JPS6015880B2 - Device that controls the flow of exhaust gas - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an apparatus for controlling the flow of exhaust gas, and more particularly to an apparatus for controlling the flow of exhaust gas between a plurality of rocket stations and a common exhaust gas manifold coupled thereto. .

At many military facilities, a large number of rockets are stored in storage areas or launch tubes located very close together.
These will be collectively referred to as rooms below.

Exhaust gas outlets are typically provided to direct rocket exhaust gases generated during intended or unexpected rocket ignition from storage, launch tubes, etc. to a safe location. Where available space is at a premium, for example on ships, it is now necessary to group many rooms into a common exhaust duct system. There is clearly a problem if the ducts connecting rooms to a common exhaust manifold are open at all times, i.e. normally.

Occurs when one (or more) rockets are ignited intentionally or unexpectedly.
At least a portion of the exhaust gases of 00F) flow through the common manifold into the other rooms via open coupling ducts. Rockets and rocket warheads in these other rooms will almost certainly be ignited or exploded by this hot exhaust gas. If these other rooms are open at their tops, such as launch tubes or storage rooms, exhaust gases entering the room via coupling ducts will escape through the open ends and cause costly heat damage to nearby facilities. To prevent this from happening, some type of safety door or gas valve is usually provided either at the exit closure of each rocket vault or at the coupling duct to the exhaust manifold.

When a rocket is ignited unexpectedly or as expected, the safety door or gas valve in the room in which the rocket was housed opens to direct the exhaust gases into the manifold with the blast wave normally ejected. , other room doors or valves are kept closed to prevent the inflow of exhaust gases). However, the devices available or announced to date have significant drawbacks.

For example, one prior art technique includes the installation of non-hinged ejection doors at the bottom of each compartment of multiple rocket vaults. These doors are suitable for connecting ducts to a common exhaust manifold. When one of the rockets in the vault is unexpectedly ignited (for example, by a bullet), the force exerted by the rocket exhaust gas on the top of the vault door will cause the door to open in the direction it opens. Blow it up and let the gas get into the manifold. The associated fire extinguishing system is designed to direct pressurized water through this opening to extinguish the rocket. However, the main drawback is that there is no provision for automatically re-closing the door after the rocket has been extinguished. Unless the blowout door is manually reinstalled - although there appears to be a slight device for this purpose - hot exhaust gases from the subsequent unexpected ignition of other rockets will enter this vault and cause the rocket to explode. If reignited and extinguishing is delayed, the warhead could explode. Additionally, if the upper area of the vault is not sealed, it will not appear as if the hot exhaust gases from the primary ignited rocket are already ignited in the vault housing the rocket. After that, you will be led directly to the rocket launch pad located just above the storage room. Another very important problem in the prior art mentioned above and other similar devices is that little consideration is given to preventing this exhaust gas from flowing back into the chamber when the rocket is igniting within this chamber. This is not the case.

Whatever form of exhaust flow control door or valve is used, these are such that the exhaust gases that are released and enter the exhaust manifold can be prevented from flowing around this exhaust flow back into rocket storage. It must be of suitable shape. If this backflow occurs, the gases can damage parts of the rocket's structure, ignite other propulsion systems (if the rocket has multiple stages), or cause the rocket's warhead to explode. or Ignition of these other propulsion devices or detonation of warheads ignites or detonates adjacent rockets and warheads;
It starts a disastrous chain reaction. Therefore, it is not enough to simply open and close the rocket exhaust gas flow control door correctly; in order to prevent exhaust gases from flowing back into the chamber, the door must be kept open at all times, regardless of the state of the rocket's exhaust flow. The shape must be such that it opens just enough to allow exhaust flow. In other prior art examples of storing multiple rockets, the rocket exhaust nozzles are mounted in sealing relationship on a stub, duct, or nozzle extension that leads to a common exhaust manifold.

