Effect of Triangular Fins on Critical Heat Flux in Ethanol-Cooled Combustion Chamber

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Effect of Triangular Fins on Critical Heat Flux in Ethanol-Cooled Combustion Chamber Trans. JSASS Aerospace Tech. Japan Vol. 10, No. ists28, pp. Pa_43-Pa_48, 2012 Original Paper Effect of Triangular Fins on Critical Heat Flux in Ethanol-cooled Combustion Chamber 1) 2) 1) 1) 1) 1) By Masao TAKEGOSHI , Ryosuke SUZUKI , Toshihito SAITO , Fumiei ONO , Tetsuo HIRAIWA and Sadatake TOMIOKA 1) Japan Aerospace Exploration Agency, Kakuda, Japan 2) Tohoku University, Sendai, Japan (Received June 27th, 2011) A pressure-fed engine with a regeneratively-cooled combustion chamber is studied in JAXA. Operation chamber pressure is approximately 1 MPa. A proposed propellant combination is liquid oxygen and ethanol. However, it is necessary to understand the critical heat flux when ethanol is used as a coolant for regeneratively-cooled combustion chamber because the saturation pressure of it is 6.3 MPa. In general, it is known that the cooling wall with fins improves the cooling performance. In this study, the effect of triangular fins on critical heat flux of ethanol in ethanol-cooled combustion chamber was investigated. As the result, it was found that the critical heat flux of cooling wall with triangular fins was 23 % higher than that of that without fin in the same velocity condition of the coolant. The critical heat flux increases by the triangular fins on the cooling surface due to the effect of the combination cooling with film boiling and nucleate boiling. Key Words: Ethanol, Critical Heat Flux, Triangular Fin, Regenerative Cooling, Nucleate Boiling Nomenclature Ishimoto discussed to develop a small rocket-powered winged vehicle that will be launched from a platform aircraft and has P : pressure also conducted a concept study of such a flight demonstrator1). Pc : chamber pressure Because the ethanol is nontoxic, liquid at the room 2) Pf : fuel injection pressure temperature, and easy to handle as a fuel , rocket engines Po : oxygen injection pressure using LOX and ethanol seemed to be the most suitable for this q : heat flux reusable experimental vehicle. JAXA has started the r : radius development of technologies necessary to realize the reference 1) A pressure-fed engine with a regeneratively-cooled t : thickness systems . rocket combustion chamber3) was started to study in 2009. TC : thermocouple Operation chamber pressure is approximately 1 MPa. However, Tsat : saturation temperature it is necessary to understand the critical heat flux when it is Twall : wall temperature V : velocity used as a coolant for regeneratively-cooled combustion chamber because the saturation pressure of it is 6.3MPa. ΔT : degree of super heat sat Previous studies4,5) of critical heat flux for fluids at λ : thermal conductivity subcooling conditions have been conducted using electrically Subscripts heated tubes, and they indicated that the cooling performance bulk : bulk of ethanol was not enough for regeneratively-cooled c : surface of cooling side combustion chamber. On the other hand, Niino et al.6) reported CHF : critical heat flux that the critical heat flux was increased by the cooling wall EA : ethanol with triangular fins of water-cooled chamber. h : surface of heated side In this study, the effect of triangular fins on critical heat sub : subcooling flux of ethanol in ethanol-cooled combustion chamber was TC : at the position of thermocouple investigated experimentally. 1. Introduction 2. Experimental Procedure and Experimental Apparatus Experimental research work for the ethanol propulsion 2.1. Test facility and test apparatus system has been performed in JAXA/Space Transportation Figure 1 shows the simplified schematic of the test facility Mission Directorate as study for future reusable launch to measure the critical heat flux of ethanol under sub-cooling vehicle. LOX/ethanol rocket engine is thought to be one of the conditions. Combustion gas generated by gaseous hydrogen promising candidates to realize a next generation’s reusable and gaseous oxygen was used as a heat source. The launch vehicle with low cost and high frequency. Fujii and combustion chamber consisted of three water-cooled Copyright© 2012 by the Japan Society for Aeronautical and Space Sciences and ISTS. All rights reserved. Pa_43 Trans. JSASS Aerospace Tech. Japan Vol. 10, No. ists28 (2012) chambers and an ethanol-cooled chamber. Figure 2(a) shows chamber is 50 mm in diameter. The throat is 26 mm in the schematic of the test chamber. The lengths of water-cooled diameter. chambers were 100 mm and 142 mm for cylinder parts, and Eight co-axial injectors, each with an oxygen post and a 70 mm for the nozzle throat, respectively. The length of the hole in the faceplate, were installed at equal distance around ethanol-cooled cylinder chamber was 20 mm. The combustion the torch igniter. The inner path of the co-axial injector was for gaseous oxygen and outer path was for gaseous hydrogen. Vent The