533 results on '"Regenerative cooling"'
Search Results
502. Method of Preventing the Plugging of Liquid Coolant Passages of a Regeneratively Cooled Rocket Engine Thrust Chamber.
- Author
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DEPARTMENT OF THE AIR FORCE WASHINGTON D C, Duesberg,Joe D., DEPARTMENT OF THE AIR FORCE WASHINGTON D C, and Duesberg,Joe D.
- Abstract
In the patent, the liquid coolant passages of a regeneratively cooled rocket engine thrust chamber are prevented from becoming plugged by foreign particles. The method includes the steps of forming an inlet and an outlet for each liquid coolant passage. Each inlet and each outlet is so configurated and so dimensioned as to prevent the entry into the respective liquid coolant passage of foreign particles of a predetermined size and larger which would plug the liquid coolant passage. more...
- Published
- 1973
503. HIGH CHAMBER PRESSURE ROCKETRY PROGRAM. BOOK 1
- Author
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AEROJET-GENERAL CORP SACRAMENTO CA and AEROJET-GENERAL CORP SACRAMENTO CA
- Abstract
The objective of this program was to investigate, by both experimental testing and supporting analytical studies, the feasibility and degree of advantage of high chamber pressure rocket engines using nitrogen tetroxide/50% UDMH--50% N2H4 propellants. Both uncooled and cooled thrust chambers were test-fired at the 3000-psia pressure level; supporting studies included a study of the gas-side heat transfer coefficient, a propellants investigation which included some advanced propellant combinations, and system studies to determine the degree of advantage of high chamber pressure. Two injector concepts were developed using uncooled chambers, one of which attained a performance level of 97%*. Cooling systems investigated during cooled chamber testing included regenerative cooling with both oxidizer and fuel, film cooling with oxidizer, thermal barrier coatings, and vortex cooling. Based on the test results and supporting studies, it is concluded that operation of engines at high chamber pressure is feasible, and that the optimum chamber pressure is in the range of 2500 to 3500 psia. The best potential cooling system for future advanced high-pressure engines is regenerative cooling using N2O4 in combination with a thermal barrier coating and film cooling., See also Book 2, AD03680639. Air Force Program Structure No. 750G more...
- Published
- 1965
504. STORABLE TOROIDAL COMBUSTOR DEMONSTRATION PROGRAM.
- Author
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ROCKETDYNE CANOGA PARK CALIF and ROCKETDYNE CANOGA PARK CALIF
- Abstract
Performance and cooling feasibility demonstrations are planned at 2000-psia chamber pressure with a 10,000-pound-thrust toroidal combustor using nitrogen tetroxide/50% hydrazine-50% unsymmetrical dimethylhydrazine (N2O4/N2H4-UDMH, 50-50) propellants. Injectors, workhorse chambers, and cooled chambers are being designed and fabricated to support these demonstrations as discussed in this report. Results of a performance analysis are also presented. (Author) more...
- Published
- 1965
505. Heat Transfer in Rocket Engines.
- Author
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ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT PARIS (FRANCE), Ziebland,H., Parkinson,R. C., ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT PARIS (FRANCE), Ziebland,H., and Parkinson,R. C. more...
- Abstract
In the first part of this book the various basic heat transfer processes are considered, -- simple convective heat transfer from hot gases to the engine walls under various conditions, radiation heat transfer, and coolant heat transfer processes. This part is followed by one describing the various methods of cooling used in liquid propellant rocket engines, such as regenerative, film, ablation and radiation cooling. The final part concerns the properties of materials that will have to be known by the engine designer, from the transport properties of the hot combustion gases to those of the materials from which the engine will be constructed. Emphasis was placed on presenting simple methods for calculating the magnitude of heat transfer rather than providing the most modern and rigorous theories, particularly in the field of developing boundary layers. (Author), NATO furnished. more...
