SFB 1029: TurbIn - Substantial Efficiency Increase in Gas Turbines through Direct Use of Coupled Unsteady Combustion and Flow Dynamics

SFB 1029：TurbIn - 通过直接使用耦合非稳态燃烧和流动动力学大幅提高燃气轮机效率

• 批准号: 200291049
• 金额: --
• 依托单位: Universität Bayreuth
• 依托单位国家: 德国
• 项目类别: Collaborative Research Centres
• 财政年份: 2012
• 资助国家: 德国
• 起止时间: 2011-12-31 至 2020-12-31
• 项目状态: 已结题
• 来源: https://gepris.dfg.de/gepris/projekt/200291049?language=en
• 关键词: SFB; 1029; TurbIn; Substantial; Efficiency

A significant increase of the efficiency of gas turbines is the objective of the CRC 1029 and shall be achieved by changing the combustion concept towards an approximately constant volume combustion. Two concepts have been investigated up to now. While the pulsed detonation combustion bases on an extremely fast combustion triggered by shock waves, it also causes large pressure fluctuations. These are largely reduced by the alternative concept of a shockless explosion combustion, where a specific layering of the fuel and the utilization of acoustic phenomena lead to a homogeneous auto-ignition of the whole combustion tube. The third period of CRC 1029 will additionally include the rotating detonation combustion. Due to pressure waves travelling in circumferential direction at very high frequencies, this concept seems to be very promising for implementation in gas turbines as well.In contrast to conventional gas turbine processes, all described combustion concepts feature periodically unsteady pressure waves and will thus have a significant impact on the operating conditions of the turbomachinery components within the gas turbine. Methods and experiments have been investigated to effectively reduce the pressure pulsation at the interfaces between compressor, combustion chamber and turbine. Furthermore, sufficient cooling of the first turbine stage as well as flow stability at the compressor exit must be safeguarded and have thus been further focus areas of CRC 1029. One objective was to reduce the additional effort to a minimum to protect the overall efficiency gain of the whole gas turbine. Within the third period, the developed measures shall be driven towards a higher degree of maturity within relevant gas turbine conditions. For the same reason, the holistic assessment of the engine, which was solely based on well-developed thermodynamic methods so far will now be expanded to look at structural mechanics’ aspects as well.Within the third period, the achieved results of the projects shall coalesce in the setup of a demonstrator platform. It shall serve to develop process control strategies in different load regimes as well as to derive representative boundary conditions for the experiments with dedicated stand-alone rigs of compressor and turbine.

CRC 1029 的目标是显着提高燃气轮机的效率，并且应通过将燃烧概念改为近似恒定体积燃烧来实现。到目前为止，已经研究了两个概念。虽然脉冲爆震燃烧基于冲击波引发的极快燃烧，但它也会引起较大的压力波动。通过无冲击爆炸燃烧的替代概念，这些问题在很大程度上减少，其中燃料的特定分层和声学现象的利用导致整个燃烧管的均匀自燃。 CRC 1029 的第三阶段将额外包括旋转爆震燃烧。由于压力波以非常高的频率沿圆周方向传播，这一概念似乎也非常有希望在燃气轮机中实现。与传统的燃气轮机过程相比，所有描述的燃烧概念都以周期性不稳定压力波为特征，因此将对燃气轮机内涡轮机械部件的运行条件产生重大影响。研究了有效降低压气机、燃烧室和涡轮之间界面处的压力脉动的方法和实验。此外，必须保障第一涡轮级的充分冷却以及压缩机出口处的流动稳定性，因此成为 CRC 1029 的进一步重点领域。一个目标是将额外的工作量减少到最低限度，以保护整个燃气轮机的整体效率增益。在第三个时期内，所制定的措施应在相关燃气轮机条件下趋向更高程度的成熟度。出于同样的原因，迄今为止仅基于成熟的热力学方法的发动机整体评估现在也将扩展到结构力学方面。在第三阶段内，项目所取得的成果将在演示平台的建立中得到整合。它将用于开发不同负载状态下的过程控制策略，并为使用压缩机和涡轮机的专用独立装置进行实验得出代表性的边界条件。