A toggle clamp is used to hold the nose of the rocket inside the vault, creating virtually no compartmentalized rooms. At the lower end of each nozzle extension is a pair of hinged doors which are normally spring biased closed.
Exhaust gas pressure from an unexpectedly ignited rocket forces the nozzle extension door to swing open against its spring, allowing gas to flow into the manifold and away from it. Discharge. The gas pressure created within the manifold acts on the underside of the other closed doors, forcing them sealingly and preventing hot exhaust gases from flowing back into the other nozzle extensions. However, the door hinge and compression spring are located in the path of a stream of hot exhaust gases from other previously ignited rockets and are heated and corroded by this exhaust gas.

As a result of heat and corrosion damage, the door directly beneath the ignited rocket will likely not be able to return to the closed position after ignition, even if it is not burned enough to bend completely.
Also, the heat from the hot exhaust gases flowing through the manifold is likely to damage other door pressure springs. Even if these doors were held closed by pressure within the manifold during this particular ignition, the doors would eventually bend. Therefore, upon the next unexpected rocket ignition, the gas flow through the manifold will impinge on the curved door rather than closing it, forcing hot gas into the upper nozzle extension and thereby igniting this rocket. I end up.
Even if a spring-loaded flow control door is used in conjunction with the storage of small rockets, in which case there will probably be no ignition, and even if there is, the ignition time will be short, this door may be satisfactory. , are completely unsatisfactory where they are subjected to repeated or sustained rocket exhaust gas streams.

Such doors are therefore unsatisfactory for use in the storage or launch of large rockets or in conjunction with launch tubes in which large numbers of small rockets are fired. For these and other reasons, improving the control of rocket exhaust gas flow for multiple rocket stations and a common exhaust gas manifold is not desirable but necessary.

An apparatus for controlling the flow of exhaust gas according to the present invention includes a plurality of high-velocity, pressurized fluid sources and a common manifold located below the sources and having a plurality of fluid inlet ports and a common fluid outlet closure. , open the fluid source to the appropriate manifold inlet □
a coupling device coupled to the fluid source and a flow control device disposed within the coupling device for controlling fluid flow between the fluid source and the manifold.

The coupling device has a plurality of fluid transitions, each transition connecting a fluid source and a manifold, and at least a portion of the transition is typically generally vertical. The flow control device has a pair of flow control doors located in each floret. The doors, which are pivotably mounted along their mating parts for independent movement, are forced by gravity and their lower ends are moved at least from the vertical to each other when there is no fluid pressure at the appropriate fluid source or manifold inlet. It is suspended so that it is tilted slightly inward. The door pivots fully open and remains open in response to fluid pressure at the manifold inlet that is greater than the fluid pressure at the fluid source. They also pivot to various equilibrium openings in response to the moment created by the difference between the fluid source pressure acting on the fluid source side of the door and the manifold pressure acting on the manifold side of the door. In particular, the fluid source includes a small rocket storage room, launch tube, etc., and the fluid includes hot rocket exhaust gases.

The hinge portion of the door is located directly out of the flow path of the hot exhaust gases through the transition portion, and at least a portion of the door is thermally protected with an insulating or heat-absorbing material. The hinge area can also be wrapped with thermal insulation to further protect the hinge. A high-temperature seal is placed along the green section of the door to prevent gases from the manifold from flowing through the door into storage, launch tubes, etc. The door at which the rocket is ignited is rotated to open to an equilibrium position determined by the balance of moments on the interior and exterior surfaces of the door, and this equilibrium position changes with changes in exhaust gas flow.

The door and transition section are such that at each equilibrium position, the door opens just enough to allow exhaust gas to pass through, so that the exhaust gas flow passes through the door and into the room.
The shape is such that it will not flow back into the launch tube. The flow control door is preferably balanced so that it hangs fully or nearly fully closed in a static condition under the action of gravity, with the door in the closed position being approximately 30° from vertical.
Preferably at a small angle.

An elongated gas deflection device is secured to the interior surface of the manifold at an inlet entrance to the manifold.

An outwardly projecting and upwardly recessed lower deflection surface within the manifold is provided for deflecting exhaust gases to deflect exhaust gases flowing upwardly from the bottom of the manifold away from the manifold inlet closure. To achieve the desired shape of the door and transition element, the ends of the transition section are angled outwardly in the axial direction of the manifold, and the sides of the transition section are angled inwardly.

