Design Principle and Cycle Analysis of Millimeter-Scale Micro-Turbine

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Design Principle and Cycle Analysis of Millimeter-Scale Micro-Turbine

更新时间：2025-05-08

- Design Principle and Cycle Analysis of Millimeter-Scale Micro-Turbine
- Vol. 45, Issue 5, Pages: 42-46+93(2011)
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
- DOI：
  CLC： TK124
- Online First：10 May 2011，
  
  Published：2011
- 稿件说明：
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Design Principle and Cycle Analysis of Millimeter-Scale Micro-Turbine[J]. 2011, 45(5): 42-46+93.
DOI：

Design Principle and Cycle Analysis of Millimeter-Scale Micro-Turbine[J]. 2011, 45(5): 42-46+93. DOI：

摘要

针对多学科领域中毫米级微型燃气轮机系统的设计原则、性能参数选取和整体可实现性条件进行了理论综述、对比研究和量化分析.结果表明:由于毫米级微型燃气轮机系统通常采用无回热器结构的布雷顿简单循环体系

压气机与透平主要受到低Re流动的影响和二维几何结构的限制

因此在设计时需利用不同叶片厚度来分布控制流动分离

并采用相同叶高且间隙分别是弦长和叶高的0.2%和1%; 间隙泄漏、传热损失、转捩流动、出口损失和尺寸效应等因素对性能的影响不容忽视; 微型燃烧室设计要求确保充分预混并采用小当量流量比稳定燃烧; 装置材料应选用高强度系数的耐高温陶瓷、硅或合金

轴承采用高稳定性气体轴承.通过循环分析表明

微型燃气轮机要达成10

W级的可实现性循环

透平进口温度应大于1 100 K

压比大于3

压气机和透平的效率分别达到70%和75%

流量控制在2 g/s以下

叶轮的直径转速乘积达到8 500 mm·r/min

燃烧室总压损失不超过5%.

Abstract

The design method

selection of performance parameters

and feasibility condition for millimeter-scale micro-turbine systems were discussed and analyzed. The results indicate that because the simple Brayton cycle without a regenerator is adopted in the design of micro-turbines

and the micro-compressors and micro-turbines are affected by flow with low Reynolds number and restricted by two-dimensional geometry

the different blade thickness distribution is used to control separation and the same blade height is applied with the tip clearance of 0.2% chord and 1% blade height. The performance degradation caused by leakage flow

heat loss

transition

exit loss and scaling effect should not be neglected in the design. The adequate mixing of fuel and low equivalence ratio combustion are needed in the micro-combustor design. The high stiffness material is required

and the gas bearings and rotors with high stability are recommended for the system. The cycle analysis shows that the turbine inlet temperature of more than 1 100 K

pressure ratio of over 3

compressor efficiency of 70% and turbine efficiency of 75%

mass flow of below 2 g/s

impeller DN value of 8500

and total pressure loss of less than 5% in the micro-combustor are needed to realize a 100 W-class micro-turbine cycle.

关键词

Keywords

references

EPSTEIN A H. Millimeter-scale, MEMS gas turbine engines [J]. ASME Journal of Engineering for Gas Turbines and Power, 2004, 126(2):205-226.

EPSTEIN A H, SENTURIA S D, AL-MIDANI O, et al. Micro-heat engines, gas turbines, and rocket engines [C]∥Proceedings of the 28th AIAA Fluid Dynamics Conference. Reston, VA, USA: AIAA, 1997: 1773.

PEIRS J, REYNAERTS D, VERPLAETESN F, et al. A microturbine for electric power generation[J]. Sensors and Actuators: A Physical, 2004, 113(1):86-93.

EPSTEIN A H, SENTURIA S D. Macro power from micro machinery [J]. Science, 1997, 276(5316):1211.

JACOBSON S A. Aerothermal challenges in the design of a microfabricated gas turbine engine [C]∥Proceeding of the 29th AIAA Fluid Dynamics Conference. Reston, VA, USA: AIAA, 1998:2545.

FU Lei, SHI Yan, DENG Qinghua, et al. Aerodynamic design and numerical investigation on overall performance of a micro radial turbine with millimeter-scale [J]. ASME Journal of Engineering for Gas Turbine and Power, 2010, 132(3):2301-2309.

付雷, 石龑, 邓清华,等. 毫米级微型透平的气动优化设计研究 [J]. 西安交通大学学报,2009,43(1):15-19.

FU Lei, SHI Yan, DENG Qinghua, et al. Aerodynamic design and optimization of a radial inflow millimeter-scale turbine [J]. Journal of Xi'an Jiaotong University, 2009, 43(1):15-19.

付雷, 邓清华, 丰镇平. 微型向心透平级速比与DN值的最优选择 [J]. 西安交通大学学报, 2009, 43(7):16-20.

FU Lei, DENG Qinghua, FENG Zhenping. Analysis and optimal selection of stage velocity ratio and DN-value for micro radial turbine [J]. Journal of Xi'an Jiaotong Univerisity, 2009, 43(7):16-20.

ISOMURA K, MURAYAMA M, TERAMOTO S, et al. Experiment verification of the feasibility of a 100 W class micro-scale gas turbine at an impeller diameter of 10 mm [J]. Journal of Micromechanics and Microengineering, 2006, 16(9): 254-261.

GROSHENRY C. Preliminary design study of a micro-gas turbine engine [D]. Cambridge, MA, USA: MIT,1995.

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