DE3413954A1 - Method for suppressing the induced surrounding incident flow in the event of baffle plate flow - Google Patents

Abstract

Deflector flows generate a flow-induced surrounding incident flow which can be a hindrance in many cases where this flow is used, for example in the launch of rockets, vertical take-off aircraft, helicopters etc. By arranging rotationally symmetrical components in the flow field, this induced surrounding incident flow can be suppressed during baffle plate flow. The necessary measures can be extended in that an additional thrust is obtained and/or components are protected against thermal overloading by means of minimal structural alterations and the addition of water.

Description

Process for suppressing the

induced Um @ e @ d inflow flow with pralIpate flow.

2. Description.

Prof. @atthias Brünig, 2000 Hamburg 65 Prof. Dr.-Ing. Werner Möller, 2000 Hamburg 61 Process for suppressing the induced surrounding inflow flow with flapper flow.

The invention relates to the application of a flow according to According to the preamble of claim 1, the physically determined inflow mass a flapper flow, which normally flows in from the wider area and may cause a strong inflow flow, including the weight of the primary flow can be removed.

The invention can also be used in the application a flow according to claim 1 changed direction of flow of the outflowing Volume resp.

Mass flow, occurring flow forces directed, which, by The addition of water for the purpose of generating water vapor can also be enlarged.

The starting point of the present invention is the known flapper flow, in which a jet comes from a nozzle, a diffuser or a staurolir, perpendicular hits a wall and then spreads out along the wall like a plate diffuser.

While in the patent applications with the file number P 32 29 653.3-13 and P 34 06 868.6 the fact is used that the nozzle, 1) iffusor or Pitot tube current a multiple of its own volume per unit of time sucks in from the wider area, the present invention is directed to to suppress this surrounding inflow flow as far as possible. Through this surrounding inflow flow This is because additional frictional forces arise, e.g. when a rocket is launched, which counteract the direction of thrust and Move @ to suppression the induced surrounding inflow flow in the case of flapper flow.

thus slowing down the rocket considerably in the launch phase.

The conditions for vertical take-offs and helicopters are similar before.

The present invention is based, inter alia, on the object to prevent these currents, which e.g.

adversely affect the launch of a rocket. Another goal is otherwise unused, high-energy flow areas in the flapper flow usable in order to achieve an additional boost, e.g. on the Bodeil a missile could work.

The attached figures are intended as an example of some possibilities show how these goals can be achieved by arranging suitable components.

Fig. 1 shows the conditions in an axial section for a normal Bulging; batten flow.

Fig. 2 shows in axial section the arrangement of the deflection part for suppression the surrounding inflow.

Fig. 3 shows in axial section the arrangement of the deflection part for partial Redirection of the plate diffuser-like flow.

Fig. 4 shows in an axial section the arrangement of the segments for partial Return of the plate diffuser-like flow.

Fig. 5 shows in axial section the arrangement and design of the deflection part as well as the position of the second baffle plate for using the additional thrust.

Method for suppressing the induced ambient inflow flow with flapper flow.

w. Explanations of the figures.

The basic flow pattern of a baffle plate flow is based Figure 1 shows.

The one from a nozzle, a diffuser, a pitot tube (1) or the like primary volume or mass flow emerging and striking a baffle plate (2) creates a rotationally symmetrical flow pattern, essentially consisting of one: 1. primary flow 1.1 cone diffuser-like flow (3) 1.2 plate diffuser-like Flow (4) 2. Secondary flow 2.1 Environment inflow flow (5) 2.2 Return flow (5) With regard to the surrounding inflow flow, it can be determined that they is directed essentially towards the deflection point (6).

The secondary flow, in particular as an Emfeld inflow flow, can be a hindrance in some applications, e.g. when launching the rocket.

When a rocket launches, they propagate at a very high speed emitted gases, as shown in Figure 1 on the ground. Thereby air (5, inflow flow) from the environment at a correspondingly high speed from the escaping gases sucked in.

The direction of flow of the surrounding inflow is the direction of movement but essentially directed exactly in the opposite direction to the rocket. This will be during the start phase, because of the already existing high relative speed, Effective frictional forces along the missile body. These counteract the thrust. In addition, equipment and devices in the start area are protected by the here as Noise field that becomes effective in the downward flow of the incoming flow (5) is endangered.

According to the invention, the disruptive surrounding inflow flow is corresponding the claims 1 and 2 prevented, Procedure: 2îlm suppression the induced surrounding inflow flow with flapper plate flow that - as in figure 2 - the plate diffuser-like flow (4) of the flapper flow by means of a rotationally symmetrical}, it connecting part (7) in its radial all width limited and the IT deflection of the flow to the cone diffuser-like flow area (3) or the deflection point (6) is forced.