- Published
- 1971
506. HEAT TRANSFER AND FLOW FRICTION CHARACTERISTICS OF SEVERAL PLATE-FIN TYPE COMPACT HEAT EXCHANGER SURFACES.
- Author
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NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF, Pucci,P. F., Ball,S. F. , Jr., Traister,R. E., NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF, Pucci,P. F., Ball,S. F. , Jr., and Traister,R. E.
- Abstract
Experimental results for the convective heat transfer and flow friction characteristics of plate-fin type heat transfer surfaces are presented for five surfaces. Four surfaces had a sinusoidal fin geometry. Two of these were fabricated of stainless steel, two of nickel. One of the nickel surfaces had perforated nickel fins. The fifth surface was fabricated of stainless steel and had a triangular fin geometry. The heat transfer data were obtained by the single-blow transient testing technique and by the cyclic testing technique. The two techniques compliment each other in extending the range of testing capability. (Author), See also AD-467 052. more...
- Published
- 1967
507. COMPOUND A/HYDRAZINE ENGINE DESIGN STUDY. PART II. APPENDIXES.
- Author
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AEROJET-GENERAL CORP SACRAMENTO CALIF LIQUID ROCKET OPERATIONS, Williams,Clayton W., Luscher,Werner P., Henry,C. Scott, Paavola,Clifford, Coats,R. Verne, AEROJET-GENERAL CORP SACRAMENTO CALIF LIQUID ROCKET OPERATIONS, Williams,Clayton W., Luscher,Werner P., Henry,C. Scott, Paavola,Clifford, and Coats,R. Verne more...
- Abstract
The results of the Compound A/Hydrazine Engine Design Study, including the parametric engine information needed to perform mission analyses for evaluation of advanced engine design concepts, are reported in two parts. Part 1 includes parametric engine performance, weight, envelope, and capability for numerous engine concepts utilizing various fuels and different technologies for the feed system, propellant injection, and chamber cooling systems. Part 2 is made up of six appendixes, which encompass a discussion of specific propellant characteristics, along with methods used in accomplishing performance, weight, and heat transfer calculations. In addition, those design methods for turbopumps and gas generators which are common to all engine concepts are discussed. more...
- Published
- 1968
508. COMPOUND A/HYDRAZINE ENGINE DESIGN STUDY. PART I.
- Author
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AEROJET-GENERAL CORP SACRAMENTO CALIF LIQUID ROCKET OPERATIONS, Williams,Clayton W., Luscher,Werner P., Henry,C. Scott, Paavola,Clifford, Coats,R. Verne, AEROJET-GENERAL CORP SACRAMENTO CALIF LIQUID ROCKET OPERATIONS, Williams,Clayton W., Luscher,Werner P., Henry,C. Scott, Paavola,Clifford, and Coats,R. Verne more...
- Abstract
The results of the Compound A/Hydrazine Engine Design Study, including the parametric engine information needed to perform mission analyses for evaluation of advanced engine design concepts, are reported in two parts. Part 1 includes parametric engine performance, weight, envelope, and capability for numerous engine concepts utilizing various fuels and different technologies for the feed system, propellant injection, and chamber cooling systems. These concepts encompass passive and active cooling methods, liquid and gaseous propellant injection, and pressure-fed as well as pump-fed systems of both the bleed cycle and the staged-combustion cycle. The applicability as well as comprehensiveness of the data is demonstrated by its use in three different missions specified by the Air Force. These include a synchronous orbit, trailer propulsion, and integrated propulsion for a re-entry vehicle. Payload or ideal velocity increment differences for various engine design concepts are shown. However, in view of the preliminary design concept approach as well as a lack of detailed engine design specifications, a number of basic assumptions were made in evolving the data within the scope of this program. Therefore, a description is provided for modifying the parametric data needed in a mission analysis to make it consistent with a different set of assumptions should new information subsequently become available. more...
- Published
- 1968
509. HIGH CHAMBER PRESSURE ROCKETRY PROGRAM. BOOK 2
- Author
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AEROJET-GENERAL CORP SACRAMENTO CA and AEROJET-GENERAL CORP SACRAMENTO CA
- Abstract
See also Book 1, AD368640.
