Study on Combustion Performance of the Radial Staged Combustion Chamber with Lobed Nozzles

In order to investigate the effect of the radial gradation of the lobed nozzles on the flow field organization,a cold water model experimental platform for a combustion chamber with radial⁃staged 13-point lobed nozzles is built.Compared with a series of combustion OH*luminescence experiments tested by the University of Cincinnati,the four corresponding working conditions of no load,partial load,cruise and take off are selected.The vortex structure,vorticity value,multi-combustion materiel field and combustion characteristics of the flow field in the radial staged combustion chamber of the lobed nozzles under the equivalence ratio,the fuel injection method,the fuel injection ratio and other factors are numerically studied.The results show that under different influencing factors,the varation trend of the hydroxyl flame field of the lobe combustion chamber is basically the same as that of the hydroxyl light emission experiment of the swirl combustion chamber,but the flame field shape is quite different.The local equivalent ratio has a greater influence on the relevant combustion performance of the combustion chamber.Under the conditions of lower equivalence ratio,three-stage air and fuel injection mode,and gradually transferring the fuel flow of the pilot circuit to the external circuit,the temperature field and flame field of the combustion chamber are more evenly distributed,the outlet temperature field quality is better,the combustion efficiency is higher,and the NO_(X) emission is relatively low.These are basically consistent with the cold test results.The cold experimental results illustrate the importance of the influence of the flow field organization on the combustion organization and verify the reliability of the calculation results.

Effect of Fe_(2)O_(3) on the Formation of Micro Glass Beads under Air Staged Combustion

The effect of Fe_(2)O_(3) on the formation of micro glass beads(MGBs)under air staged combustion was studied.The experimental temperature was 1450℃,and Hegang bituminous coal was used as the experimental object.X⁃ray diffractometer(XRD),ash fusion tester,viscosity formula and scanning electron microscopy(SEM)were used to analyze the fly ash.Nano Measurer 1.2 software was used to measure the diameter of MGBs.The results showed that with the increase of Fe_(2)O_(3) in Hegang coal,the glass phase in fly ash first increased and then decreased.When the amount of Fe_(2)O_(3) was 15%,the content of the glass phase was the highest,which was 51.26%.The ash melting point first decreased and then increased,while the viscosity gradually decreased and the particles gradually became spherical.With the increase of Fe_(2)O_(3),the proportion of MGBs with particle size less than 10μm increased gradually.From the above results,it can be concluded that the addition of Fe_(2)O_(3) is conducive to the formation of MGBs and the reduction of particle size.

Turbulence Characteristics of Swirling Reacting Flow in a Combustor with Staged Air Injection

This paper presents an experimental investigation of the turbulent reacting flow in a swirl combustor with staged air injection. The air injected into the combustor is composed of the primary swirling jet and the secon-dary non-swirling jet. A three dimension-laser particle dynamic analyzer (PDA) was employed to measure the in-stantaneous gas velocity. The probability density functions (PDF) for the instantaneous gas axial and tangential ve-locities at each measuring location, as well as the radial profiles of the root mean square of fluctuating gas axial and tangential velocities and the second-order moment for the fluctuating gas axial and tangential velocities are ob-tained. The measured results delineate the turbulence properties of the swirling reacting flow under the conditions of staged combustion.

高压补燃液体火箭发动机推力室冷却技术及结构优化

The LM-5B launch vehicle has successfully completed four missions.Eight high-pressure staged combustion LOX/kerosene engines(YF-100)are equipped in the four boosters of the LM-5B,two in each booster.The YF-100 engine adopts various cooling techniques to ensure cooling,including a metal thermal barrier coating,multiple liquid film cooling slots,spiral milled regenerative cooling channels with high aspect ratio,a non-weld forming thrust chamber and an optimal cooling flow path design.In addition,the 480-ton LOX/kerosene engine for China’s future heavy-lift launch vehicle LM-9 will be larger in size,which makes it more difficult to be developed and will have more strict requirements in the cooling process.The main differences between the LM-5B and LM-5 are briefly described in this paper and the development process and working characteristics of YF-100 engines are introduced.The advantages and disadvantages of main cooling methods used in the thrust chambers of high-thrust liquid propellant engines are also described.Finally,the future challenges and countermeasures in cooling technology for China’s high-thrust LOX/kerosene engines and future reusable rocket engines are also presented.

