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Numerical approach to the modelling of transient interaction of prospective combustor concepts and conventional high pressure turbines
Propulsion and Power Research ( IF 5.3 ) Pub Date : 2019-02-14 , DOI: 10.1016/j.jppr.2019.01.008
F. Bakhtiari , H.-P. Schiffer

The Institute of Gas Turbines and Aerospace Propulsion at Technische Universität Darmstadt conducts research projects in the field of “combustor turbine interaction” (CTI). This paper presents numerical studies on the interaction between novel combustion concepts and conventional “high pressure turbine” (HPT) stages. In order to obtain higher efficiency and reduce emissions of jet engines, it is necessary to apply innovative and revolutionary technologies. The most promising technical solutions are based on the cycle processes, employing “pressure gain combustion” (PGC) methods. PGC methods provide a significant thermal efficiency enhancement and low NOx-emission rates at the same time. The investigations presented in this paper give information on the integrability of revolutionary combustion concepts into conventional engine architecture. This paper aims at providing insight into the numerical modelling of the transient behaviour of prospective combustion outflow and its influence on the operation of HPTs, especially on the first stage. The focus is on the aerodynamic effects and loss mechanisms within the blade passage. The interaction between the two components plays an important role. To study the performance under new conditions, an engine-like HPT geometry is used. This study reveals a decrease in turbine efficiency with transient inflow conditions compared to a steady-state inflow case. The decrease is primarily due to the interaction between transient inflow and the loss mechanisms in the turbine. The presented research was done as part of the project “Technologien für REVolutionäre Arbeits Prozesse” (TREVAP).



中文翻译:

预期燃烧器概念与常规高压涡轮机瞬态相互作用的数值模拟方法

达姆施塔特工业大学的燃气轮机和航空航天推进研究所在“燃烧器-涡轮相互作用”(CTI)领域开展研究项目。本文对新型燃烧概念与常规“高压涡轮”(HPT)级之间的相互作用进行了数值研究。为了获得更高的效率并减少喷气发动机的排放,有必要应用创新的革命性技术。最有前途的技术解决方案基于循环过程,采用“压力增益燃烧”(PGC)方法。PGC方法可显着提高热效率并降低NO x-同时排放。本文介绍的研究提供了有关革命性燃烧概念与常规发动机架构的可集成性的信息。本文旨在提供对预期燃烧流出的瞬态行为的数值模型及其对HPT(特别是第一阶段)运行的影响的洞察力。重点是叶片通道内的空气动力效应和损失机理。两个组件之间的相互作用起着重要作用。为了研究新条件下的性能,使用了类似引擎的HPT几何形状。这项研究表明,与稳态流入情况相比,瞬态流入条件下涡轮机效率会降低。减少的主要原因是瞬态流入与涡轮机中的损失机制之间的相互作用。所介绍的研究是“技术革新型技术”(TREVAP)项目的一部分。

更新日期:2019-02-14
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