- Published
- 1965
510. ADVANCED ROCKET ENGINE--STORABLE.
- Author
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AEROJET-GENERAL CORP SACRAMENTO CALIF and AEROJET-GENERAL CORP SACRAMENTO CALIF
- Abstract
The objective of the ARES (Advanced Rocket Engine, Storable) program is to demonstrate the engineering practicality and performance characteristics of an advanced storable propellant modular engine embodying high chamber pressure and the staged-combustion cycle. This report describes the technical accomplishments of the period which was characterized as one in which many analyses and designs were finished, fabrication of components was initiated and testing accelerated. The most noteworthy accomplishment was the successful hot firing of several full-scale regeneratively cooled thrust chambers at high chamber pressure. (Author) more...
- Published
- 1966
511. Air Force Reusable Rocket Engine Program XLR129-P-1 Engine Performance
- Author
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PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FL FLORIDA RESEARCH AND DEVELOPMENT CENTER, Atherton, Robert R., PRATT AND WHITNEY AIRCRAFT WEST PALM BEACH FL FLORIDA RESEARCH AND DEVELOPMENT CENTER, and Atherton, Robert R. more...
- Abstract
This special technical report presents information and data on the XLR129-P-1 rocket engine. Information is presented for both the demonstrator engine and flight engine versions of this rocket engine. A general description and pertinent technical information are presented for the demonstrator engine. The demonstrator engine program schedule is also presented. Parametric design, performance, cost, and schedule data are presented for the flight engine. This technical report has been prepared for the use of airframe manufacturers and government personnel who are conducting mission and vehicle studies. more...
- Published
- 1969
512. THROTTLING AND SCALING STUDY FOR ADVANCED STORABLE ENGINE. PART 1
- Author
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AEROJET-GENERAL CORP SACRAMENTO CA LIQUID ROCKET DIV, Andrus, Stanley R., Bishop, H. L., Duckering, R. E., Gibb, J. A., Nelson, A. W., AEROJET-GENERAL CORP SACRAMENTO CA LIQUID ROCKET DIV, Andrus, Stanley R., Bishop, H. L., Duckering, R. E., Gibb, J. A., and Nelson, A. W. more...
- Abstract
This report documents the technical accomplishments of the ARES (advanced Rocket Engine Storable) Throttling and Scaling Study Program. Included also in this report is the sponsored design of a throttlable- restartable 100K ARES engine which was used as the baseline engine for this design study. Throttlable, restartable ARES (Advanced Rocket Engine Storable) engine designs are presented at 25,000, 100,000, and 500,000 lb rated thrust levels. On the basis of these designs, engine thrust scaling parametric data are presented over a thrust range of 25,000 to 500,000 lb with nozzle expansion ratios of 50:1 and 150:1., See also Part 2, AD387058. more...
- Published
- 1968
513. 30 KW ARC-JET THRUSTOR RESEARCH.
- Author
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GIANNINI SCIENTIFIC CORP SANTA ANA CALIF, Todd, James P., GIANNINI SCIENTIFIC CORP SANTA ANA CALIF, and Todd, James P.
- Abstract
A research and advanced developmentprogram on a 30 KW arc-jet thrustor is described herein. An experimental radiation-cooled, hydrogen-propelled thrustor designed under a previous Air Force program had demonstrated a high level of performance with a lifetime greater than 100 hours. The current program, a continued effort at the 30 KW power level, required the attainment of improved performance characteristics (eta > or = 55% at Isp = 1000 secs.) and a lifetime demonstration of 500 hours. To attain these difficult performance requriements a thrustor having a regeneratively-cooled anode/nozzle was designed which maintained as closely as possible the internal geometry which had performed successfully in the previous program. The successful completion of a continuous 500-hour endurance test at the required operating conditions without failure indicates that this 30 KW arc-jet thrustor is indeed as advanced as any other type of electric propulsion system at this time. (Author), Supersedes AD-601 534. more...