The Reduction of Thermal Nitrogen Oxides (NOx) Emission Using Staged Combustion in Furnace

The experimental study described in this paper is to investigate the control of thermal nitrogen oxides emissions from a 2.28 MW gas-fired test furnace. Tests, including changing axial or radial air flow rate, adding cooling water, and adding staged air, were performed to characterize and opimize the fuel-rich burning zone and the fuel-lean burnout zone independently. Detailed measurements of O_2, CO_2, CO, NO and NOx were made at the fuel-rich burning zone and furnace exit. The influence of forming CO, NO and NOx was examined. Results indicated that adding staged air in the fuel-rich burning zone (75 cm from burner) will reduce the mawximum NO and NO_x emissions. Adding cooling water in a right position may further lower the NO and NO_x emissions. In addition, the least formation of thermal nitrogen oxides in the first stooge fuel-rich bunting zone will occur at the stoichiometric ratio's inverse value, (φ_1)^(-1), 0.65 to 0.7.

NO_(x) and H_(2)S formation in the reductive zone of air-staged combustion of pulverized blended coals

Low NO_(x) combustion of blended coals is widely used in coal-fired boilers in China to control NO_(x) emission;thus,it is necessary to understand the formation mechanism of NO_(x) and H2S during the combustion of blended coals.This paper focused on the investigation of reductive gases in the formation of NO_(x) and H2S in the reductive zone of blended coals during combustion.Experiments with Zhundong(ZD)and Commercial(GE)coal and their blends with different mixing ratios were conducted in a drop tube furnace at 1200℃–1400℃with an excessive air ratio of 0.6–1.2.The coal conversion and formation characteristics of CO,H_(2)S,and NO_(x) in the fuelrich zone were carefully studied under different experimental conditions for different blend ratios.Blending ZD into GE was found to increase not only the coal conversion but also the concentrations of CO and H2S as NO reduction accelerated.Both the CO and H2S concentrations inblended coal combustion increase with an increase in the combustion temperature and a decrease in the excessive air ratio.Based on accumulated experimental data,one interesting finding was that NO and H2S from blended coal combustion were almost directly dependent on the CO concentration,and the CO concentration of the blended coal combustion depended on the single char gasification conversion.Thus,CO,NO_(x),and H2S formation characteristics from blended coal combustion can be well predicted by single char gasification kinetics.

A Review of Throttling Technology Development for Large-Thrust Liquid Rocket Engines

Throttling of large-thrust liquid rocket engines,which can improve mission adaptability of a carrier rocket,reduce risk and facilitate rocket recovery,is a key technology for current and future space development.This paper summarizes the state of the art and trends of throttling technology for large-thrust liquid rocket engines at home and abroad.According to the working principles of propulsion for rocket engines,throttling the propellant flow rate is a major way of adjusting thrust,and regulation devices along with adjustable injectors are primary measures of throttling propellant flow rates.This paper clarifies the working principles of typical regulation devices and adjustable injectors,introduces the regulation schemes of typical large-thrust engines such as YF-100,RD-170,and SSME,and summarizes the main characteristics of current throttleable large-thrust engines.Finally,critical technologies and development trends of throttling are discussed,including combustion stability and reliable cooling of thrust chambers at low thrust levels,turbopump stability,and stable regulation and precise control in a wide range of operating conditions.

Fluidized bed combustion of high water content alcohol extracted herb residue and the impacts of blending wasted activated coke

Combustion of herb residues(HRs)for heat recovery is a good way for their utilization,but there exists such a problem as high concentration NOx emission in flue gas.The alcohol extracted herb residue(AEHR),one special type of HRs,was chosen as the object and was subjected to immediate combustion in a fluidized bed reactor to investigate the characteristics of its resulting NOx emission.The results showed that,most of the NOx in the flue gas was produced from the char nitrogen(C-N);as the fuel water content increased,the NOx emission concentration exhibited a trend of first decreasing and then increasing;and a properly low combustion temperature inhibited the NOx emission upon the premise of ensuring full combustion.Air staging combustion was adopted to effectively control NOx:the NOx emission concentration in the flue gas was reduced to 296 mg⋅m􀀀3 and the NOx emission reduction rate reached 46.51%compared to conventional combustion.Co-combustion by blending wasted activated coke(WAC)into the AEHR helped both stabilize the combustion state and reduce further the NOx emission.When the blending ratio of WAC fell within a proper range of 20-30%,the NOx emission concentration in the flue gas was as low as 231.4 mg⋅m􀀀3.In addition to the dilution effect of the combustion flue gas of the blended WAC,the local reducing atmosphere caused by its incomplete combustion as well as its strong absorbability and catalytical effect was accountable for the further decrease of the NOx emission concentration.