Fan system for a boundary layer ingesting jet engine

用于边界层吸入喷气发动机的风扇系统

基本信息

批准号：
EP/F015070/1
负责人：
Cesare Hall
金额：
$ 38.6万
依托单位：
University of Cambridge
依托单位国家：
英国
项目类别：
Research Grant
财政年份：
2008
资助国家：
英国
起止时间：
2008 至无数据
项目状态：
已结题

来源：
https://gtr.ukri.org/projects?ref=EP%2FF015070%2F1
关键词：
Fan system boundary layer ingesting

项目摘要

This project sets out to combine a well-known theoretical ideal with a new practical approach to achieving it. The ingestion of slow moving boundary layer fluid for the efficient propulsion of a vehicle is a well-established objective (used in ships and submarines), but so far this principal has not been successfully applied to aircraft propulsion. The new approach proposed here becomes timely and practical as a consequence of recent efforts to design more efficient, and less noisy, aircraft. The favoured layout of the new aircraft makes use of a large lifting surface, the so called 'blended wing body', in conjunction with surface mounted engines ingesting boundary layer fluid. The engines would be mounted above the wing to reduce noise on the ground.The fundamental challenge for engines ingesting boundary layer fluid is the non-uniform, or distorted, velocity profile of the air entering the engine. Conventional fan engines will not accept distorted inlet flow without serious loss of operability. A possible way around this problem is to mix the slow moving air adjacent to the wing surface with free stream air taken from further above the wing. The mixing process is inefficient and so the theoretical advantage of boundary layer ingestion is reduced. However, a new approach is proposed here in which the fan of a conventional aero-engine can be modified to accept distorted boundary layer flow without the need for pre-mixing. This project plans to test and develop the new fan design using both calculations and experiments. The ultimate aim is to develop a novel aero-engine fan that will accept a distorted inlet velocity profile, without significant loss of operability or efficiency, whilst delivering a near normal flow distribution to the remainder of the engine.

该项目旨在将众所周知的理论理想与实现它的新实践方法相结合。吸入缓慢移动的边界层流体以实现车辆的有效推进是一个既定的目标（用于船舶和潜艇），但到目前为止，这一原理尚未成功应用于飞机推进。由于最近努力设计更高效、噪音更低的飞机，这里提出的新方法变得及时且实用。新飞机的受欢迎的布局利用了大的升力表面，即所谓的“混合翼体”，与吸入边界层流体的表面安装发动机相结合。发动机将安装在机翼上方，以减少地面噪音。发动机吸入边界层流体的根本挑战是进入发动机的空气速度分布不均匀或扭曲。传统的风扇发动机无法接受扭曲的进气流，而不会严重影响可操作性。解决这个问题的一种可能的方法是将机翼表面附近的缓慢移动的空气与从机翼上方更远的地方获取的自由流空气混合。混合过程效率低下，因此边界层吸入的理论优势降低了。然而，这里提出了一种新方法，其中可以修改传统航空发动机的风扇以接受扭曲的边界层流，而不需要预混合。该项目计划通过计算和实验来测试和开发新的风扇设计。最终目标是开发一种新型航空发动机风扇，该风扇能够接受扭曲的入口速度分布，而不会显着损失可操作性或效率，同时向发动机的其余部分提供接近正常的流量分布。