- Published
- 1964
514. Design and Development of a Free-Displacer/Thermal Compressor Cryogenic Refrigeration System.
- Author
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PHILIPS LABS BRIARCLIFF MANOR NY, Cohen, Barry, Daniels, Alexander, PHILIPS LABS BRIARCLIFF MANOR NY, Cohen, Barry, and Daniels, Alexander
- Abstract
The program described in this report involved analysis, design and testing of a split-type, Vuilleumier cryogenic refrigerator capable of producing 2.0 watts at 77 K. The objective of the contract specifications was to arrive at a lightweight, self-running, silent refrigerator capable of being integrated into infrared imaging systems. Both analytical and experimental results showed taht the goals set for the cold side of the system i.e., the expander, could be achieved. However, difficulties encountered during the design of the system's hot side, i.e., the thermal compressor, indicated that the weight and self-running requirements for the system could not be met. As a result of these findings, the program was terminated prior to its last phase, i.e., the fabrication of final hardware. (Author) more...
- Published
- 1973
515. MULTI-TUBE BOILER AND CONDENSER CAPSULE.
- Author
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TRW EQUIPMENT LABS CLEVELAND OH and TRW EQUIPMENT LABS CLEVELAND OH
- Abstract
The recommended design of an experimental system to evaluate the performance of an orbital organic multi-tube boiler and condenser capsule is presented. The system will have characteristics identical to an isotope-powered system with the exception of: (a) an electrical heat source is used in place of an isotope heat source and (b) a nozzle is used in place of a turboalternator unit. The experiment will provide critical zero gravity information on two-phase thermodynamics and hydrodynamics typical of a Rankine space power system. An important aspect of the system is its dual radiator-condensers. One condenser is designed to operate in a 1 g acceleration environment (flow 'upward') to guarantee orbital stability. The second is designed to operate at 1.0 psia inlet pressure in order to simulate operation of a high efficiency system and to permit the condenser margin of stability to be parametrically evaluated. Both condensers will be operated consecutively in orbit. The system is composed of a flash-type, electrically heated, parallel tube boiler; a choked nozzle for turbine simulation; a compact regenerator; dual direct radiator-condensers; dual condenser pressure regulating tanks; state-of-the-art pumping system; batteries; electrical controls; instrumentation; telemetry; and associated structure. more...
- Published
- 1967
516. New Energy-Saving Cooling System
- Author
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K. Kobayashi, H. Yamamoto, and I. Fukuchi
- Subjects
Air cooling ,Chiller ,Regenerative cooling ,Waste management ,Passive cooling ,Nuclear engineering ,Active cooling ,Water cooling ,Environmental science ,Free cooling ,Physics::Atomic Physics ,Hydronics ,Physics::Atmospheric and Oceanic Physics - Abstract
This paper describes an energy-saving cooling system for the cooling of computer rooms that does not require the operation of existing cooling systems but carries out cooling utilizing the cold outdoor air of the winter season. Instead of using conventional refrigerants as the cooling medium, the new cooling system utilizes cold water. Water cooled by the low temperature outdoor air is taken to a heat exchanger, and the air in the computer room is cooled by this heat exchanger. The temperature of the computer room can be regulated to within ±1°C. by this system. more...
- Published
- 1982
- Full Text
- View/download PDF
517. Cooling with supercritical oxygen
- Author
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D. Rousar and F. Miller
- Subjects
Regenerative cooling ,Sigma heat ,Materials science ,Computer cooling ,chemistry ,Critical heat flux ,Heat transfer ,chemistry.chemical_element ,Thermodynamics ,Liquid oxygen ,Oxygen ,Supercritical fluid - Published
- 1975
- Full Text
- View/download PDF
518. OPEN CYCLE 3-TON SOLAR AIRCONDITIONER: CONCEPT, DESIGN AND CYCLE ANALYSIS
- Author
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P. Gandhidasan and M.C. Gupta
- Subjects
Regenerative cooling ,Engineering ,Architectural engineering ,Solar air conditioning ,business.industry ,Water cooling ,Ton ,business ,Process engineering ,Adiabatic process ,Physics::Atmospheric and Oceanic Physics ,Evaporative cooler - Abstract
This paper discusses an open cycle solar space cooling system suitable for hot, humid climates. The proposed method is based on dehumidification of air by using a liquid absorbent followed by adiabatic evaporative cooling. One of the major advantages of this system is that the required temperature of 60 – 75°C for regeneration of absorbent solution can be easily obtained by using a simple device, solar collector-cumregenerator. In this paper the concept, design and cycle analysis of such a system is described. more...