oxygen injector posts and faceplate were made of nickel. Regulated He supply The faceplate had twenty-four cooling fuel injection holes, each being 0.5 mm in diameter. Ethanol Two kinds of cooling passage were used for ethanol-cooled Tank combustion chambers. One is the cooling surface with (supply) triangular fins. Another is the cooling surface with flat surface. Figure 2(b) shows the contour of the cooling passage in detail. Flow meter The height of each fin is 1.5 mm. The coolant flows in the Cooling water P TC direction of the circumference of the chamber. The width of supply the cooling passage is 10 mm in width and 3mm in height. The thickness of the chamber wall was 4 mm. The wall Regulated temperature at the 2 mm from the surface and the bulk GH2 supply P TC Test section temperature of coolant ethanol was measured by thermocouple Torch Igniter at the position of 3/8 rounds away from the inlet. The pressure Combustion Hot gas flow of coolant ethanol was also measured with pressure chamber transducers at the position of 3/8 rounds away from the inlet. P TC 2.2. Procedure and test sequence Regulated In the electrically heated tube tests, the method that the Pc P TC GO2 supply heating power was increased in steps until the heat flux Vent approached a critical heat flux while keeping the flow rate and Cooling water pressure of coolant stable was used. In this study, the flow rate jettison Ethanol of ethanol at the critical heat flux was measured by decreasing Tank (return) the pressure of ethanol supply tank while keeping the chamber pressure stable. Fig. 1. Simplified schematic of the test stand for evaluation of the Figure 3 shows a typical test sequence of heating test. A cooling performance. typical test run started by filling the supply tank with Chamber pressure Fuel supply Water-cooled chamber Ethanol Fuel Spark supply plug Oxygen supply Torch igniter Fuel manifold Oxygen supply 100 142 20 41.5 Thermocouple Water-cooled nozzle (a) water-cooled chambers and an ethanol-cooled chamber (b) cooling passage with flat surface and with fins Fig. 2. Schematic of heating apparatus. Pa_44 M. TAKEGOSHI et al.: Effect of Triangular Fins on Critical Heat Flux in Ethanol-cooled Combustion Chamber Fig. 3. Typical test sequence. regulated helium gas. First, the shut-off valve for coolant was minutes after the temperature of hardware was steady. opened 8.0 s prior to ignition. The coolant flow was stabilized During tests, combustion chamber pressure (Pc), fuel at flow rate and back pressure set points prior to firing. A injection pressure (Pf), oxygen injection pressure (Po) and torch spark plug was operated 1.0 s prior to GH2 and GO2 coolant pressure (P) were measured with strain-gage pressure injections into the igniter. Though the oxygen supply to the transducers (PG-U series, KYOWA ELECTRONIC igniter was cut off 1.5 s after the onset of the main injection, INSTRUMENTS CO., LTD.). All pressure transducer was the hydrogen supply to the igniter was continued to cool the calibrated with pressure calibrator (Dead weight tester, PD27 injector faceplate. of Nagano Keiki CO., Ltd) before the tests. A sensor for 5 After stabilization of chamber pressure, the supply valve to MPa was used for Pc pressure measurement and coolant the ethanol tank was closed at 10.0 s. As the pressure of pressure measurement; measurement error was ± 0.01 MPa. A ethanol tank decreased automatically, the flow rate of coolant sensor for 10 MPa was used for Pf and Po pressure was decreased gradually. When the critical heat flux was measurement, measurement error being ± 0.02 MPa. reached, the wall temperature at the thermocouple showed a The test stand had turbine-type flowmeters to measure the sharp increase. The sharp increase in wall temperature flow rates of fuel, oxygen and ethanol directly, their indicated the drastic reduction in heat transfer coefficient of measurement error being ± 1 % in volume flow rate. Pressure the fluid as it transitioned to film boiling. When the wall and temperature within the supply lines close to the temperature exceeded 550 K, heating test was stopped flowmeters were monitored to deduce mass flow rate. The automatically. temperatures of coolants were measured by thermocouples of Heat flux was calculated based on the temperature type E (chromel-constantan thermocouple). The electronic difference between inlet and outlet, the specific heat, flow rate, cold junction compensation of acquisition device of National density of the coolant fluid. Coolant side wall temperature was Instruments Corporation was used for the temperature calculated based on the heat flux, conductivity of wall compensating. material, and wall temperature measured by thermocouple. The temperature of the chamber wall at 2 mm from the The heat flux to the wall was controlled by combustion surface was measured by thermocouples, as shown in Fig. 2. pressure. Combustion pressure was kept at constant during The points measured by thermocouples are indicated as TC.
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