RU2526998C2 - Method of lfre chamber geometrical axis installation and compensating closing device for its implementation - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering and can be used in gas-hydraulic lines of liquid-fuel rocket engines. In the method of liquid-fuel rocket engine chamber geometrical axis installation in rated position based on excluding influence of process tolerances during manufacturing aggregates, parts and assembling units, as well as influence of material shrinkage in joint welds of gas lines between auxiliary pump-drive assembly and chamber heads for angular deviation of chamber geometrical axes from rated position. According to invention, measurement of compensating closing device actual parameters, its manufacturing, adjustment and welding are performed at the final stage of line assembling after executing all welds of jointed aggregates, parts and assembling units. The method is implemented by gas line compensating closing device containing equalising sub with cavities at its butt ends for backing rings installation. According to invention, in the device, cavities for backing rings installation are made of length equal to length of backing rings, and above cavities, through holes are drilled where fixtures for moving backing rings to the area of parts and assembling units joint welds; cavities in fixtures for screw-driver are turned perpendicular to chamfer projection plane; fixtures are installed along perimeter at every 120°; in holes of equalising sub and fixture heads bevels are made to exclude poor penetrations in weld roots.

EFFECT: invention provides higher accuracy of its installation and lowering thrust vector losses of engine working in flight or on stand.

5 cl, 12 dwg

Description

The invention relates to rocket and space technology and can be used in gas-hydraulic lines of liquid rocket engines (LRE) to provide a given location of the geometric axes of the chambers and reduce the loss of thrust vector on the side component.

A known method of installing the geometric axis of the chambers of a liquid rocket engine (LRE) in the nominal position, based on the installation in the gas lines between the turbopump unit and the camera heads of the closing compensating devices (compensation bushings), made taking into account the installation of aggregates, parts and assembly units on clamps before performing welds at their joints with each other.

Known closure compensating device installed in the gas line of the rocket engine, for the implementation of the known method of installing the geometric axis of the rocket engine (working drawings 14D23.00-00.000GCH, 14D23.B.00-00.000SB design JSC KBHA Voronezh, see figure 1 prototype).

».The gas trunk of the liquid-propellant rocket engine with 4 chambers for the third stage of the Soyuz-2 launch vehicle is installed between the turbopump unit 1 and chamber 2 and contains pipes 3, 4, 5, 6 (see Fig. 2), a heat exchanger 7, and a flexible unit pipelines (BHT) 8 and compensating devices 9, 10. In welded joints of compensating devices with mates 4, 5, 6 and heat exchanger 7, standard washers 11, 12 (see Figs. 3 and 4) with a width of 10 mm and a temperature gap are installed h = 1.2 mm for shrinkage of the filler material after performing welds marked with the symbol "

".

Compensating devices 9 and 10 are adjusted and modified locally after installing all the components of the gas line on the engine: pipes 3, 4, 5, 6, heat exchangers 7, flexible piping units 8 on clamps 13 before welding is completed.

Welds are made after the assembly of the line and preliminary tacking by welding of the included DSE (parts, assembly units), assemblies and blocks of flexible pipelines. In this way, the assembly line provides the location of the geometric axis N of the camera 2 (see figure 1).

A disadvantage of the known method of installing the camera is its low accuracy, due to the fact that the adjustment of the closing compensating devices is carried out before the welds are included in the DSE line, which in turn leads to increased gaps in the joints and the effect of the total shrinkage of the filler material in the welds of the DSE and assemblies highway to the location of its geometric axis “N” of the camera, as a result of which the specified axis deviates from the nominal location “N” to the location “M” by an angle γ exceeding the specified The angle γ = 15 ′, which was reached by the technical task, is approximately 10′-15 ′.

Since the geometric axes of the opposing combustion chambers installed in the stabilization planes I-III (KC1 ÷ KC3), stabilization planes II-IV (see FIGS. 1 and 10) (KC2 ÷ KC4) are rejected at different angles γ ₁ , γ ₃ , γ ₂ , γ _4, respectively, then their resulting ones cause the asymmetry of the thrust vectors R _KC1 ... R _{KC4 of the} chambers, which leads to some loss of them on the side components of R _bok1 ... R _bok4 .

The objective of the proposed method for installing the geometric axis of the chambers of a liquid propellant rocket engine in a nominal position and a compensating closing device for its implementation is to eliminate the influence of technological deviations in the manufacture of assemblies, parts and assembly units, as well as material shrinkage in the welds of the joints of the gas mains between the turbopump unit and the camera heads the angular deviation of the geometric axes of the chambers from the nominal position, i.e. increasing the accuracy of its installation and reducing the loss of thrust vector operating in flight or at the engine stand.