- Published
- 1978
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519. Space storable regenerative cooling investigation
- Author
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J. W. Neal and J. P. Mitchell
- Subjects
Regenerative cooling ,Engineering ,business.industry ,Mechanical engineering ,Injector ,Space (mathematics) ,Methane ,law.invention ,chemistry.chemical_compound ,chemistry ,law ,Chamber design ,FLOX ,business - Abstract
Space storable regenerative cooling with FLOX/methane under conditions for small pump fed engine, describing injector and chamber design
- Published
- 1969
- Full Text
- View/download PDF
520. Heat Transfer in Piston Cooling
- Author
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A. Stotter
- Subjects
Regenerative cooling ,Piston ,Materials science ,Critical heat flux ,law ,Heat transfer ,Active cooling ,Internal combustion engine cooling ,Free cooling ,Mechanics ,Heat sink ,law.invention - Published
- 1966
- Full Text
- View/download PDF
521. Radiative, ablative, and active cooling thermal protection studies for the leading edge of a fixed-straight wing space shuttle
- Author
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A. V. Gomez, D. M. Curry, and C. G. Johnston
- Subjects
Engineering ,Regenerative cooling ,Leading edge ,Atmospheric entry ,business.industry ,Heat shield ,Active cooling ,Radiative transfer ,Space Shuttle ,Radiant cooling ,Aerospace engineering ,business - Abstract
Performance prediction of fixed wing leading edges radiative, ablative and active cooling thermal protection systems and system weights comparison for space shuttle entry mission
- Published
- 1971
- Full Text
- View/download PDF
522. The Cooling System
- Author
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J. Whipp and Rodney A. Brooks
- Subjects
Chiller ,Regenerative cooling ,Materials science ,law ,Nuclear engineering ,Active cooling ,Oil film ,Water cooling ,Hydronics ,Combustion ,Cylinder (engine) ,law.invention - Abstract
During combustion the temperature of the burning gases are (momentarily) sufficient to melt the metal of the cylinder. It is the function of the cooling system to prevent the engine becoming overheated (in practice the oil film would be burned away and the pistons expand and seize in position before the engine melted), but at the same time to allow it to operate at a temperature high enough to ensure efficient operation. more...
- Published
- 1973
- Full Text
- View/download PDF
523. Space storable regenerative cooling investigation
- Author
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W. Kaminski
- Subjects
Regenerative cooling ,Materials science ,business.industry ,Aerospace engineering ,Space (mathematics) ,business - Published
- 1968
- Full Text
- View/download PDF
524. Heat-pipe-cooled thrust chambers for space storable propellants
- Author
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D. C. Rousar
- Subjects
Propellant ,Regenerative cooling ,animal structures ,Materials science ,genetic structures ,business.industry ,musculoskeletal, neural, and ocular physiology ,education ,Thrust ,Heat sink ,Heat pipe ,Heat flux ,Thermal radiation ,Aerospace engineering ,business ,human activities - Abstract
Heat pipe cooled thrust chambers for space storable propellants, discussing design feasibility for radiation and regeneratively cooled concepts
- Published
- 1970
- Full Text
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525. Nucleate and Film Boiling Heat Transfer to Nitrogen and Methane at Elevated Pressures and Large Temperature Differences
- Author
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C. P. Colver, E. L. Park, and C. M. Sliepcevich
- Subjects
Regenerative cooling ,chemistry.chemical_compound ,Materials science ,chemistry ,Heat flux ,Convective heat transfer ,Boiling ,Heat transfer ,Thermodynamics ,Leidenfrost effect ,Nucleate boiling ,Methane - Abstract
Boiling heat transfer to cryogenic liquids has an obvious immediate application in the cooling of nuclear reactors, regenerative cooling of rocket engines, and industrial processes. In many instances these systems involve simultaneous, localized nucleate and film boiling as well as convective heat transfer at elevated pressures. Gross design data can be obtained for specific applications with all of these heat transfer modes occurring, but the key to eventual understanding lies in obtaining information on each process separately. more...
