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.

该项目着手将著名的理论理想与实现它的新方法相结合。摄入缓慢移动的边界层流体以有效地推进车辆是一个完善的目标（用于船舶和潜艇），但到目前为止，该本金尚未成功应用于飞机推进。由于最近努力设计更高效，更嘈杂的飞机，此处提出的新方法变得及时且实用。新飞机的偏爱布局利用了一个大型提升表面，即所谓的“混合翼主体”，并结合表面安装的发动机摄入边界层流体。发动机将安装在机翼上方，以减少地面上的噪声。摄入边界层流体的引擎的基本挑战是进入发动机的空气的不均匀或变形的速度。传统的风扇发动机不会在没有可操作性严重损失的情况下接受扭曲的入口流。围绕此问题的一种可能的方法是将与机翼表面相邻的缓慢移动空气与从机翼上方的更远的空气中取出的自由流空气混合。混合过程效率低下，因此减少了边界层摄入的理论优势。但是，这里提出了一种新方法，可以修改常规航空引擎的粉丝以接受扭曲的边界层流，而无需预混合。该项目计划使用计算和实验测试和开发新的粉丝设计。最终的目的是开发一个新型的航空发动机风扇，该风扇将接受变形的入口速度曲线，而不会显着丧失可操作性或效率，同时向发动机的其余部分提供了接近正常的流量分布。