This system for controlling the flow of exhaust gases is suitable for multiple rockets where the door is repeatedly exposed to a stream of hot exhaust gases because spring pressure is not used and the hinges and door are thermally protected. It can also be used effectively for those with launch tubes, where large rockets are hemmed into multiple rocket vaults where the associated door receives a long stream of hot exhaust gases in the event of an unexpected ignition. It can also be used effectively.

Next, preferred embodiments of the present invention will be described with reference to the accompanying drawings.

Briefly speaking with reference to FIG.
, a duct for transferring the exhaust gas flow or transition duct 26 and an exhaust manifold 28, the transition duct 26 being connected to the room 20.
and the manifold 28.

Rocket 22 and chamber 20 serve as a source of high velocity pressurized fluid, particularly a rocket exhaust gas line, when the rocket engine is ignited. The chamber 20, which serves as a rocket storage, launch tube, test ignition pad, etc., may be closed or open at its top and sides. Within the chamber 20, the rocket 22 is supported in a conventional manner (not shown), and the rocket 22 need not be along the marquee line of the chamber 20 or even properly parallel. At the bottom of the chamber 20 is an outlet closure 30 that allows exhaust gases from the ignited rocket 22 to flow into the transition duct 26. A flow control device 32 is located within the transition duct 26 to control the flow of exhaust gas therethrough as described in more detail below. An inlet gateway 34 is provided from the bottom of the transition duct 26 into the top of the manifold 28.

The manifold 28 and its inlet ports 34 are located well below the chamber outlet ports 30 to allow the flow control device to be placed within the normally vertical portion of the transition duct 26. The reason will become clear soon. However, the chamber 20 need not be placed vertically above the manifold 28 as shown, but rather the chambers 20 may be arranged at a considerable angle from the vertical, and the transition ducts may have a suitably rounded section for interconnection. It's okay. The equipment described in this) is
This is an example where multiple stations 10 are coupled to a common manifold 28 and it is necessary to control rocket exhaust gases entering and exiting the manifold.

For example, in FIG. 2, three stations 10 are connected to manifold 2.
81 is shown spaced apart along the
Three or more stations can be used. Stations 10 are substantially identical and are designated (from left to right in the drawing) as stations 1, 2, and 3 for illustrative purposes. Referring again to FIG. 1, the flow control device 32 has a pair of opposing flow control doors - a first door 40 and a second door 42, both of which are substantially identical.

The door 40 is pivotally attached by a hinge 46 to an inwardly projecting first edge 48 of the transition duct 26 along its upper inner ridge 44; Along the section 50' is pivotally attached by a hinge 52 to an opposing inwardly projecting second green section 54 of the transition duct. The doors 40 and 42 are
As described in more detail below, the manifold 28 pivots closed under the influence of pressure within the manifold 28 and when the rocket 22 of the other rocket station 10 ignites, the exhaust gases flow from the manifold 28 upwardly into the chamber 20 through the transition duct 26. [Door 40 of Station 2 in Figure 2]
, 42 states].

Doors 40 and 42 are opened by the pressure of exhaust gas released when rocket 22 ignites. And that amount is only necessary to cause the exhaust stream 56 (stations 2 and 2 in FIG. 2) to flow downwardly from between the open doors. Accordingly, this exhaust flow 56 can prevent exhaust from flowing back upwardly from the manifold 28 through the door into the room 2. As shown in FIGS. 1, 2, and 4-7, doors 40 and 42 are each counterbalanced by weights 587 and 60 fixed to the upper exterior of the doors.

