-art tip-timing systems and trained operators. This paper analyses forced vibrations of axial compressor blades, measured during the bench tests of the SO-3 turbojet. In relation to earlier studies conducted in Poland with a small number of sensors, a multichannel tip-timing system let us observe simultaneous responses or higher-order modes. To find possible symptoms of a failure, blade responses in a healthy and unhealthy engine
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Dissertations / Theses on the topic "Airplanes – Turbojet engines – Blades"

1

Chesnakas, Christopher J. "Experimental studies in a supersonic through-flow fan blade cascade." Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/39790.

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An investigation has been performed of the flow in a supersonic through-flow fan blade cascade. The blade shapes are those of the baseline supersonic through-flow fan (STFF) under investigation at the NASA Lewis Research Center. Measurements were made at an inlet Mach number of 2.36 over a 15° range of incidence. Flowfield wave patterns were recorded using spark shadowgraph photography and steady-state instrumentation was used to measure blade surface pressure distributions and downstream total and static pressure distributions. A two-dimensional LDV system was used to map the downstream
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Kwan, Pok Wang. "Flow management in heat exchanger installations for intercooled turbofan engines." Thesis, University of Oxford, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.711622.

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Gaeta, Richard Joseph Jr. "Liner impedance modification by varying perforate orifice geometry." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12258.

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Nygaard, James Robert. "Understanding the behaviour of aircraft bearing steels under rolling contact loading." Thesis, University of Cambridge, 2015. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.709284.

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Pavelec, Sterling Michael. "The development of turbojet aircraft in Germany, Britain, and the United States : a multi-national comparison of aeronautical engineering, 1935-1946 /." The Ohio State University, 2004. http://www.ohiolink.edu/etd/send-pdf.cgi/Pavelec%20Sterling%20Michael.pdf?acc_num=osu1082396007.

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6

Bensel, Artur. "Characteristics of the Specific Fuel Consumption for Jet Engines." Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2018. http://d-nb.info/1175791237.

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Purpose of this project is a) the evaluation of the Thrust Specific Fuel Consumption (TSFC) of jet engines in cruise as a function of flight altitude, speed and thrust and b) the determination of the optimum cruise speed for maximum range of jet airplanes based on TSFC characteristics from a). Related to a) a literature review shows different models for the influence of altitude and speed on TSFC. A simple model describing the influence of thrust on TSFC seems not to exist in the literature. Here, openly available data was collected and evaluated. TSFC versus thrust is described by the so-call
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Mutschall, Marcel. "Die Genauigkeit einer vereinfachten Berechnung der Steigzeit von Flugzeugen." Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2018. http://d-nb.info/1175497711.

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Ziel - Die Zeit die ein Flugzeug benötigt, um auf eine bestimmte Höhe zu steigen (die Steigzeit) kann mit einer Formel berechnet werden, die vereinfachend annimmt, dass die Steiggeschwindigkeit über dem gesamten Steigflug mit zunehmender Höhe linear abnimmt. Ziel der Untersuchung ist, zu ermitteln, ob die Annahme einer linear abnehmenden Steiggeschwindigkeit realistisch ist bzw. welche Fehler sich aus der Annahme ergeben. ----- Methode - Mit der Höhe ändern sich Parameter wie Luftdichte, Widerstand, Schub und damit auch die optimale Fluggeschwindigkeit für den Steigflug. Die Parameter beeinflu
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Hmad, Ouadie. "Evaluation et optimisation des performances de fonctions pour la surveillance de turboréacteurs." Thesis, Troyes, 2013. http://www.theses.fr/2013TROY0029.

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Cette thèse concerne les systèmes de surveillance des turboréacteurs. Le développement de tels systèmes nécessite une phase d’évaluation et d’optimisation des performances, préalablement à la mise en exploitation. Le travail a porté sur cette phase, et plus précisément sur les performances des fonctions de détection et de pronostic de deux systèmes. Des indicateurs de performances associés à chacune de ces fonctions ainsi que leur estimation ont été définis. Les systèmes surveillés sont d’une part la séquence de démarrage pour la fonction de détection et d’autre part la consommation d’huile po
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Books on the topic "Airplanes – Turbojet engines – Blades"

1

Kost, Friedrich. Längswirbelentstehung in einem Turbinenlaufrad mit konischen Seitenwänden. Deutsche Forschungsanstalt für Luft- und Raumfahrt, 1993.