- Published
- 1966
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526. Sıvı yakıtlı bir roket motorunun rejeneratif yöntemle hesaplamalı akışkanlar dinamiği ve eşlenik ısı transferi kullanılarak soğutulması
- Subjects
Eşlenik ısı transferi ,Rejeneratif sogutma ,Conjugate heat transfer ,Sıvı yakıtlı roket motoru ,Soğutma kanalı ,Regenerative cooling ,Liquid rocket engine ,Cooling channel - Abstract
Rejeneratif soğutma, sıvı yakıtlı roket motorlarının soğutulması için kullanılan bir yöntemdir. Roket motor duvarlarını soğutmak için sıvı yakıt (bazı motorlarda oksitleyici) duvarların içinde bulunan soğutma kanallarından geçerek duvarın motor boyunca soğumasını sağlar ve duvarların zarar görebileceği sıcaklığa ulaşmasını önler. Genel olarak en kritik yer, en yüksek ısı akısının meydana geldiği roket motoru yakınsak-ıraksak lülesinin boğaz bölgesidir. Rejeneratif olarak adlandırılan bu yöntem ile kanaldan geçen yakıtın sıcaklığı enjektöre kadar sürekli artar ve böylece yakıtın iç enerjisi yükselmiş olur ve bu olay yanma verimliliğine ve kararlığına olumlu yönde etki eder. Ancak, rejeneratif soğutma işlemi, kanaldan geçen yanıcı basıncının düşmesine neden olur. Bu nedenlerden dolayı, rejeneratif soğutma işleminde en iyi verimi elde etmek için düşük basınç kaybı ve düşük duvar sıcaklığı hedeflenmelidir. Wadel ve Meyer'in çalışmaları simülasyonların doğrulanması için kullanılmıştır. Rejeneratif soğutma analizlerinde zamandan bağımsız 3 boyutlu, türbülanslı Hesaplamalı Akışkanlar Dinamiği farklı türbülans modelleri ve eşlenik ısı transferi ticari bir yazılım kullanılarak çözülmüştür. Yanma sonucu oluşmuş sıcak gaz karışımından kaynaklanan ısı akısı Bartz denklemi kullanılarak modellenmiştir. Rejeneratif soğutma analizleri için, literatürdeki çalışmalar incelenmiş ve deneysel sonuçlar ile karşılaştırılmıştır. Doğrulama çalışmasından sonra, yakıt dağıtıcısının rejeneratif soğutma kanallarına yakıtı nominal kütlesel debiden farklı dağıttığı koşulların soğutmaya olan etkisi incelenmiştir. Rejeneratif soğutma kanallarından bir tanesinin tıkanması durumunda roket motor duvarındaki sıcaklık değişimleri araştırılmıştır. Bunlara ek olarak, soğutma kanallarının sayısı ve boy-en oranı için farklı geometrik konfigürasyonların soğutma üzerindeki etkileri incelenmiştir., Regenerative cooling is a method used for cooling liquid fuel rocket engines. To cool the engine walls, the liquid fuel (oxidizer in some engines) passes through the cooling channels in the walls, allowing the wall to cool down along the engine and preventing the walls from reaching the temperature at which they may be damaged. In general, the most critical location is the throat region of the convergent-divergent nozzle, where the highest heat flux occurs. With this method, which is called regenerative cooling, the temperature of the fuel passing through the channel continuously increases up to the injector, thus increasing the internal energy of the fuel, which has a positive effect on combustion efficiency and stability. However, the regenerative cooling process causes the fuel pressure drop passing through the channel. For these reasons, to achieve the best efficiency in the regenerative cooling process, low pressure loss and low wall temperature should be targeted. Wadel and Meyer's studies are used to validate simulations. In the regenerative cooling analyzes, time-independent 3D, turbulence Computational Fluid Dynamics was solved using different turbulence models and conjugate heat transfer model using commercial software. The heat flux resulting from the combustion hot gas mixture was modeled using the Bartz equation. For regenerative cooling analyzes, the studies in the literature are examined and compared with the experimental results. After the validation study, the cooling effects of the differences from the nominal mass flow rate originating on the fuel manifold are investigated. In case of blockage of one of the regenerative cooling channels, temperature changes in the wall of rocket engine are studied. Additionally, the effects of different geometric configurations on cooling were investigated for the number and aspect ratio of the cooling channels. more...
