DE1069951B - Device for burning fuel and for directed discharge of Verforeninuriigsgase, in particular for rocket engines - Google Patents

Description

GERMAN

The invention relates to an uncooled device, in particular for rocket engines, for Burning of fuel and directed discharge of the combustion gases with a combustion chamber section, a conical outlet section for the fuel gases and one between them Nozzle section with a narrowed cross-section, which sections have a lining made of refractory, hard, have ceramic material and are arranged within a metal shell, between the Linings of the combustion chamber section and nozzle section on the one hand and the outer metal jacket on the other a ceramic intermediate layer is provided and the lining of the combustion chamber section consists of pressed material and compared to the total wall thickness in this section is only small Has wall thickness. The corrosive and erosive attacks in such devices require a hard material, and such materials have a high specific gravity and are expensive to manufacture.

Because of the indispensable resistance to corrosion and erosion, the high weight must be accepted become, which is very undesirable because in rocket propulsion and also in "jet propulsion for aircraft low weight savings are also of great importance.

The purpose of the invention is to create a combustion device, which combines the necessary resistance to corrosion with as much as possible low weight and with the least possible use of expensive lining materials. Included the invention relates to a cleaning device without cooling the nozzle, which is already more advantageous in terms of weight than one with a Cooling device and the coolant.

According to the invention, the stated purpose is thereby achieved achieved that the lining of the nozzle section consists of the pressed material, while the intermediate layer between the combustion chamber and nozzle section on the one hand and the metal jacket on the other and that part of the device bounded by the inner surface of the outlet cone and the outer metal jacket from a cast in a manner known per se, compared to the pressed lining material lighter material.

Both types of material are known per se, the invention relates to the characterized type of their Use in the structural design of the device to achieve the purpose explained above.

In order to save further weight, in that of the inner surface of the outlet cone and the outer Metal jacket limited part made of light cast ceramic material by a pore former Pores be generated.

contraption

for burning fuel
and to the directed outlet

the combustion gases,
especially for rocket engines

Applicant:

The Carborundum Company,
Niagara Falls, NY (V. St. A.)

Representative:

Dipl.-Ing. W. Cohausz, Dipl.-Ing. W. Florack

and Dipl.-Ing. K.-H. Eissei, patent attorneys,

Düsseldorf, Schumannstr. 97

Kenneth Charles Nicholson, Niagara Falls, N.Y.

(V. St. A.),
has been named as the inventor

The drawings show two exemplary embodiments.

Fig. 1 is an end view of a jet engine according to the present invention;

Figure 2 is a cross-sectional view taken on line 2-2 of Figure 1;

Fig. 3 is a cross-section through a modified embodiment;

Figure 4 is the end view of the nozzle of Figure 3;

Fig. 5 is a cross-sectional view taken along line 5-5 of FIG Fig. 4.

According to FIGS. 1 and 2, the jet engine consists of a combustion chamber 7, a cross-section of narrowed one Nozzle 8 and an outlet cone 9. The liner 11 of the combustion chamber 7 and the nozzle body 12 are made of previously pressed and fired refractory material of sufficient strength. In the vicinity of the nozzle body 12, the lining 11 expands and forms a transition to the wall narrowing in a trapezoidal shape ■ of the nozzle. This has the advantage that the nozzle body 12 is shortened and has a thicker cross-section at one end, so that the nozzle move more easily in the press can be produced as if the nozzle body converges trapezoidally towards its ends:

The nozzle body 12 is also preformed and pre-burned and consists of a hard, highly refractory material that the strong erosive attacks when Flow of hot gases at high speed

: 909 650/144

resisting through the nozzle. The outside 14 of the nozzle body runs inwardly in a trapezoidal shape to reduce the volume of the heavier pressed piece 12 and thus to reduce the weight of the nozzle. Granular silicon carbide with a boron carbide can be used as the material for the lining 11 and the nozzle body 12 and boron nitride bond or refractory oxides.

. The liner 11 and the nozzle 12 lie within a cylindrical metal jacket 15 in between is a layer 16 of a pourable and moldable refractory cement, such as. B. water-hardening calcium aluminate cement. The press cement is poured into a temporary mold or cone 10 and forms so the end part 17 within the metal jacket 15. The cone 10 is removed after 24 hours. The metal jacket 15 has a flange 18 with bolt holes 19 and is attached to the fuel injection head.

FIG. 3, in which the same parts are provided with the same reference numerals, shows a modified form of ao Jet engine, in which the refractory body 14 of the nozzle has an even smaller volume and thus smaller Has weight. The weight of the jet engine can be further reduced by the fact that the refractory cement 21, which forms the body of the outlet cone, by adding pore-forming material is made frothy. However, since such foamy cements have lower fire resistance, will expediently the cement 17 is protected on the outside by a metal jacket 22 which then forms the inner surface of the cone forms.

The ends of the cone 22 are welded to the outside of the cylindrical steel jacket 15.

4 and 5 show the outlet cone, the upper wall 23 of which has several openings 24 through which the refractory cement 21 can be poured to form the main part of the exit cone. Of the The upper part of the metal cone has an incision 26 on which the nozzle 14 rests.

40

Claims (3)

Patent claims: 1. Uncooled device, especially for rocket engines, for burning fuel and for the directed discharge of the combustion gases with a combustion chamber section, a conical outlet section for the fuel gases and one between them Nozzle section with a narrowed cross-section, which sections have a lining made of refractory, have hard, ceramic material and are arranged within a metal jacket, wherein between the linings of the combustion chamber section and nozzle section on the one hand and the outer metal jacket on the other hand, a ceramic intermediate layer is provided and the Lining of the combustion chamber section from pressed Material consists and one compared to the total wall thickness in this section only has a low wall thickness, characterized in that the lining (12) also des Nozzle section (14) consists of the pressed material, while the intermediate layer (16) between Combustion chamber and nozzle section on the one hand and metal jacket (15) on the other hand and the bounded by the inner surface of the outlet cone (9 or 22) and the outer metal jacket (15) Part (17 or 21) of the device from a cast in a known manner, in comparison the pressed lining material consists of lighter material. 2. Apparatus according to claim 1, characterized in that the from the inner surface of the Outlet cone (9 or 22) and the outer metal jacket (15) limited part (17 or 21) in in a manner known per se by including a pore former in its weight is relieved. 3. Apparatus according to claim 1 or 2, characterized in that the inner surface of the outlet cone (22) in a manner known per se by a metal jacket, for example made of stainless steel Steel, is covered. Documents considered: French Patent Nos. 966 332, 947 656; British Patent Nos. 705 847, 578 007; U.S. Patent Nos. 2,658,332, 2,487,435. 1 sheet of drawings © 909 650/144 11.59