Weights 58 and 60 indicate that when room 20 and transition duct 26 are in a vertical position, doors 40 and 42 are fully closed (FIG. 1) or nearly so in a static or unignited state at gravity height. It is preferable that the shape is such that it hangs in a fully closed state. The substantially fully closed state means that the combined weight of the doors 40 and 42 and the weights 58 and 60 and the positions of the hinges 46 and 62
This means that the lower edges 64, 66 of 2 touch lightly and just barely close in a static condition with no exhaust gas pressure acting on either side of the door. Preferably, the doors 40 and 42 form an angle of about 30 degrees or less with the vertical when fully closed, but the doors may have a closing angle as large as 90 degrees (i.e., they are horizontal when closed). function properly. A counterweight pressing the doors 40 and 42 together in a static state is neither necessary nor desirable. The reason will become clear in the following explanation. Doors 40 and 42 are statically fully closed or do not need to be balanced to be fully closed. Experiments have shown that their operation is quite satisfactory as long as the doors 40 and 42 are configured to hang slightly inwardly toward the longitudinal vertical axis of the transition duct 26 in their static state. It is clear from For example, doors 40 and 42 will operate properly as long as they are static and suspended substantially vertically as shown in FIG. If the doors 40 and 42 are hung almost vertically in a static state like this, if the doors are hung so that they are located outside the upper inner green areas 44 and 45, the weight 5
8 and 60 are almost unnecessary. Significant advantages can nevertheless be envisaged by balancing the doors m40 and 42 so that they hang statically closed.

In many cases, especially when used on board a ship, the entire rocket station 10' is raised from a horizontal position at least occasionally (Figure 4). If doors 40 and 42 are not counterweighted and are suspended horizontally and approximately vertically (FIG. 3), one of the doors will be suspended when station 10 is slightly bent. But it tilts away from the longitudinal axis of the transition duct rather than towards it. Therefore, both doors 40, 42 will not close properly due to manifold pressure when another rocket 22 ignites, and the outwardly facing door will swing open further and the exhaust stream 56 will be forced into the manifold. 28
It becomes impossible to prevent the flow from flowing backwards into the room. When station 10 is horizontal, doors 40 and 42 (closed or nearly so) are balanced to a closed static condition.
Even when station 10 is tilted and one door is pivoted toward the open position, both doors remain aligned with the axis of the transition duct in all cases of practical tilt angle of station 10 (Figure 4). It is possible to function properly because it is maintained in a state of (but not symmetrical) (with a symmetrical state).

Operation of the door in the tilted condition is further ensured by a stop 68, which is fixed inside the transition duct 26 and prevents either the door 40 or 42 from swinging past the normal fully closed position. I have to. There are psychological benefits to balancing doors 40 and 42 statically closed even if station 10 is not tilted.

In practice, doors 40 and 42 are suspended nearly vertically open in a static condition, and although they function correctly, the pressure in the manifold closes the open suspended doors of the non-ignition stations. He seems unsure if he can do it. Therefore, if the doors 40 and 42 are balanced to close in a static state, a greater sense of security can be provided.However, by using a counterbalanced key, the doors 40 and
It is possible to prevent mechanical malfunctions that would prevent the door 42 from rotating and closing from a statically open state, and to reliably close the door. In certain conditions when rocket 22 is ignited, exhaust gas pressure forces doors 40 and 42 open to a partially open equilibrium position as shown at station 1 in FIG. 2, as detailed below. It will be done.

In other equilibrium conditions, doors 40 and 42 would have to tilt away from each other rather than vertically (second
Station 3 in the figure) is pushed to the fully open position. In order to obtain such a fully open condition, the transition duct 26 is formed in a trapezoidal shape, and the lower portions of the end walls 72 and 74 of the transition section are formed as shown in FIG.
As shown in the figure, it slopes outward from the vertical along the bag line of the manifold. Because the doors 40 and 42 can be fully opened and because the outer surfaces 76 and 78 of the doors can contact the corresponding inner surfaces 80 and 82 of the edges 72 and 74, the upper portions 90 and 92 of the edges are connected to the bell 58. It is formed outwardly so as not to interfere with 60. The green seals on the doors 40 and 42 to prevent leakage of exhaust gas are the lower edges 64 and 6 of both doors.
6 (FIG. 1) by a refractory gas seal 94 mounted along one side.

