FR2788813A1 - Centrifugal combustor for aircraft gas turbine has annular ducts to deflect air flow to central ejection nozzle - Google Patents

Abstract

The aircraft gas turbine has annular ducts (1) which selectively deflect the air flow and curve it towards the central axis where the flow ejection nozzle (5) is situated. The ejection nozzle is thus situated at the centre of a helical turbulent flow. This causes a continuous flow of fresh air.

Description

-1 -

  My invention is an airplane reactor designed to keep the advantages of turbo-

  reactor without having the disadvantages. I created it to be mounted on a wing with double lift action (which is another patent that I filed) because this present reactor allows in my opinion to rise much higher in the atmosphere. 11 can be used however on any plane ... The major drawback of the turbojet engine is that the "compression" (I would say centrifugation) is carried out by a mobile mechanical system

  This fact has important consequences: -

  - Manufacturing cost, complexity, shearing ...

  - Once a certain speed has been reached, the air intake is limited by the blades of the turbo,

  1 0 regardless (or almost) of the air density.

  What I propose here is a centrifugal motor entirely caused by fixed elements ... Without bearings, without lubrication, without risk of breakage ... My system also has the advantage of being able to put reactors on top of each other ( several reactors on a single block) (Fig 1 and 3) and to be able to put if necessary the common ejection nozzles 1 5 ... Here is the principle of this reactor: The principle is to transport the air by a movement vortex, from a position

  circular remote to a central position (like a sink that empties).

  To do this, you must separate the air flow from the inlet (1) by a cone (Fig 2).

  In this conical chimney the surface of the flow must remain the same what makes that the more the flow deviates from the axis and the more the walls of the chimney approach. Once the maximum width has been reached, the surface of the cone slips out towards the axis exponentially: This curvature causes the flow to fall towards the central nozzle and gives a general shape to this element which makes it look like a menhir. To facilitate the vortex of air, spiral partitions are installed either on the conical front part or on the rear part where the air drops towards the center (10) (or both). In my opinion, a simple priming on the conical part is enough because when the flow drops towards the center, it can only accentuate its swirling effect (like a cyclone). In addition this long spiral (Fig 2) allows

  keep the reactors on top of each other (fig 1).

  The result sought for the principle of my reactor and that the air which fell in the central ejection nozzle (5) swirls in a spiral (13) (a bit like a spring), which allows the general priming during from firing backwards. It is necessary to calculate the size (and the shape if it is necessary) of the first ejection chimney so that there is suction by the inlet mouth (1). We can use a conventional turbojet engine for this first central reactor if we want ... Once this reactor ejects gases backwards, it participates in the suction of air by other chimneys (if we chosen not to separate the ejection nozzles (Fig 4, Fig 1). Let's also say that by my method, it is allowed to install a double reactor (see page two) at the tail of the aircraft around the fuselage of the plane

  As if the plane itself was the central cone that spreads the air.

  -2- The swirl effect of my reactor is summed up by two angles ... First, the angle of attack of the flows on the central nozzle, in longitudinal section (Fig 1) which should just be sufficient to allow the initiation of the vortex which is characterized by the second angle: The angle of attack of the flow (coming from the chimneys) on the central nozzle (of ejection) in cross section which must be sufficient for it to avoid entering full force in the ejection flow of an interior (and previous) reactor. It is the addition of the two angles which determines the non-return function during combustion. The advantage of making several reactors superimposed with an ejection nozzle common allows to cause aspiration in the upper chimneys; to ignite more easily; space saving;

  1 0 a certain saving; an optimal return ...

  In the embodiment which I propose here, it is a tri-reactor suspended under the wing, with common ejection nozzle and therefore with multiple ejection stages. The areas of the inlet openings are: multiplied by 3 for reactor two compared to reactor one; and again multiplied by 2.7 for reactor three: The central reactor represents less than 10%

  and can be powered by a special fuel or replaced by a conventional reactor.

  1: entrances to chimneys one and two; 2: surface of the walls; 3: end of the spiral partition in the chimneys; 4: central reactor burner in the nozzle; 5: zone where the flow from the third chimney meets the gases ejected from reactors 1 and 2; 6: burner of the last reactor; 7: fuel supply pipe; 8: reactor (or assembly) support; 9: hollow area; 10: curved area of the chimney walls where the centrifuged flow falls towards the center; 11: support seen from the front in section; 12: mouth of the third reactor (in this drawing the spiral partitions start from the inlet while the reactors can be recessed one from the other) Fig 1); 13,14,15 (Fig 4): arrived with

  angle of the fresh air flows before ignition and ejection.

  Note that the effect of air rotation can destabilize the plane: it is therefore necessary to provide either two reaction blocks or else (if one installs for example the block at the tail of the aircraft) half of the chimneys which rotate air in one direction and half in the other direction but ending in separate nozzles (as if we split the reactor of Figure 3 in the vertical direction; the right part in a nozzle, the part

  left turning upside down in another) ...

  It should also be noted that the hollow parts (9) are the source of depressions which attract the

  flux. This data contributes to the general operation of the reactor ...

  Let’s finally say the practical implications of my invention ... This reactor, by opening gaping mouths, could climb to very high altitude with wings with double lift action and launch a space shuttle equipped with the same wings and with powder motors ... allows as I said at the beginning, to manufacture cheaper and more reliable reactors ... not to be limited in power by the mechanical system (to have a

  high power variability) ... etc ...

-3-

Claims (4)

  1) Pneumatic mechanism for an airplane reactor which makes it possible to bring a centrifuged air flow (rotating on itself while advancing) into the nozzle where combustion and ejection takes place without a mobile mechanism, characterized in that the flow is   first moved away from its axis and then fall back on the same axis while spinning.   2) Pneumatic mechanism according to claim 1 being an annular chimney (transversely) which separates the flow (air) from a central axis characterized by walls which progressively deviate from the central axis of the chimney and contain the flow , partitions (in the longitudinal direction) which curve gradually and which   put the flow in rotation in the annular chimney separating it into several parts.   3) Pneumatic mechanism according to claim 1, following the chimney of claim 2, which allows to return (fall) the flow (which accentuates the vortex or creates one) faster than it was removed in the axis of the burners and the nozzle where the gases will be ejected, characterized by an annular chimney, following the chimney of claim 2 (or not), bending rapidly (in the longitudinal direction), or decreasing 1 5 rapidly diameter (in the transverse direction), with partitions or not, which allows   accentuate the vortex and position it opposite the ejection nozzle.   4) Pneumatic mechanism according to claims 1,2,3 which allows to   superimposing annular chimneys on each other, or creating a reactor around a fuselage as if it were the last chimney, these chimneys being reactor mouths, which lead to a common nozzle or nozzles separated, characterized by superimposed chimneys spreading the flow and then returning it, the outermost chimney (or around a fuselage) may not have a partition   outside on the part that spreads the flow.   ) Pneumatic mechanism according to any one of claims 1 to 4,   allowing the superimposed annular chimneys to contain an increasing flow at each superposition and that they are of different length, which makes them end up in different places of the ejection nozzle allowing a reaction in several stages, characterized by chimneys joined by the mouth which curve in a different way, finding themselves separated by hollow spaces (double walls) and which arrive in a central nozzle in different places; this nozzle (in which combustion takes place) takes a larger diameter each time a new   annular chimney ends there to cause a new combustion.