| Heavy-duty gas turbines reflect a country’s top scientific level and themachinery manufacturing cutting-edge technology, known as "the crown jewel ofthe equipment manufacturing industry." Today’s advanced gas turbine manufacturerhas introduced a heavy-duty gas turbine, compressor design has improvedcontinuously. In this paper, the turbine inlet temperature of1700℃beginning ofH-class ground heavy duty gas turbine, in order to reach its maximum efficiencypoint determines the compression ratio of16or more pressure than45multi-stagecompressor design objectives, based on multi-stage low degree of reaction designideas, put forward a set of multi-stage compressor design process and thedevelopment of appropriate design platform.This paper describes the design of multi-stage low degree of reaction designideas, by adjusting the rotor blades spin control imported pre-diffuser factor rotorblades, rotor blades to avoid flow separation, the substantial increase in totalpressure ratio under the premise to ensure the efficient rotor blades flow; Meanwhile,vanes or angled design to control the use of small diffuser vanes factor, or using alarge corner supplemented by efficient active flow control means in order to achievea larger diffuser vanes factor in the efficient flow. Based on this design hasdeveloped a multi-stage compressor low degree of reaction design platform, anddetermine a preliminary design:16adsorption pressure ratio compressor designpoint48above, isentropic efficiency still room for improvement, only was79%, andpolytropic efficiency87%surge margin of13.2%.Numeca using commercial software programs on the preliminary studiescarried out numerical simulations, and has design features characteristic of classaerodynamic performance analysis carried out confirmed the multi-stage low degreeof reaction feasibility and preliminary design ideas in the flow angle matchingprograms and Trail assigned to work on the deficiencies.This article will be applied to three-dimensional multi-stage compressor bladetechnology intermediate stage vanes, high-angled bend through different programscomparative study concluded that for smaller-scale flow separation, being bent toensure proper flow cascade the efficiency; but in the main area can not bear the endwall of the negative effects, the anti-molding technology in curved bladescorresponding to the static blade root, and root angle region disposed in the suctionstructure, in the suction surface the angle between the wall and the end zones arearranged several suction hole through the corner area to ensure that low-energy fluidsucked efficient flow angle region, which is also the structural design of the turbine cooling tie.Finally, working with adsorption compressor boundary layer suction techniquemainly to boundary layer suction to the means test and numerical simulationconfirmed in the form of holes instead of slots for boundary layer suction flow havethe same right significant control action, the structures suction holes equallysensitive to different locations. Meanwhile, for the selection of pumping solutions,has developed a program automatically optimizes suction design process, and basedon a multi-stage low degree of reaction last stage compressor stator blade suctionchannel pumping as study subjects the program automatically optimizes suctionobtained at selected points on the static cascade design, radial grooves programs andoptimal suction end suction surface angle region with tangential suction slot the bestsolution, the total pressure loss than the prototype down40%or more.This paper attempts to design a last diffuser factor of0.9over the last stagestator blade designs. The results show that in the final stage stationary blade designprocess, is able to achieve the diffuser flow factor above0.9is still worthy of furtherexploration. However, if the boundary layer suction to use technology to achievesuch a flow to the suction tank in the form of efforts to control significantly strongerthan the suction holes. |
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