DE1803937A1 - Thrust generating device with swiveling nozzle - Google Patents

Description

DR. MÜLLER-BORE DIPL.-ΙΝΘ. QRALFS 18039

DIPL.-PHYS. DR. MANITZ DIPL-CHEM. DR. DEUFEL

PATENT LAWYERS

October 16, 1968 Bol / wi - R 325

EOLLS-BOYGE LIMITED, of Moor Lane, Derby, ENGLAND

Thrust generating device with swiveling nozzle

The invention relates to a thrust-generating device with a tubular housing, on whose one end of a nozzle is pivotally mounted transversely with respect to the longitudinal axis of the housing. The invention relates in particular to a rocket motor, but it can also apply to other thrust generating motors Devices for propelling air, water or underwater vehicles are used.

The problems with the high temperatures and the pressure of the drive gases inside the housing and the nozzle in a rocket engine are connected, make the practical implementation of a very difficult swivel nozzle.

The object on which the invention is based is to create a nozzle which, during operation can be pivoted under high temperature and high pressure conditions.

A thrust generating device having a tubular housing which at one end has a having curved bearing or support surface, the

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a seat for a complementary surface on a nozzle carried by the housing forms, is characterized according to the invention in that the bearing or support surface of the housing has an opening or a channel which is provided with an external a source of pressurized sealing fluid located halfway through the housing is connected, which into the interior of the housing through the opening or the channel and between the bearing or support surface and the complementary surface in use the thrust generating device is insertable that an annular seal around the bearing or support surface between its downstream end and the opening therein or the channel located therein and that an actuating device is provided is for pivoting the nozzle in relation to the housing.

The sealing fluid can be a gas or a liquid. E.g. with a Rocket propulsion can be a gaseous or liquid propellant or a fluid be to pressurize the propellant.

The purpose of the sealing fluid passing between the bearing or support surface is inserted upstream of the annular seal is not only to prevent leakage of the Drive fluid from the interior of the housing to the bearing or support and complementary ones To prevent areas by, but also in cooling and lubricating them,

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whereby materials which were previously known can be used for the sealing. The film of the seal flow agent thus enables a practical pivoting or rotatable nozzle can be provided, for example in a rocket drive, in which the The temperature and pressure of the propellant gases are very high. Also, the film reduces the Sealing fluid means the friction between the bearing or support surface and the complementary surface, and consequently that of the actuating device required power to be delivered is less than that which would be required in the case of a similar or similar nozzle bearing that does not have a sealing Fluid is provided.

The actuating device can comprise at least one actuating device of the type of a pushing device be, which is arranged so that it pushes or pulls the nozzle, about its axis transversely to incline to the longitudinal axis of the housing. If the bearing or support surface and the complementary If the surface is partially spherical or curved, the nozzle can also extend outwards have extending abutment which can be brought into engagement with a drive part that on the circumference or tangentially in relation is movable on the surfaces to thereby rotate the nozzle about the longitudinal axis of the housing in addition to their pivoting.

An embodiment of the invention The thrust-generating device, in particular for a rocket drive, is described below

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described by way of example using the drawing! the single figure of which is a schematic axial sectional view of a thrust generating device according to the invention Establishment shows.

According to the drawing, the thrust generating Device on a tubular housing 1, which can be a rocket combustion chamber, or those with a motive fluid can be supplied by a gas generating device or compressor device. That Downstream of the housing 1 is designed as a bearing or support part 2, which has a Has concave part-spherical bearing or support surface. The latter supports the Universal swivel movement a converging-diverging one Nozzle 3, which at its upstream end has an outer circumferential surface of partially spherical Has a shape complementary to the bearing or support surface of the bearing 2. The bearing 2 has in its bearing or support surface an annular groove which an annular seal 4 such. B. an O input contains. Upstream of the seal 4 is the bearing 2 with several circumferentially spaced provided radial channels 5, each opening into opening 6 in the bearing surface and with a longitudinally extending channel 7 are in communication, the inside the wall of the housing 1 is formed. The channel 7 is at its upstream end with a Source of sealing fluid in connection, which the housing 1 alt a Pressure is supplied, which is greater than the

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Inside the housing at the upstream end of the nozzle · Palis the tubular housing 1 is a rocket combustion chamber, the Channel 7 with a propellant or fluid to pressurize the propellant are supplied. The pressurized fluid can be a gas, which is fed directly to a propellant container, or it can be a liquid, which is used to generate a pressure generating gas.