Because the walls 70 of the transition duct 26 are generally inward (see FIGS. 4 and 6 and discussed in more detail below) and the doors Z40 and 42 are not square, the edges 98 of the doors A soft or slippery heat resistant seal 96 is provided. Inner surface 100 of wall 70
The seal 96 in contact with the door 40, 42 curls or slides inwardly to form a side green seal regardless of the Z position of the door. At least the inner surface 1 of the doors 40 and 42
02 and 104 (Figure 1) are layers or coatings of thermally insulating material (
(not shown). The thickness of the insulating material is determined by the maximum exhaust gas flow rate and the total exhaust mass flow, according to well-known principles. Alternatively, at least the interior surfaces 102 and 104 of the door may be coated with a suitable heat extracting material. The hinges 46 and 52 are located on the outside of the exhaust gas flow path and further on the edge 48 of the transition duct.
and a downwardly extending flange 110,1 formed at
12 and protected from the temperature of the exhaust gas.

For example, the hinge area is illustrated with common thermal insulation (see Figure 3).
Additional thermal protection can also be provided by a cover or wrap as shown in Figure 4). Particularly when the diameter of the manifold 28 is small compared to the supersonic wavelength of the rocket displacement 56, the exhaust gases that impinge downwardly on the bottom of the manifold 28 through the manifold inlet entrance 34 will cause the gas to reverse direction and cause the manifold to Flowing upwardly along the inner wall 114 generates such high pressure that it flows back into the transition duct 26 .

An elongated longitudinal fluid diversion device 1 16 is fixed in opposed relation along both walls 114 of the manifold in the area of the inlet gateway 34 to prevent this backflow, and both ends of the fluid diversion device are connected to the inlet opening □. 34 in the marlin direction. Assuming that the inlet closure 34 is generally horizontal, the fluid converting device 116 has a lower arcuate surface 11.
8 is placed in a horizontal plane passing approximately through the center of manifold 28 (FIG. 6). A surface 118 that is concave upwardly and projects outwardly from the wall 114 diverts exhaust gas flowing upwardly along the wall and prevents the gas from flowing upwardly into the entrance 34 and along the manifold 28. It acts to flow in the direction of the wisteria line. OPERATION When the rocket 22 of either station 10 is ignited, the exhaust gas flowing into the manifold 28 pressurizes the manifold.

The resultant moment (equal to the manifold pressure multiplied by the area of the outside surfaces 76, 78 of the doors) applied to the doors 40, 42 of the other stations to close the doors would be greater if the doors were initially suspended open. If so, the doors are forced closed and held closed while the manifold pressure is slightly higher than the pressure in the chamber 20 above. Before the ignition rocket 22 begins to rise from the chamber, and during forced ignition (station 1 in FIG. 2), the doors 40 and 42 below the chamber are pivoted open by the force of the exhaust gases impinging on them. I try to do this. If the weight of weights 58 and 60 is greater than that required to just close doors 40 and 42, pressure will build up on the doors until the extra counterbalance is overcome. While the pressure builds up in this way, the exhaust gas inside the rocket 22
This extra balance must be avoided as it will damage the area and its surroundings. When the doors 40 and 42 rotate to open, the door -
on the inner surfaces 102, 104 of. The opening moment caused by the collision force of the exhaust gas is applied to the outer surfaces 76, 7 of the door.
The door normally reaches a balanced, non-open position when the closing moment caused by the manifold pressure acting on the door is just equal to the closing moment caused by the manifold pressure acting on the door. Rocket exhaust flow changes over time.
For example, in the case of a fired rocket, both impact forces and manifold pressures change over time, causing doors 40 and 42 to constantly pivot to new equilibrium positions. As the launched rocket 22 rises and exits the upper closure 120 of the chamber (station 3 in FIG. 2), the exhaust stream 56 expands and completely fills the cross section of the chamber in the lower region of the chamber.

To prevent exhaust gas flow from being inhibited in such conditions, the flow cross-section through the transition duct 26 and the manifold 28 must be at least larger than the flow cross-section of the chamber 20. Manifold 28 can be constructed to have the usual required flow cross-section given the particular chamber diameter. When the rocket 22 moves away from the closure 30,
The areas of the door inner surfaces 102, 104 with which the exhaust gas directly impinges gradually increase, eventually causing the door to rotate fully open.

