the jet propulsion with closed combustion type

[qumf]

Originally Posted by goku

it helps me to understand the engines if i can see them turning.
i've always been facinated with engines and motors,
the creators of such are the true smart people

If it became ture, it will be the best, better than anything,
If somebody wants to make it out, I will try my best to cooperate.

[cwes99_03]

I suggest contacting the site creator. He seems to be the best guy to help you make a gif of what you want to create.

[qumf]

Sorry.
I would like to call :"the jet engine with consistent-volume combustion" instead of the old one.The new one will be more fit the fact. The varied volume combustion also can be closed combustion. Can I change the post name?
When I first proposed the thought by patent, It called" the jet propulsion with consistent-volume combustion"

[qumf]

You have seen the conception picture. Now I state the work procedure.

Let us review the current jet engine's work procedure: the first step is that compressor suck air and increase the pressure to high level, the air enter combustion chamber, be mixed with fuel, burning, during the course the pressure remain consistent in chamber; after complete burning, gas goes out of chamber and drives turbine; turbine transmit the power to the compressor ahead; at last the gas utiliza the rest energy to accelerate itself to push jet engine.

In my design: The first step of jet propulsion's work procedure is that the blower suck air and increase it to proper pressure, mix fuel as well; then through a pipe the gas enter the combustion chambers, after the front door and back door close, then burning inside chambers and the pressure increase rapidly, the back door open; the gas is spouted out into the branch pipe; then general pipe, around the joining point of the two pipes there is a little turbine to get power for the blower ahead. After the branch pipe the gases converge, flow out off the engine so as to give whole engine a consistent push force .

Upper I state two work courses, there is another course, at the end of the spouting course, the front door of chamber opens, the fresh gas enters meanwhile drive the waste gas out off the chamber. So the chambers spout gas alternatively. All courses are controlled by chambers’ front door and back door. In common case, there are always two chambers at the same course.All chamber arrange as a circle. the section shape of chamber is round or close to round.

As to one chamber, it has over 5500 times combustions every minute, otherwise it might have no enough advantage compete the current jet engine.

I suggest You also should see the first paragraph of this post about this jet engine's advantage.

About the attached picture:The left one is the section per axis, it show almost all main parts.The another two pictures show the main parts: the front door and back door of the combustion chambers. two doors control and regulate work to complete combustion one by one. anyone of chamber sometimes sucks mixure gas,simetimes has combution inside; sometimes spout gas. So the chamber sometimes is sealed;sometimes open on both side;sometimes open on one side. So the door has openings(slot) in it.The doors rotate at same speed and coperate.

As the amount of chamber and their shape,I think it is 6 or 8. It depends on the utilization rate of space;parts strength; work cooperation conveniently and so on.

Later I will analyse the performance.

[qumf]

The biggest difficulties to realize the new type jet engine are:
1. The force that some parts bear are not steady, It is harmful for these parts. My method is make parts bear force from pulling force to pressure or both. Thus that would be better. But it will be a little weigh after this measurement.
2. To regulate the work procedure for high efficiency, safety, and economy is really hard, but the jet have to work under many circumstances. The simple countermeasures are: 1. Set the engine rotation speed within a certain range while working. Out off the tolerance the engine will be inefficient, even dangerous. 2. Change the turbine’s position to some extent, move it forward and backward; change the flow resistance in general pipe; change the shape of the general pipe. 3. If necessary we can add openings or bypass on the general pipe.

Temporary I shall set the rotate speed of the chamber’s front door and back door at 5000~ 6500rpm, the blower’s rotate speed will be higher a lot. Set the gas pressure from blower increase by 30%. As to the chamber: length: diameter=1.5: 1 (All these datas depend on the size of engine)

I roughly calculate an example of the kind of jet. The size is petty big.
1. While without move, the pulling force per engine’s section area is less than current the most advanced engine by 15% because at this time there isn’t enough gas and rotate speed is limited. Once the jet begins to move, the situation will turn better.
2. to compare with the current jet, If they have same pulling force, the new type jet’s lighter by 30% (I estimate some components, maybe more actually)
3. to compare with the current jet, the efficiency of this jet is higher by over 80%
Regarding to common jet engine, the last two specifications are more important.
I have stated merit and dismerit. everybody,Is it worth practice?

[GAHD]

asssuming you are right in regards to feul efficiency and weight reduction it would be very worth it to develop the design. What you need is a prototype to make your claims more concrete.

I would like to know what makes you think it will be over 80% more efficient, that's quite the large number.

[qumf]

Dear GAHD:

I said "the efficiency is higher by 80%" because I only considered the two main parts' effect.compressor and turbine related to the current jet engine.blower and turbine related to my jet engine.I didn't considered the loss of energy at other portions(courses)' influence,such as convergence of gas.I think these influences are comparatively small or similar between two type of jet engines.
I ever calculated a common current jet engine before, the energy from spouted gas that can be utilized, about 70% of them will be absorbed by turbine for the compressor ahead.according to some specialized book I know the efficiency of compressor is 60% or less.The turbine in my engine can only absorbs 30% of the energy because the blower needn't increase the pressure so high. The blower's efficiency can get 85%.
Based on the premises, I said so. The proportion of efficiency 80% is acomparative data, not absolute data. Though some other course may influence the whole efficiency to big extent that I ignore improperly, I still think my engine' efficiency must be very high.
Who can guide me how to calculate the loss of energy at other course?
If the data I state here has some wrong or I misunderstand, pls point out.

[Ver]

Hi
Just a couple of thoughts re your engine qumf
Where will the drive for the doors be taken from.-- I presume there will be a reduction gearbox.
Will the doors to the combustion chamber remain flat as in the diagram.
Is the first compartment after the compressor an accumulator of sorts.
What size aircraft would you put it on.
What about noise because it is pure jet thrust and no bypass, considering modern bypass can put out perhaps 70 000lb thrust and more. A pure jet at those thrust levels with pulse system combustion may be a little noisy.
The basic system looks interesting. I hope you overcome any problems you encounter.
regards Dave R

[qumf]

Dear Dave R:

Thank you remind me these questions.
to drive the doors,I think I will use reduction gearbox. The consumed energy is small because we only need rotate the two doors . For now I would set the reduction rate (from turbine to doors )as 3~3.5 The gearbox is small.I did n't show the component in diagram.
In the example I calculated, the section area of the jet engine's out circle is 1.4 squre meter. i'm sure we can use small size. I think we can adopt it in ship firstly because We can cool it conviently and safety.We will use different parameters for different size of jet engine.
Truly spouting gas discontinously will cause noise.So big noise will happen in branch pipes. the gas from the commen piston type internal combustion engine( I don't know how to call by english) is also discontinuous.In fact over half of noise spread out from opening in this type of internal combustion engine. At the opening of the general pipe of my jet,the flow can be ensured steady and uniform . So the noise can be reduce. On the other side, all work course exist at any time. the noise might be absorbed each other.(to be confirmed by prctise), another method:I take some measurement on the branch pipes.absorb noise and insulate noise and make less noise happen.
I would like you say it feasible than interesting.
Thanks QMF

[Ver]

Hi
I understand you may use it in a ship first. Ok- cooling and noise no problem.
I would be interested in your drive system in a ship. Perhaps a free turbine or adding an extra turbine and driving off the compressor shaft. How will you do that?

the noise might be absorbed each other

Do you mean noise cancelling perhaps.
I can see this working but you are brave to take it on and you have seen some of the stress problems that may arise. I hope it all goes well
regards Dave R.