RU2366825C1 - Liquid-propellant jet engine chamber nozzle - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention relates to missilery and can be used in production of nozzles of liquid-propellant jet engines (LPJE). Inner shell lengthwise main ribs, arranged inside cooling loop and in the zone of maximum rib spacing, feature increased thickness, their length making at least double rib spacing in the said zone. Note here that two or more radial groves are made nearby the nozzle larger edge. Note also that total area of radial groove cross section makes at least not smaller than one radial groove cross section area. Mind that aforesaid grooves are spaced apart for at least dual spacing between lengthwise ribs.

EFFECT: higher strength of both nozzle shell welded pack and that of nozzle proper.

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Description

The invention relates to rocket technology and can be used to create nozzles for liquid rocket engines (LRE).

Known nozzle of the LRE chamber containing the outer and inner shells that form the cooling path, communicating with the inlet collector, longitudinal and U-shaped ribs located inside the cooling path. Moreover, between the longitudinal and U-shaped ribs under the collector, an annular radial groove is made (patent No. 2139439, IPC F02K 9/97 - analogue).

The disadvantage of this nozzle design is the formation of U-shaped channels, the manufacture of which requires special unique equipment.

Known nozzle of the LRE chamber, containing the outer and inner shells with longitudinal main ribs, between which equally located additional ribs of shorter length, forming a cooling path, communicating through holes through a radial groove with an assembly manifold placed before the conical flange made on the nozzle exit (patent No. 2095609, IPC F02K 9/97 - prototype).

This design of the nozzle is not strong enough in the area of the radial groove, which does not improve the reliability of the nozzle as a whole without increasing its mass.

The technical task of the proposed invention is the creation of such a nozzle design, which allows to increase the strength characteristics of the soldered package of the nozzle shells and, thereby, increase the reliability of the nozzle as a whole.

This problem is solved using the nozzle of the chamber of a liquid rocket engine (LRE), including the outer and inner shells with longitudinal ribs, between which additional ribs of shorter length are equally located. Moreover, inside the cooling path in the zone of the largest pitch (C), the longitudinal main ribs of the inner shell have an increased thickness that increases the strength of the soldered package of the shells of the LRE nozzle. The width of the channels in the area of the radial groove near the large diameter of the nozzle is the largest with a constant width of the longitudinal ribs (S), therefore this zone has the smallest soldered joint strength. Additionally, this area is weakened due to the presence of a radial groove. The weakest point of the solder joint is where the widest channels meet the radial groove.

In order to increase the strength of the soldered nozzle package in the zone of large diameter, the width of the longitudinal channels is reduced by increasing the thickness of the ribs. The length of the ribs of increased thickness (L) is not less than two steps of the ribs in this zone (L≥2C), which extremely slightly increases the mass of the nozzle. The increased thickness of the longitudinal ribs (S ₁ ) and the length of the increase in thickness (L) are selected depending on the design of the nozzle. Instead of one wide groove of the chamber nozzle, instead of one wide groove (T), two or more radial grooves (K) are made with a total cross-sectional area of at least one cross-sectional area of one radial groove and at least twice the longitudinal pitch spaced apart from each other (b) ribs (b≥2C). The width of the radial grooves of the overflow is determined by calculating the hydraulic characteristics on the one hand and the permissible strength of the solder joint on the other hand (T = K + K) (Fig. 2).

The invention is illustrated by drawings.

Figure 1 shows the nozzle of the LRE chamber in section;

figure 2 - the implementation of a wide groove at a larger nozzle;

figure 3 - the implementation of two or more radial grooves;

figure 4 - internal cooling path in the area of the largest step.

The outer shell 1 is connected to the inner shell 2 along the main longitudinal ribs and additional short ribs (not shown) by soldering, thus forming a cooling path 3. Between the main longitudinal ribs and additional short ribs are two or more radial grooves 5. On the outer shell 1 is a collector 4 with a sub-collector ring (Figure 1).

The nozzle operates as follows.

The cooler is fed into the collector 4 and through the holes made in the sub-collector ring of the collector 4, is fed into the longitudinal ribs and moves in both directions. Through the channels, the cooler enters the radial grooves 5. Through the radial grooves 5, the cooler enters the channels that do not communicate with the openings of the collector ring, and returns. Thus, the entire surface of the nozzle is cooled.

The proposed design of a nozzle of a liquid propellant rocket engine increases the strength characteristics of a soldered package of nozzle shells in the weakest point - the zone of radial grooves, and also increases the strength of the nozzle design as a whole.

Claims (1)

The nozzle of the chamber of a liquid rocket engine (LRE), containing the outer and inner shells with longitudinal main ribs, between which equally located additional ribs of shorter length, forming a cooling path, communicating through holes through a radial groove with a manifold, characterized in that inside the cooling path in the zone of the greatest step of the ribs, the longitudinal main ribs of the inner shell have an increased thickness, the length of the ribs of increased thickness is at least two ribs in this zone, at m a large slice chamber nozzle perform two or more radial grooves to the total cross-sectional area not less than the cross sectional area of one of the radial grooves and spaced apart by a distance not less than twice the pitch of the longitudinal ribs.

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