AboutPaul Soderman Expertise Aeronautics, Fluid Mechanics, Aeroacoustics, Noise Control, Muffler Design, Wind Tunnel Research.... I know nothing about India - do not ask about schools, jobs, application requirements, career choices, etc. for India. Please, no text message verbiage; I prefer full words in full sentences. Thanks.
Experience 38 years as research engineer at NASA
Publications AIAA, NASA
Education/Credentials B.S. and M.S. Aeronautical Engineering - U. of Washington
Graduate work Standford U.
Awards and Honors AIAA Associate Fellow (American Institute of Aeronautics and Astronautics)
Question Dear sir;
In modern jet engine approximately two thirds of the total energy developed with in the combustion chamber is absorbed by the turbine wheel to sustain the operation of the compressor. the remain energy is discharged from the rear of the engine as high jet velocity jet, the reaction to which is thrust or forward movement of the engine. in turbo shaft and turboprop engine the same events happening to drive the rotor and propeller. The engine failure will leads to several disaster.
For high speed helicopter and high speed propeller driven aircraft, the propulsion system is the main problem. to over come the drag which is generated by the high speed helicopter should be counteract by the high speed turbo shaft engine. today this technology is not available. so there is pusher propeller is used in the helicopter to achieve the high speed. to use this pusher propeller will use more power generated by the engine.
the power generated by the engine is used by the main rotor as well as the tail rotor. tail rotor uses approximately 20-30 percent of power produce by the engine.
I have developed a multistage combustion jet engine. which will solve all the problem.
i am looking to test my technology in wind tunnel and in propulsion software. what kind of test is possible for the analysis of this technology. where can i get the basic equation to design an jet engine in all type.
Answer Vincent
I understand that you have a new idea for a multistage combustion engine. Multistage turbo compressors already exist, but you have not explained what is unique about your design. And your comments about helicopters seems confused - they do not use pusher propellers. But to get to your main question - what kind of test is possible. If you could convince NASA or an engine manufacturer to do testing for you, they would probably start with a static test on a thrust stand and measure the static performance. This is assuming they would build a prototype engine. If results were promising they could go into a wind tunnel test program to get flight effects and finally flight tests might be accomplished. As you can imagine this is all very expensive so you would have to have a very very good idea and some willingness to share ownership of the technology. For an individual to sell the idea to a big company would be extremely difficult... but possible.
I know of no software that would help your development. Your final statement is even more confusing because you are asking for an equation to design the engine. Usually, design precedes development so I assume your idea is very conceptual. There is no magic equation. Sounds to me like you need to study aircraft propulsion systems as a discipline to proceed.
Paul