Therefore, the portion of the transition duct 26 where the doors 40 and 42 are located must have a substantially uniform flow cross section (between the doors) to prevent flow restriction. During ignition, the air and gases above the doors 40, 42 at the ignition station are carried by the exhaust stream 56 and flow out, reducing the pressure within the chamber 20.
and draws outside air into the upper closure 120 of the room (station 1 in Figure 2). Particularly if the upper end of the chamber 20 is closed, a partial vacuum will be created within the chamber. A typical design with control doors 40, 42 and transition duct 26 is as follows:
The following parameters need to be considered.

namely, the ballistics of the rocket motor (including chamber pressure, flow velocity, combustion temperature, and throat diameter), the flow cross-sectional area of chamber 20, the maximum design chamber pressure for normal launch, and the manifold 28.
the flow cross-section of The flow factors are pitot pressure, shedding pressure or local ambient pressure (P^MB), static temperature, velocity, Mach number, gas constant and specific heat]. The design generally proceeds in the following manner.

The top dimensions of the doors 40, 42 and the transition duct 26 are determined by the end dimensions of the chamber 20 and/or the flow rate of the chamber. If the room has a circular cross section, a transition to square dimensions is made.
The dimensions of the lower door greens 64 and 66 are determined by the requirement that the opening that crosses the lower door greens must be completely drawn in at the exhaust pitot pressure PR, which is at least as high as the static pressure in the manifold 28. It's the size. Any particular cross section of the exhaust flow 56 (or flow region) can be described as a series of identical rings PR as shown in FIG.
R increases towards the axis of the discharge stream 56 and PR, is PR2
greater than, PR2 is greater than PR3, which in turn is greater than PR4, and PR4 is equal to P^MB. The static pressure within the manifold 28 is determined in a conventional and well known manner from the mass flow rate and static characteristics of the exhaust and from the manifold cross-sectional area.
As shown in FIG.
The inner PR of diameter 122 determined at the equilibrium opening position of 2
must be at least as large as the manifold static pressure to prevent gas in the manifold from flowing back into the chamber 20. If the intraluminal ballistics of the rocket motor change over time, the exhaust pressure area will change accordingly, and assuming the manifold cross-sectional flow area is constant, the pressure within the manifold 28 will change accordingly. do.

The initial design is based on the maximum expected rocket flow rate (and intraluminal ballistics) and is examined at lower flow rates to ensure that the manifold pressure does not exceed the exhaust pitot pressure at the new equilibrium door position. Once this is done, the dimensions of the lower greens 64, 66 of the door must then be made smaller so that a higher exhaust pitot pressure is created at the bottom opening of the door to prevent backflow. If a relatively large number of chambers 20 are provided along the manifold 28, the length of the manifold inlet closures will be approximately equal. The flow area entering manifold 28 must be at least equal to the flow area of chamber 20 during normal firing, ie, when the door swings fully open.
It is desirable that the dimensions of the lower edges 64, 66 of the door be as large as possible within the above limits. Once the top and bottom dimensions of the doors 40, 42 are determined by the aforementioned criteria, the lengths (or heights) of the doors are determined on the interior and exterior surfaces 102, 104 of each door.
and 76 and 78 are determined based on the equilibrium between the acting moments. The pressure inside the manifold 28 is
6 and 78, it is thought that a closing moment is generated, and the door inner surface 102
, 104 is opposed by the exhaust flow or non-uniform impingement pressure. Once the top and bottom dimensions of the doors 40, 42 and the pressure within the manifold 28 are determined, the balance of these moments is determined by the door area, door length, exhaust impingement angle with respect to the door interior surfaces 102, 104, and exhaust flow. 56 (which determines the recovery pressure at a particular subsonic or supersonic Mach number of the exhaust), the impact strength decreases as the door swings open from the closed position. . The final shape to balance the moments must also match the criteria used to size the door undergreens 64, 66. If this is not the case, the design must be redesigned. The angle of the transition wall 70 and the height of the transition duct 26 follow the final geometry of the doors 40,42.

Preferably, the angle between the centerline of the exhaust flow 56 and the doors 40, 42 and transition wall 70 is always less than about 30 degrees, no matter what the door balance is, thereby avoiding high heat. The associated perpendicular pressure shocks can be prevented from being applied to the door or side wall.