The problem is achieved in that in the proposed method for installing the geometric axis of the combustion chamber of a liquid propellant rocket engine, including setting the chambers to their nominal position, installing closing compensating devices made taking into account the installation of units, parts and assembly units mounted on clamps according to the invention after the chambers are exposed in the slipway to the nominal position, pairwise assembly of the gas ducts of the opposing combustion chambers is carried out, while the assemblies and parts of the assembly units a power rails are installed on clamps, then sliding and spring-loaded simulators of compensating devices are installed, after grasping parts of assembly units and assemblies at the joints, the clamps are removed and welded by the joints at the joints of opposite pairs of combustion chambers located in mutually perpendicular planes, and the simulators of compensating devices are removed from the main with compression of the sliding spring, determine the geometric parameters of the compensation sleeve, obtained taking into account the shrinkage of all welds in the details of assembly units: length, eccentricity, tilt and turn angles of the connecting flanges, perform its manufacture, fitting and welding at the final stage of assembly of the mains after all welds of the joined assemblies, parts and assembly units have been completed.

The specified method is implemented by a compensating locking device for gas lines, comprising a compensation sleeve with grooves at its joints for installation of backing rings, in which according to the invention grooves for installing backing rings are made with a length equal to the length of the backing rings, and through holes are drilled above the grooves in which the clips are installed to move the washers into the weld zone of the joints of parts and assembly units; grooves in the clamps for a screwdriver are deployed perpendicular to the plane of the projection of the bevel; clamps are installed around the perimeter through angles equal to 120 °; chamfers are made in the holes of the compensation sleeve and the heads of the clamps to eliminate imperfections of the root of the welds.

The invention is illustrated by drawings.

Figure 1 presents the main view of a liquid-propellant rocket engine with afterburning of the generator gas,

Where:

1 - turbopump unit (TNA);

2 - combustion chamber (KS1 ... KS4);

"N" is the geometric axis of the chamber in the theoretical nominal position;

"M" - the geometric axis of the camera in a real deviated position from the nominal;

R _KS - thrust of the combustion chamber;

R _side - lateral component of the thrust of the combustion chamber.

Figure 2 shows a view of a gas line between THA1 and combustion chamber 2 containing compensating devices (prototype), where:

3, 4, 5, 6 - nozzles;

7 - heat exchanger;

8 - a block of flexible pipelines;

9, 10 - compensating devices;

13 - clamps.

Figure 3 shows the remote element B in the form of a section of the junction of the compensating device 9 installed between the heat exchanger 7 and the pipe 4 of the prototype,

Where:

11 - backing rings 10 mm long;

- сварной шов.

- weld.

h is the gap in the joints of the compensating devices 9, 10.

Figure 4 shows the remote element In the form of a section of the junction of the compensating device 10 installed between the nozzles 5 and 6 of the prototype,

Where:

12 - backing rings.

Figure 5 shows a view of the gas line between the TNA and the combustion chamber of the same engine shown in figure 1, but for the invention,

Where:

1, 2, 3, 4, 5, 6, 7, 8, 10 — the same elements of the gas main as in the prototype device;

14 - compensating device of the invention.

Figure 6 shows a section GG on the connection of the compensating device installed between the heat exchanger 7 and the pipe 4 of the present invention,

Where:

15 - compensation sleeve;

l ₁ - groove length of 10 mm in the compensation sleeve 15, equal to the length of the washer ring;

16, 17 - joints of the welded DSE;

d - through holes in the compensation sleeve 15;

18 - clamps.

Figure 7 presents the latch 18, the main structural elements of which are:

19 - a groove in the head for a screwdriver;

20 - bevel;

The groove 19 (see Fig. 7) in the head of the retainer 18 is made strictly perpendicular to the plane of projection of the bevel 20 onto the plane of the drawing, which is a prerequisite for determining the position of the underlay ring and the bevel of the bevel shifted into the weld zone, since after installation of the compensating device 14 joints 16, 17 of assembly units, power fittings, backing rings and bevels are invisible to the eyes of a fitter.

Fig. 8 shows a section DD on the plane in which the latches 18 are located. To prevent the rotation of the washer rings 11 in the grooves of l ₁ joints, the latches are installed in an amount of 3 pcs. evenly through 120 ° around the perimeter.

Figure 9 shows an embodiment of the heads of the clamps 18 and the holes d in the compensation sleeve 15 with grooves (chamfers) for welding so that after welding the heads of the clamps there are no lack of penetration of the root of the welds,

Where:

21 - cutting (chamfer).

Figure 10 shows a top view of the engine,

Where:

22 - gas mains.

The compensating locking device of the gas lines 22 for implementing the method of installing the geometric axis of the LRE chambers in the nominal position contains a compensation sleeve 15, shown in Fig.6, with grooves l ₁ at its joints for installing washer rings 11, drilled through the holes l ₁ through holes d, in which the clamps are installed 18. In the heads of the clamps 18 (see Fig. 7), the grooves 19 for the screwdriver are deployed perpendicular to the plane of projection of the bevel 20, and the clamps 18 themselves are installed around the perimeter evenly through 120 ° (see Fig. 8) .

In the through holes d of the compensation sleeve 15 and the heads of the latches 18, grooves 21 are made (see Fig. 9).