527. Coupled heat transfer analysis in regeneratively cooled thrust chambers
- Author
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Barbara Betti, Marco Pizzarelli, and Francesco Nasuti
- Subjects
Pressure drop ,Engineering ,Materials science ,Liquid-propellant rocket ,business.industry ,Mechanical Engineering ,Aerospace Engineering ,Mechanical engineering ,Thrust ,Heat transfer coefficient ,Mechanics ,Computational fluid dynamics ,Chamber pressure ,Coolant ,Supercritical Pressures ,Regenerative Cooling ,Hydrocarbon Fuels ,Physics::Fluid Dynamics ,Fuel Technology ,Heat flux ,Space and Planetary Science ,Heat transfer ,Combustion chamber ,business - Abstract
The coupled hot gas–wall–coolant environment that occurs in regeneratively cooled liquid rocket engines is studied by a computational procedure able to provide a quick and reliable prediction of thrust chamber wall temperature and heat flux as well as coolant flow characteristics, like pressure drop and temperature gain in the regenerative circuit. The coupled analysis is performed by means of a computational fluid dynamics solver of the Reynolds-averaged Navier–Stokes equations for the hot gas flow and by a simplified quasi-two-dimensional approach, which widely relies on semiempirical relations, for the coolant flow and wall structure heat transfer in the cooling channels. Coupled computations of the space shuttle main engine main combustion chamber are performed and compared with available literature data. Results show a reasonable agreement in terms of coolant pressure drop and temperature gain with nominal data, whereas the computed wall temperature peak is closer to hot-firing test data than to the ... more...
528. Development and validation of a conjugate heat transfer code for regenerative cooling structure with OpenFOAM
- Author
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Sufen Li, Hang Pu, Ming Dong, Si Jiao, and Yan Shang
- Subjects
Regenerative cooling ,020303 mechanical engineering & transports ,Materials science ,Development (topology) ,020401 chemical engineering ,0203 mechanical engineering ,Nuclear engineering ,Code (cryptography) ,02 engineering and technology ,Conjugate heat transfer ,0204 chemical engineering
529. [Untitled]
- Subjects
Regenerative cooling ,Computer science ,Enthalpy ,Aerospace Engineering ,02 engineering and technology ,Computational fluid dynamics ,01 natural sciences ,Methane ,010305 fluids & plasmas ,chemistry.chemical_compound ,0203 mechanical engineering ,0103 physical sciences ,Aerospace engineering ,Fluid Flow and Transfer Processes ,Pressure drop ,Propellant ,business.industry ,Mechanical Engineering ,Condensed Matter Physics ,Supercritical fluid ,020303 mechanical engineering & transports ,chemistry ,Space and Planetary Science ,Heat transfer ,Rocket engine ,Combustion chamber ,business - Abstract
Methane is considered being a good choice as a propellant for future reusable launch systems. However, the heat transfer prediction for supercritical methane flowing in cooling channels of a regeneratively cooled combustion chamber is challenging. Because accurate heat transfer predictions are essential to design reliable and efficient cooling systems, heat transfer modeling is a fundamental issue to address. Advanced computational fluid dynamics (CFD) calculations achieve sufficient accuracy, but the associated computational cost prevents an efficient integration in optimization loops. Surrogate models based on artificial neural networks (ANNs) offer a great speed advantage. It is shown that an ANN, trained on data extracted from samples of CFD simulations, is able to predict the maximum wall temperature along straight rocket engine cooling channels using methane with convincing precision. The combination of the ANN model with simple relations for pressure drop and enthalpy rise results in a complete reduced order model, which can be used for numerically efficient design space exploration and optimization. more...