The housing 1 also carries an annular one Drive ring 8, which is mounted on ball bearings 9 and by means of the circumference in Spacing teeth 10 is rotatable about the housing. The drive ring 8 engages an arm 11 attached to the outside of the nozzle 3, thereby turning it of the binge 8 with respect to the housing 1, the nozzle 3 is rotated about the longitudinal axis of the housing 1 will. The Hing 8 also carries at least one actuator 12 of the type a shock device or a piston-cylinder device through which the inclination the axis of the nozzle 3 to the longitudinal axis of the housing 1 can be changed. Venn the Actuator is double acting is a single actuator sufficient to cause the nozzle to tilt · Palis but single-acting Control devices are provided, as shown, for example, a pair of such actuators were

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directions are required »those on the circumference of the nozzle at a distance from each other are arranged. By suitable operation of the actuating device 12 and the ring 8, the nozzle 3 can be pivoted universally are in relation to the housing 1. The fluid for actuating the actuating device or the actuating devices can be a propellant or be a fluid for pressurizing a propellant.

W During the operation of the thrust-generating device, the sealing fluid supplied through the channel 7 flows through the tree between the bearing surface and the complementary surface and forms a film therebetween, which has the following three functions:

(a) Leakage of drive fluid between the bearing surface and the complementary surface to prevent

t (b) he holds the stock and complementary

Surfaces cool and therefore the sealing ring 4 can be made of conventional sealing material be made, and

(c) the force exerted by the actuator 12 and the gear drive required to rotate the ring 8 is reduced. The latter feature enables accurate vector control to be performed.

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Another advantage of the arrangement is that between the bearing and Complementary surfaces flowing sealing fluid then into the interior The combustion chamber is pushed in at the upstream end of the nozzle where there is a boundary layer will generate inside the nozzle. The boundary layer cools the inside of the nozzle and also protects it against the combustion gases, if these contain corrosive components.

The embodiment shown is compact, since only one actuating device 12 is required is. However, instead of the ring and the arm 9 for rotating the nozzle around the Axis of the housing 1, a pair of actuators of the (type of a pushing device or piston-cylinder device that is offset by 90 degrees with respect to each other with connected to the nozzle, can be used to carry out an all-round or universal Panning.

If the sealing fluid is a propellant for a combustor Rocket propulsion, the flow will seal center of flow Is with the propulsion firing sequence is synchronized and thus it is not an additional control system for the sealing fluid necessary.

If used as a sealing fluid Gas to pressurize a propellant for a combustion chamber of a rocket

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drives are used, a relief valve in the compressed gas circuit may be unnecessary, because the flow of the compressed gas to the space between the bearing surface and the complementary surface has the function of a pressure relief or pressure reduction.

Each opening (6) can be formed by a pocket or recess in the bearing 2 or the openings can be formed by an annular or partially annular Canal passage formed in the camp 2.

Although a converging-diverging nozzle is shown, the nozzle may of course also have any other shape, e.g. it can be ring-shaped.

- patent claims -

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Claims (1)

Claim * θ 1. Thrust-generating device with a tubular housing which is attached to the one end has a curved bearing or support surface that seats a complementary surface on one formed by the nozzle carried by the housing, and actuating means for pivoting the nozzle with respect to the Housing, characterized in that the bearing or support surface of the housing (1) has an opening or a channel (6) which or which with one outside the inside of the case lying source of pressurized sealing fluid is that into the interior of the housing through the opening or the channel (6) and between the storage area and complementary area when operating the thrust-generating device can be introduced, and that an annular seal (4) extends around the bearing or support surface between its downstream ends and the opening therein. 2. Slip-generating device according to claim 1, wherein the tubular housing has a combustion chamber a rocket engine is equipped with means for supplying a gaseous or liquid propellant to the combustion chamber, characterized in that the feed device also with the opening (6) in the bearing or support surface of the housing (1) is connected, so that the 909840/0166 , Propellant aucti the sealing fluid forms. * 5. Slip-case generating device according to claim 1, in which the tubular housing is a rocket engine combustion chamber with means to accommodate one of the fuel chambers to put the propellant to be supplied under pressure, the devices for pressurizing a supply of a Having flow means in order to carry out the pressurization, characterized in that the flow medium supply also with the opening (6) is connected in the bearing or support surface of the housing (1). 4. Thrust generating device according to claim 2 or 3, wherein the tubular housing, has a concave partially spherical bearing or support surface at its downstream end and the nozzle at its upstream end has an outer peripheral surface that is partially spherical Has a shape which is complementary to the bearing or support surface, characterized in that the tubular housing (1) has a longitudinally extending channel (7) in its peripheral wall, around the sealing fluid several openings (6) in the bearing or support surface for the nozzle (3) to be supplied. 5 · Thrust generating device according to one of the η zeich.net that the actuator - preceding claims, characterized geke η η 909840/0166 •• - ¹ ' ¹ BATH ORIGINAL 11 - at least one actuator (12) of the push type or piston-cylinder type s arranged to push or pull the nozzle to incline its axis transversely to the longitudinal axis of the housing. 6. slipcase generating device according to claim 5, wherein the tubular housing a Combustion chamber of a rocket engine is characterized by that the or each actuating device is operable by an in the missile " The fluid used in the engine, e.g. as a propellant, as a fluid for pressurizing a propellant or as a sealing fluid. 809840/0166 Al. Blank page