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2

Balakrishnan, Anantaram. The nozzle guide vane problem: Partitioning a heterogeneous inventory. Institute for Research in the Behavioral, Economic, and Management Sciences, Krannert Graduate School of Management, Purdue University, 1986.

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Plante, Robert. The nozzle guide vane problem. Institute for Research in the Behavioral, Economic, and Management Sciences, Krannert Graduate School of Management, Purdue University, 1987.

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4

Kay, Antony L. Turbojet: History and development. Crowood, 2007.

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5

Leṿi, Shelomoh. Menoʻe ṭurbinah li-meṭosim. Miśrad ha-ḥinukh, ha-tarbut ṿeha-sporṭ, Maḥleḳet pirsumim, 1999.

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6

Hang kong ran qi wo lun fa dong ji. Guo fang gong ye chu ban she, 1985.

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7

Nechaev, I͡U N. Aviat͡sionnye turboreaktivnye dvigateli s izmeni͡aemym rabochim prot͡sessom dli͡a mnogorezhimnykh samoletov. "Mashinostroenie", 1988.

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Abdelwahab, Mahmood. Measurement uncertaintyfor the uniform engine testing program conducted at the NASA Lewis Research Center. National Aeronautics and Space Administration, 1987.

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9

Kalinichenko, B. V. Letnye kharakteristiki samoletov s gazoturbinnymi dvigateli͡a︡mi. "Mashinostroenie", 1986.

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Compressor surge and stall. Concepts ETI, 1993.

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Conference papers on the topic "Airplanes – Turbojet engines – Blades"

1

Sturm, Wolfgang, Hermann Scheugenpflug, and Leonhard Fottner. "Performance Improvements of Compressor Cascades by Controlling the Profile and Sidewall Boundary Layers." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-260.

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For increasing the thrust-to-weight ratio of modern turbojet engines, the number of stages of the turbo components or at least the number of blades per stage have to be minimized. This inevitably forces a higher loading of the remaining blades, for which — especially in the compressor — even the use of modern controlled diffusion airfoil concepts is limited due to the danger of flow separation. Therefore, boundary layer control can be taken into consideration. The use of blowing proves to be most obvious for applications in turbojet engines, because the required pressurized air is — due to the
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2

Poncelet, Fabien, Bruno Bernay, Gaetan Kerschen, and Jean-Claude Golinval. "Damping Material Characterization and Modeling: An Industrial Case-Study." In ASME 2009 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/detc2009-87342.

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Turbojet engines contain potential nonlinearity sources such as geometric nonlinearities due to the slenderness and the length of modern blades, contacts between the blades and the shrouds, friction in the connections, and material nonlinearities. This paper focuses on the damping material which can be found in some stator stages of low-pressure compression parts. This material makes the shroud and all the blades of the stage interdependent, providing damping and fluid vein airtightness. The objective is to propose a characterization and a numerical modeling methodology that could easily be in
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van Enkhuizen, Marinus Johannus, Christian Dresbach, Stefan Reh, and Stefan Kuntzagk. "Efficient Lifetime Prediction of High Pressure Turbine Blades in Real Life Conditions." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63341.

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Jet engines of airplanes are designed such that in some components damage occurs and grows in service without being critical up to a certain level. Since maintenance, repair and component exchange are cost-intensive and limit the operating life of the engine, it is necessary to predict the component lifetime using an acceptable computational effort. To efficiently calculate the lifetime consumption of turbine components with sufficient accuracy under operational conditions, we developed a hybrid approach, which is based on the following three steps: First, the possible operation space is analy
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Harada, Hiroshi, and Junzo Fujioka. "New Developments in High Temperature Materials 21 Project in Japan." In ASME 2005 Power Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/pwr2005-50367.