530. Parametric analysis of heat transfer to supercritical pressure methane
- Author
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Francesco Nasuti and Annafederica Urbano
- Subjects
Propellant ,Regenerative cooling ,chemistry.chemical_compound ,Materials science ,chemistry ,Liquid-propellant rocket ,Heat transfer ,Context (language use) ,Mechanics ,Supercritical fluid ,Methane ,Coolant - Abstract
Methane is an interesting propellant to be used together with oxygen in a liquid rocket engine and has the required features to be used as a coolant in a regenerative cooling system also in the case of an expander cycle engine: in this context its behavior as a coolant ow must be controlled and this is complicated by the fact that methane could be in a near critical condition in the cooling channels and thus be subjected to high thermophysical properties variations. The present study investigates the heat transfer to methane looking at the inuence of the thermodynamic and transport properties variations on the methane heat transfer capabilities. In particular the heat transfer deterioration that could aect methane is deeply investigated. To carry out the necessary parametric studies a parabolized Navier Stokes solver developed by the authors has been used together with accurate equation of state and transport properties models able to describe methane in all the thermodynamic conditions of interest. more...
531. A note on the Ericsson refrigeration cycle of paramagnetic salt
- Author
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Zijun Yan and Jincan Chen
- Subjects
chemistry.chemical_classification ,Paramagnetism ,Regenerative cooling ,Specific heat ,Chemistry ,Stirling cycle ,General Physics and Astronomy ,Thermodynamics ,Refrigeration ,Salt (chemistry) - Abstract
It is pointed out that the Ericsson refrigeration cycle of a simple paramagnetic salt cannot possess the condition of perfect regeneration.
- Published
- 1989
- Full Text
- View/download PDF
532. 4462577 apparatus for gas cooling work parts under high pressure in a continuous heat treating vacuum furnace
- Author
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Herbert William Westeren
- Subjects
Air cooling ,Work (thermodynamics) ,Regenerative cooling ,Vacuum furnace ,Chemistry ,Heat transfer ,Mechanical engineering ,Gas cooling ,Condensed Matter Physics ,Instrumentation ,Seal (mechanical) ,Surfaces, Coatings and Films ,Heat treating - Abstract
A vacuum furnace having a heating chamber for heat treating work parts under vacuum therein, and a cooling chamber located adjacent to the heating chamber for receiving the heat treated work parts for the rapid cooling thereof, the work parts being rapidly cooled in the cooling chamber by the circulation of a cooling gas therein, a high-velocity fan being provided in the cooling chamber for the rapid circulation of the cooling gas over the work parts, heat transfer means located in the cooling chamber and over which the cooling gas is circulated for withdrawing heat therefrom after the passage of the gas over the work parts, and a unique door arrangement being located in the cooling chamber to insure the sealing of the cooling chamber both during the evacuation thereof upon transfer of the work parts thereto and during the cooling cycle therein, whereby in the cooling cycle the pressurized cooling gas within the cooling chamber acts to seal an inner door so that the use of exterior clamps and/or locks for sealing the cooling chamber is avoided. more...
- Published
- 1985
- Full Text
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533. Heating/cooling heat pump
- Author
-
Delrac Ltd
- Subjects
Chiller ,Regenerative cooling ,Thermoelectric cooling ,Materials science ,Mechanical Engineering ,Heat pump and refrigeration cycle ,Nuclear engineering ,Hybrid heat ,Building and Construction ,law.invention ,Reversing valve ,law ,Air source heat pumps ,Heat pump - Published
- 1983
- Full Text
- View/download PDF
Catalog
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