The inventors of the present invention have recognized that physically conditional inflow volume is not necessarily deducted from the wider environment must be taken directly from the plate diffuser-like flow (4) can, which then largely suppressed the actual surrounding inflow flow will. After the equilibrium has been reached, one of the gas quantities introduced will flow corresponding amount (8) from the deflection part (7), against the direction of flow in the conical diffuser-like flow area (3), as an annular jet (8).

It is also possible that, when applying that characterized according to claim 2 Device (7) to prevent counter-rotating ring jet flow (8) occurring, by only diverting part of the mass flow (4) and the remaining part of can flow freely elsewhere.

According to claim 3, as set out in Figure 3, the claim 2 named device (7) at a distance parallel to the baffle plate (2), e.g. radially extending ribs (9), arranged.

When the device is arranged in the manner described, not only the surrounding inflow flow (5) but also the unfavorable under certain circumstances effecting annular flow (8) largely prevented, since a Gas volume flow corresponding to the volume or mass flow (10) above the ground-level Cylinder jacket slot can flow off. The retention of an annular deflecting part (7) could be related to the geometric dimensions and also strength-related Have advantages over the, according to claim 4 and shown in Figure 4, procedure to suppress the induced surrounding inflow flow in the case of flapper flow.

Segmentation of the device (7) mentioned in claim 2.

Rei the illustrated arrangement of several segments (11) - iii of the figure 4 it would be e.g. three - if the partial mass flow (10) flows between the segments (11) in full height through, while in that, through the circumferential extent of the segments defined sector area, the full deflection of the mass flow (4) takes place.

The possibility of articular diversion shown here points to, on the other hand that described in claim 3, the advantage of better adaptation to variable Conditions on. Such a variable variable is e.g. the mass flow (3) hotter Gases when launching rockets of different sizes. To optimize the situation at different missile types could easily be the centric distance to the center of the Flapper flow and / or the number of segments can be changed.

The elevation of the segments, through supports (9) and thus a combination of the devices according to claim 7 and 4 is also possible.

The present invention is directed further and in context with claims 1 and 2 on the use of at least a part of the baffle flow remaining kinetic and thermal energy amounts.

According to claim 5, iii of Figure 5 is the device according to claim 2 shown in a modified form in such a way that the outlet area of the deflection part (7) is nozzle-shaped. The annular mass flow (8) retains a corresponding high speed, so that when it hits the second baffle plate, e.g. Missile floor (12), an additional thrust takes effect during the lift-off phase.

The arrangement of a Schtitzmantels (13) un the jet exit area on the rocket floor (12) forces the deflection of the entire ring jet (8) radially to the outside, without the primary jet (3) in the exit area being caused by cross currents being affected.

Move @ to suppress the induced surrounding inflow flow with flapper flow.

The device shown thus makes it possible to use part of the im Beam to use existing kinetic energy, which so far in friction and thus non-usable thermal energy is converted.

The hot gases emerging from a rocket pollute the 1Tmfield the launch site and the equipment available here. The one contained in the gas jet Thermal energy is made usable in two ways if, according to claim 6, Water introduced into the deflector housing (7) and evaporated by the hot gases will.

On the one hand, the high temperature of the gases is reduced, which Environment is exposed to a lower temperature load. Also in the ltin look the thermal load on the end of the rocket will result in more favorable behavior, instead of hot gases, a gas / water vapor mixture emerges from the deflection part (7).

In the other, the thermal energy can be converted into kinetic energy of the Water vapor are implemented if, according to claim 5, the deflecting part (7) accordingly is designed. This additional mass and the resulting higher speed in the Ring beam (8 !, require an increase in the additional bell during the start phase.

In principle, several of the ring-shaped deflection parts (7) according to claim 2 and / or claim 5 are arranged one above the other in order to achieve a longer lasting Effect of the effects described to arrive.

The advantages of the invention are only at the point of a rocket launch described. Similar advantages result from an analogous arrangement for helicopter and VTOL landing sites, especially on ships.

Claims (6)

Proceed @ to suppress the induced @mfeld inflow flow at Pra @@ plate flow 1. Claims. 1. Application of a procedure for the extensive suppression of the Surrounding inflow flow of a flow directed onto a baffle surface, marked as a result, that the physically determined inflow mass corresponds to the plate diffuser-like flow area is removed and at the same time fed back to the primary flow. 2. Device for applying the method according to claim 1, characterized by central arrangement of a ring-shaped deflection part for full deflection the plate diffuser-like flow in the opposite direction. 3. Device for partial deflection of the plate diffuser-like Flow according to Claims 1 and 2, characterized by the arrangement of the deflecting part after Ansjiruch 2 at a distance from the impact surface 4. Partial drainage device the plate diffuser-like flow according to claim 1, 2 and 3, characterized by central arrangement of a segmented IT steering part. 5. Apparatus for applying a method according to claim 1 and 2, characterized by a, the primary impact surface at a distance opposite, arranged second baffle on which the outflowing ring jet impinges. 6. Application of a method according to claim 1 to 5, characterized by changing the outflowing mass flow as a result of the introduction of water in the deflector.