And the greater the angle mentioned above, the greater the possibility that some of the exhaust gas from the upper part of the transition duct 26 will flow back into the room 20. Although a particular arrangement of a rocket exhaust chamber flow control device according to the invention has been shown above for the purpose of illustrating how the invention may be advantageously used, the invention is not limited thereto. Therefore, any modifications, changes or equivalent devices made by those skilled in the art should be considered to be within the scope of the claims.

[Brief explanation of the drawing]

FIG. 1 is a vertical cross-section of the rocket exhaust flow control system showing the flow control door balanced in the fully closed position, and FIG. Cross-sectional views showing two different rocket ignition conditions; Figure 3 is a vertical cross-sectional view of the exhaust gas flow control system with the flow control door unbalanced and open and suspended in a nearly vertical position; 4 is a vertical cross-sectional view of the apparatus of FIG. 1 with all firing stations deposited and showing the effect of the flow control door, and FIG. 5 is a vertical cross-sectional view of the apparatus of FIG. A cross-sectional view shows the top of one of the flow control doors; FIG. 6 is a cross-sectional view taken along line 6--6 of FIG. 7-7 shows a fully closed state of the flow control door, and FIG. 8 shows a horizontal sectional view taken along line 8-8 of FIG. 2, showing the D pitot pressure ring of the exhaust flow. FIG. 9 is a horizontal cross-sectional view in the plane of FIG. 7 showing the flow control door partially open and in equilibrium. 10... Station, 20... Room, 22... Rocket, 26... Transition duct, 28.
...Manifold, 30...Opening, 32...
・Control device, 34...Open □, 40, 42...Door, 4
4... Edge, 46... Hinge, 48, 50...
...Midoribe, 52. ．．・．． ...Hinge, 54...
...edge, 56... discharge flow, 68, 60...
・Key, 64, 66... Lower green, 68...
Stop, 70, 72, 74... Wall, 116...
... Conversion device, 118... page. Hirokyo, de cloth, JZ team. Chi Z Yu Yu-2 Z Mantu. 6. Do you want to fight against Tsufu? ,y

Claims (1)