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Following the Kyoto Conference on Climate Change (COP3) held in 1997, the improvement of thermal efficiency in power engineering systems is becoming a major issue. In High Temperature Materials 21 Project at NIMS, materials for turbine blades and vanes are being developed to improve the temperature capability and reduce the CO2 emission of industrial gas turbines (IGT) and jet engines. The target for Ni-base superalloys was set at 1100°C for 1000h creep rupture life under 137MPa to realize ultra-efficient combined cycle power plants and advanced jet engines. A high cost-performance single crys
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Meher-Homji, Cyrus B., and Erik Prisell. "Dr. Max Bentele: Pioneer of the Jet Age." In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/gt2003-38760.

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This paper will document the pioneering work of Dr. Max Bentele in his long and distinguished career in Germany, the UK and the United States. His early work on turbojets was in conjunction with his life long friend, Dr. Hans von Ohain, at the Heinkel-Hirth Corporation where he was involved in a wide range of turbojet engines culminating with the advanced HeS 011 (2940 lb thrust, 64 lb/sec, Pr Ratio 4.2:1), which he co-developed with Dr. Hans von Ohain. Dr. Bentele’s pioneering work in the area of blade vibration and its control will be documented along with details of his spectacular solution
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Battiato, Giuseppe, Christian M. Firrone, Teresa M. Berruti, and Bogdan I. Epureanu. "Reduced Order Modeling for Multi-Stage Bladed Disks With Friction Contacts at the Flange Joint." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64814.

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Most aircraft turbojet engines consist of multiple stages coupled by means of bolted flange joints which potentially represent source of nonlinearities due to friction phenomena. Methods aimed at predicting the forced response of multi-stage bladed disks have to take into account such nonlinear behavior and its effect in damping blades vibration. In this paper a novel reduced order model is proposed for studying nonlinear vibration due to contacts in multi-stage bladed disks. The methodology exploits the shape of the single-stage normal modes at the inter-stage boundary being mathematically de
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Haven, Brenda A., Aaron R. Byerley, and D. Neal Barlow. "An Undergraduate Gas Turbine Engine Program Enhanced by Design and Research Threads." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30588.

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This paper describes an undergraduate program at the USAF Academy that uses the threads of engine design and research to teach and reinforce the fundamentals of gas turbine engines. Each year approximately twelve cadets who have chosen to specialize in the propulsion track of the Aeronautical Engineering major enter a five-course sequence that includes 1.) engineering thermodynamics, 2.) intro to propulsion (advanced cycle analysis), 3.) advanced propulsion (focus on engine component performance), 4.) intro to aircraft and propulsion system design, and 5.) aircraft engine design. During the fi
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Huang, Paul Xiubao, and JianAn Yin. "From Rotating Stall to Surge: A Shock Tube Mechanism." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94128.

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Compressor surge is a complete breakdown in compression resulting in an abrupt momentary reversal of gas flow and the violent pressure fluctuation with relatively low frequency and high amplitude. It commonly exists in dynamic type turbo compressors, particularly axial compressor and jet engine, or turbo charger for reciprocating engines. It is generally accepted that surge is preceded by a rotating stall, a situation of a few stalled blades rotating around compressor annulus (cascade) with much higher frequency. In jet engine, violent surge event typically produces a frightening loud bang, lo
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Millecamps, Antoine, Alain Batailly, Mathias Legrand, and François Garcin. "Snecma’s Viewpoint on the Numerical and Experimental Simulation of Blade-Tip/Casing Unilateral Contacts." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42682.

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Aircraft engine manufacturers are developping a new generation of turbojet engines featuring a lower impact on the environment, increased performances as well as reduced gas consumption. The efficiency of an engine is mostly driven by the operating clearance between the rotating parts and the stator. Accordingly, modern designs focus on the minimization of these clearances. In this context, unavoidable rotor imbalances or mistuning stemming from manufacturing processes as well as distortions resulting from thermal expansion or assembly conditions may generate blade-tip/casing contacts that are
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