DE6901525U - DEVICE FOR CONNECTING THE COOLANT INLET RING TO THE WALL OF A ROCKET COMBUSTION CHAMBER OR THROTTLE NOZZLE - Google Patents

Description

Messerschmitt-Bölkow Ottobrunn, January 1, 1969

Limited liability company BP 796 Munich SXJ Ba / ja

Device for connecting the coolant inlet ring with the wall of a rocket combustion chamber or nozzle.

The innovation relates to a device for connection the one made of steel or similar high-strength material Coolant inlet ring of a rocket thruster or Rocket combustion chamber with the one made of copper or a comparable one soft material existing nozzle or combustion chamber

^Λ wall.

Rocket combustion chambers or thrusters are used in particular to enable good wall cooling with an inside the wall channel system through which a cooling liquid, usually a fuel component. ,, is conducted under very high pressure. These cavity walls are made in particular by the electroforming process

-f 2 -

Copper or similar metals suitable for this purpose. The cooling ducts are routed to the outer surface of the wall at the combustion can or thrust nozzle wall, which is in contact with the foot, in order to be fed with cooling liquid from a common annular duct. Due to the high pressures and the sometimes aggressive fuels, this ring channel * as well as the supply lines must be made of high-strength steel resistant to corrosion. This requirement gives rise to the Frobzea on which the innovation disclosed here is based:

Permanent connections between the steel belt are known and the Kupferkamaer. But because welded connections are expensive Requires pretreatments because untreated copper does not Withstands welding temperatures, soldered connections were used. The latter, however, have also largely proven to be inadequate because they have very high pressure loads or cannot withstand thermal stresses.

The object of the present innovation is to provide a device for connecting the coolant inlet ring © it to the wall a Brennkansser or thrust nozzle of a rocket engine to create that withstands the high stresses that occur, but at the same time not a major constructive one Requires effort.

In order to solve this problem, we will use the present one An innovation proposed, the Sinlsufring with an outer thrust nozzle or cd.ν of the BrennkaiisDer can be detached via ring conical surfaces associate.

in the development of the innovation, this is the conceived service

area having nozzle or. combustion chamber end as an annular flange formed with a T-shaped profile in cross-section, one end of which sits in an annular groove of the inlet ring.

According to a further feature of the innovation, a counter-retaining ring is used to press the two conical surfaces together to form a seal; which is firmly connected to the inlet ring and which is claw-like over the other end of the ring flange engages.

The main advantages of this innovation with the features described are insensitivity to thermal stresses and the possibility of producing the good sealing effect of conical sealing surfaces with large contact forces. By enclosing the ring flange on both sides by means of the ring groove or by means of the counter-retaining ring are the "Copper cone" occurring large contact pressure from the Steel parts added, so that even with plastic deformation of the copper ring flange no danger to the The connection is tight.

The contact pressure with which the counter-retaining ring don the inlet ring; presses on the ring flange, is produced according to another feature of the innovation by means of a screw connection, for this purpose, along the circumference of the inlet ring, numerous studs arranged. The arrangement of the stud bolts in the inlet ring and the screw connection with the counter-retaining ring has the advantage that the soft copper not; uniaiuteJLbar is loaded at each screw, but äaS oils counter-holding force evenly distributed over the counter-retaining ring on the copper ring flange acts so that the risk of it flowing away and a resulting leak will verraieöen.

According to the innovation, ötwa should be in the middle of the conical connection Ye: * bi «äungsk *nal aageoEdnAt be that of the ring line of the bin ring to the cooling channels of the Guide the thrust nozzle or combustion chimney wall. Through this Measure is achieved that with plastic. Deformation of the copper ring flange, especially in the edge zones or ends of the T-profile, there is no risk of closure ßung the cooling channels exists.

should «« sch £ is # s Ksif ^ ss iierkaal the new tion through the connecting channels in two axially one behind the other Sections subdivided cones of the nozzle edge or the inlet ring each in one single surface of the cone. This results in the advantages of larger fit tolerances and thus simplified Manufacturing.

An embodiment of the innovation is in the drawing shown. Show it:

Figure 1 is a longitudinal section through a Raketenschubäüse with the proposed device for connecting the coolant inlet ring with the

Nozzle wall, and

Figure 2 is a view of the device according to the arrow A in Figure 1.

The thrust nozzle wall 1 shown in Figure 1 is designed at its Mnteren end as a cross-sectionally T-shaped, conical annular flange 2, which with its one end Yes. is held in an annular groove 4 of a likewise conical inlet ring. 6 denotes the Künlmittelkanal in the inlet ring 5. A counter-retaining ring 7 is secured by means of stud bolts 8 and nuts 9 screwed into the inlet ring.

ring 5 screwed up. By means of a claw-like collar 10, the counter-retaining ring 7 engages over the other end yb of the T-shaped annular flange 2 and thus presses the conical surfaces 11a of the inlet ring f> and lib of the annular flange 2 onto one another. The Eiblnättel flowing into the ring channel 6 is fed to the nozzle wall via the bon rings 12a ″ and 12b, which are arranged approximately in the middle of the ring area 2.

From Figure 2 is the arrangement and the variety of Sebraub-Q Connections 8 * 9 between inlet ring 5 and counter age 7 to be seen.

With very strong tightening of the very dust connections 8,9 beyond the flow limit of the copper, the T-shaped annular flange 2 of the nozzle made of copper is inserted into the annular groove ^ and into the groove formed between the collar 10 and the inlet ring 5 until the copper is plastically deformed pressed, so that there is no risk of a decrease in the sealing effect "

= Sehut-s-claims -

Claims (6)

Messersehmitt-Bölkow Ottcbrunn, I ^. I.1969 Limited Liability Company BP 796 Mining SXj5 Ba / ja Claims for protection 1. Device for connecting the steel or similar High-strength material made of plastic on rings a rocket thruster or hooked combustion chamber with the made of copper or an incomparably soft material Nozzle or combustion chamber »and, characterized by g e, that the Sinlaufring (5) with the wall of the thrust box or fire chimney (1) over the ring cone näciiei » (11a, lib) is detachably connected. 2. XühlHjitteleinlauf according to claim 1, characterized in that the one conical sealing surface (! La) sfjfweiseijde nozzle or. Brennkaniinerrand is designed as an annular flange (2) egg * ia cross-section T-shaped profile, one end 0a) iß an annular groove (4) of the inlet ring (5) sits. 3. Xühlnjitteleinlaiäf according to claims 1 and 2, characterized in that a counter-retaining ring (7) is used to press the two conical surfaces (11a, lib) of the inlet ring (5) and the annular flange (2) tightly against one another, which sits on the Sinlaufving (5) is firmly connected and claw-like grips over one end (3 ^>) of the hanging flange (2) * 4. Kühlmitteleinlaiaf according to claims 1 to J> _t, characterized in that the counter-retaining ring (7) by means of many, along the circumference of the Kinlatifringes (5) arranged stud bolts (8) niifc deiri the inlet ring (5) is screwed. 5. KuhlmitteleinlauT according to claims 1 to 4, characterized daclurcii that about ± n the lütte of the cone joint (Ha, lib) channels (12a, 12b) are arranged which aufringes of a ring line (6) of ΈίτϊΙ (5) to cooling channels (10) of the thrust nozzle or combustion chamber wall (l). 6. Künlmitteleinlauf according to claims 1 to 5, characterized in that the by the connecting channels (12a, 12b) subdivided into two axially one behind the other sections of the nozzle edge conical surfaces & Φ} ssmsXlß ia one single surface of the cone.