Claims: 1. An apparatus for controlling the flow of exhaust gas, comprising: a plurality of gas flow elements; a common manifold; and a coupling device coupling the gas flow elements to the manifold in exchange relationship; The apparatus has a plurality of transitions adapted to separately direct the flow of pressurized gas from the gas flow elements into the manifold, and a control device for controlling the flow of the pressurized gas through the transitions. and the control device 32 includes a plurality of pairs of flow control doors 40, 42 and pivotally suspends the doors 40, 42 in pairs in opposing relationship within a corresponding portion of the transition section 26. a lowering device 46, 52, each pair of doors being suspended such that they are tilted at least slightly towards each other when only gravity is acting, and pressurized gas is not associated with When flowing into the manifold through any of the transition sections 26, it is actuated to pivot to a fully closed position in response to back pressure within the associated transition section, and pressurized gas flows through the associated transition section. A device for controlling the flow of exhaust gas which is actuated to rotate through the opening necessary to prevent backflow of fluid when flowing through the manifold. 2. The device for controlling the flow of exhaust gas according to claim 1, in which the devices 46, 52 for pivotally suspending the doors 40, 42 directly direct the hot exhaust gases through the transition section 26. A device for controlling the flow of exhaust gas located outside the flow path. 3. In the device for controlling the flow of exhaust gas according to claim 2, a device 110 for protecting the device for pivotally suspending the door from the influence of the hot exhaust gas.
, 112. 4 Any one of claims 1 to 3
2. The device for controlling the flow of exhaust gas according to paragraph 1, comprising a device for protecting at least a portion of the door from the influence of the hot exhaust gas. 5. In the device for controlling the flow of exhaust gas according to claim 4, the protection device
2. A device for controlling the flow of exhaust gases having a heat-absorbing material applied in two parts. 6 Any one of claims 1 to 5
3. The apparatus for controlling the flow of exhaust gas as described in paragraph 1, wherein said gas flow element 20 comprises a rocket storage station. 7 Any one of claims 1 to 6
3. The device for controlling the flow of exhaust gas as described in paragraph 1, wherein the gas flow element 20 comprises a rocket launch tube. 8 Any one of claims 1 to 7
In the apparatus for controlling the flow of exhaust gas according to paragraph 1, in a vertical section along the longitudinal axis of the manifold 28, the transition section 26 is generally trapezoidal, the opposite ends of which connect the transition section 26 to the gas flow element. having opposing first and second walls 70 sloping outwardly in the region of attachment to 20;
Thereby, when the pair of doors 40, 42 is pivoted to a fully open position, ie, a portion of the door lies substantially along the inside of the outwardly sloping portion, the door 4
The lower part of 0.42 is a device that controls the flow of exhaust gas and is separated from the upper part. 9. A device for controlling the flow of exhaust gas as claimed in claim 8, wherein the distinct opposite sides of the lower portion of the transition section 26 having opposite third and fourth walls 70 are inwardly connected to each other. the horizontal cross-sectional area through which fluid flows through at least a portion bounded by the fully open doors 40, 42 and adjacent sides of the transition portion 26 when the doors 40, 42 are in the fully open position; A device for controlling the flow of exhaust gases so as to be substantially equal at all heights along the doors 40,42. 10. In the device for controlling the flow of exhaust gas according to claim 8 or 9, the doors 40, 42
located along the side edge 98 of the doors 40, 42 to provide a fluid seal between the side edge 98 of the door and the adjacent side of the transition section 26 regardless of the angle at which the door is rotated. A device for controlling the flow of exhaust gas with a sealing device 96. 11. The apparatus for controlling the flow of exhaust gas according to claim 10, wherein the sealing device 96 has a sealing element that is deflected inwardly toward the side of the transition section 26. device to do. 12. In the device for controlling the flow of exhaust gas according to any one of claims 1 to 11, when there is no pressurized gas on both sides of the doors 40, 42, the action length of gravity is and a counterbalance device 58, 60 for suspending the pair of doors 40, 42 in the fully closed position. 13. In the device for controlling the flow of exhaust gas according to any one of claims 1 to 12, when the doors 40, 42 are in the fully closed position, the transition portion 26 A device for controlling the flow of exhaust gases that is inclined at an angle of less than about 30° to the longitudinal axis of the associated vertical section. 14. The device for controlling the flow of exhaust gas according to any one of claims 1 to 13, wherein the exhaust gas flow is directed around the inner wall 114 of the manifold 28 toward the inlet opening 34. Opposing inner walls 114 of the manifold 28 in the region of the manifold inlet opening 34 to divert the high velocity pressurized gas flowing along the manifold 28 and cause it to flow axially along the manifold 28 and away from the opening 34. A device for controlling the flow of exhaust gases having a deflection device 116 placed axially along. 15. In the device for controlling the flow of exhaust gas according to claim 14, the deflection device 116 is attached to the inner wall 114 and has a lower surface 11 that projects radially inward.
8, said lower surface 118 having a cross-section concave generally upwardly towards said inlet opening 34. 16. In the device for controlling the flow of exhaust gas according to any one of claims 1 to 15, the transition portion 26 is arranged to stop the door at the fully closed position. a device for limiting the pivoting movement of each door of the doors, whereby said doors are caused to close symmetrically when pivoted from an open position, and whereby neither of said doors A device that controls the flow of exhaust gas without closing any further than the other side of the door. 17. A device for controlling the flow of exhaust gas according to any one of claims 13 to 16, wherein the vertical portion of the transition section is located directly above the manifold. A device that controls the flow of gas. 18
Any one of claims 1 to 17
In the apparatus for controlling the flow of exhaust gas according to paragraph 1, when the exhaust gas flows from the ignited gas flow element 22 above it through the associated transition 26, the pair of doors 40, 42: The door is configured and operative to swing partially open such that the flow pressure through the lower portion of the door is greater than the pressure within the adjacent portion of the manifold 28, thereby causing reverse flow of gas through the door. A device that controls the flow of exhaust gases.