Guoping Huang

Investigation of the Self-Starting ability of An Internal WaveRider Inlet for Ramjet

The Internal WaveRider Inlet (IWRI) is a new type of 3D inward turning inlet with rather good performance. It still has a difficulty, no enough good self-starting ability, when IWRI used as a geometry-fixed inlet for ramjets. At first, this research presented a theoretical analysis method of starting ability and self-starting ability for IWRI, to prove that the IWRI applied in ramjet was facing more difficult challenges of self-starting ability than scramjet. The self-starting ability should be considered in the process of designing ramjet inlet. Then, effects of bleeding mechanism on geometry-fixed ramjet IWRI was investigated by flow numerical simulation, and numerical results shown that IWRI’s selfstarting ability at low Mach numbers was improved obviously: lowest Mach number of selfstarting was decreased from 3.8 to 3.2, which also can endure the greater compression ratio of 32 than 28 with no bleeding. Two different groups of bleeding positions indicated that bleeding before throat section has no effect on the self-starting ability of IWRI.

An Improved Internal-Waverider-Inlet with High External-Compression for Ramjet Engine

A new type of Internal-Waverider-Inlet(IWR inlet) for Ramjet Engine is presented in this paper. It is based on the new High External-Compression basic flowfield called Internal Conical Flow C+ (ICFC+). Such new IWR inlet can improve the starting ability at lower Mach numbers than the previous design. The designing methodology of IWR inlet is presented. Analysis of such design shows that the basic flowfield is the key part in designing progress. A new method of generating characteristic lines is developed to evaluate the compressing efficiency of variable two dimensional flowfields. With the assistance of this method, the new High External-Compression basic flowfield ICFC+ is generated. One inlet was designed by using the ICFC and another inlet with same contraction ratio then was designed by using ICFC+. The numerical simulation results show that both inlets are capable of keeping their shock structures and other main flow characteristics exactly as their derived flowfield, thus resulting in capturing almost all upstream flow. But ICFC+ based inlet has better aerodynamic performance on low Mach number condition. Further, the higher compression ability led to shorter length of ICFC+ based inlet, which is helpful to inlet-engine integration design.

Flow Analysis and Improvement of a Micro Transonic Compressor Impeller

High pressure ratio micro mixed-flow compressor is a key component of the micro turbine engine. The total to total pressure ratio of a micro impeller used in a 12 cm-diameter turbine engine is about 5:1 at the design point, which can stand comparison with the most of micro compressor. In order to enhance the performance of the engine, the components need to be improved. This research presents the test results, numerical simulation of the prototype micro compressor (80mm diameter and 520m/s tip speed), and does some improvements of the micro impeller splitter.

A novel concept with self-driving fan for high bypass ratio turbofan engine

In order to manufacture turbofan engine with lower fuel consumption, researchers are doing their best to seek higher bypass ratio turbofan, Ultra High Bypass Ratio Turbofan, which unfortunately have been suffered from incompatibility of spool speed problem. A novel concept with self-driving fan for high bypass ratio turbofan, which utilizes a selfdriving fan, may serve as a solution to this problem. At first, this paper discussed the problems caused by high bypass ratio, then the difficulties of Geared Turbofan was analyzed. After that, The potential advantages of the novel turbofan were put forward. Secondly, design philosophy in top level was discussed and some important criterions were proposed, with which the novel turbofan can be compared to modern concept like GTF. Finally, selfdriving fan system, the main component of the novel turbofan is sketchily design and its flow field is numerically simulated in order to demonstrate the feasibility of this new concept.

High Bypass Ratio Turbofan Engine with Additional Tip-Driving Fan: a Design Innovation

In order to decrease the fuel consumption, an important way is increasing the bypass ratio of the turbofan engine. Unfortunately, as the bypass ratio becoming higher, turbofan would suffer Spool-Speed Mismatching Issue (SSMI). This paper proposed a design innovation of high bypass ratio turbofan, which comprised an additional Tip-Driving Fan (TDF), aiming to solve the SSMI problem. At first, this paper presented TDF turbofan concept which comprised a high bypass ratio fan and an air-turbine at the tip of the fan. Then the advantages of TDF and its potential were analyzed, based on the discussion of the SSMI and typical designs to solve it, for instance the Geared Turbofan. Secondly, thermodynamic and aerodynamic analyses for TDF were performed and some basic equations and principles were discussed, such as: energy loss, Load factors with different spool rotating speed, matched velocity setting of fan and air-turbine. Finally, the TDF blades, the key components of this new design was preliminarydesigned and the flow field was numerically simulated. The parameter research showed that a prototype turbofan which applied the TDF obtained higher bypass ratio, 25, than its original value 5.3.