A method of increasing the accuracy of installation of the geometric axis of the camera in the nominal position is implemented as follows.

After setting the camera axes in the slipway in the “zero” position, i.e. nominally, pairwise assembly of the gas ducts of combustion chambers 2 is performed: KS1-KS3, KS2-KS4 (see Fig. 10), while the units and the power supply armature are installed on clamps.

Instead of compensating devices 14 (see Fig. 5), sliding and spring-loaded simulators are installed (they are not given in this description). After grabbing the DSE and aggregates, as in FIG. 2, at the joints by welding, clamps 13 are removed and the lines are welded at the joints for pairs of cameras KS1-KS3, KS2-KS4 located in mutually perpendicular planes. Simulators of compensating devices are removed from the line with compression of the sliding spring.

Using a measuring device, the geometric parameters of the compensation sleeve 15 (see Fig. 11) are determined: length L, eccentricity e, tilt angles α ₁ , α ₂ , and β turn (not shown in Fig. 11) of the connecting flanges obtained taking into account what happened shrinkage of all welds DSE.

On Fig presents the position of the washer rings 1 before moving them into the zones of the joints 16, 17 with the help of rotating latches 18.

According to the drawing of the compensation sleeve, a part is made that exactly repeats the section of the line between the joints 16 and 17 (see Fig. 11). In the grooves l _{1 of the} compensation sleeve 15 (see Figs. 11, 12), the washer rings 11 are inserted, which completely “sink” and do not protrude beyond its joints. The expansion sleeve 15 together with the washer rings 11 is installed between the joints 16 and 17 of the DCE of the highway (see Fig.6).

The compensating device operates as follows (see Fig. 12). The holes 18 are inserted into the holes d of the compensation sleeve 15, which are directed with the tip of their bevels 20 into the joint of the washer ring 11. By the force of the screwdrivers of the lockers, the clamps 18 simultaneously rotate around their axes and the washer rings 11 are moved towards the joints 16, 17 of the welded wire mesh. The rotation of the clamps 18 is 180 ° around its axis. In this position, the underlay rings are moved to the weld zones No. 1 and No. 2 (see FIG. 6), after which the latter are performed.

Thus, of the total number of welds of the line, the location of the geometric axis of the chamber is affected only by the end welds No. 1 and No. 2.

Carrying out the simultaneous execution of these seams in pairs for the gas lines of the combustion chambers KS1-KS3, KS2-KS4 (see Fig. 10), they achieve the minimum possible deviation of the geometric axes "M" of the combustion chambers from the axes "N" in the nominal location specified by the statement of work for engine development.

The proposed method and compensating device can improve the accuracy of the installation of the geometric axes of the LRE chambers, in which the gas ducts are welded, i.e. in which the working gas moves under high pressure, of the order of 200 ÷ 300 kg / cm ² , which cannot be reassembled after control tests and in which compensating bellows devices cannot be installed, because the gas lines themselves are “load-bearing” structures: TNA, thermal protection and other engine units are mounted on them.

Fulfillment of the necessary requirements of the technical specifications for the engine by the location of the geometric axes of the chambers will reduce the loss of the thrust vector on the side components and, thereby, will positively affect the flight range of the product.

Claims (5)

1. The method of installing the geometric axis of the combustion chamber of a liquid propellant rocket engine, including setting the chambers to the nominal position, installing closing compensating devices made taking into account the installation of units, parts and assembly units mounted on clamps, characterized in that after the chambers are set in the slipway to the nominal position, the gas ducts of the opposite combustion chambers are assembled in pairs, while the units and parts of the assembly units of the power fittings are mounted on clamps, then sliding and spring-loaded simulators of compensating devices are piled, after tacking the details of assembly units and assemblies at the joints, clamps are removed and welded by the lines at the joints of opposite pairs of combustion chambers located in mutually perpendicular planes, the simulators of compensating devices are removed from the main with compression of the sliding spring, geometric compensation sleeve parameters obtained taking into account the shrinkage of all welds in the details of the assembly units: length, eccentric the network, the angles of inclination and rotation of the connecting flanges, perform its manufacture, fitting and welding at the final stage of assembly of the mains after all welds of the joined assemblies, parts and assembly units have been completed. 2. Compensating locking device for gas lines for implementing the method of installing the geometric axis of the LRE chambers in the nominal position, comprising a compensation sleeve with grooves at its joints for installing the underlay rings, characterized in that the grooves for installing the underside rings are made with a length equal to the length of the underside rings, and through holes are drilled above the grooves, in which clamps are installed to move the washer rings into the weld zone of the joints of parts and assembly units. 3. The compensating device according to claim 2, characterized in that the grooves under the screwdriver are deployed perpendicular to the plane of projection of the bevel. 4. The compensating device according to claim 2, characterized in that the latches are installed around the perimeter through angles equal to 120 °. 5. The compensating device according to claim 2, characterized in that in the holes of the compensation sleeve and the heads of the clamps, grooves are made to eliminate lack of penetration of the root of the welds.

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