Gas duct of liquid-propellant rocket engine with after-burning

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket-propelled vehicles, particularly, to the gas duct of liquid-propellant rocket engines with after-burning. The aforesaid gas duct comprises the outlet manifold of the main turbo-pump unit, a bent pipeline and a swinging assembly. The aforesaid bent pipeline is coupled with the outlet manifold and the said swinging assembly is linked with the engine chamber. Note here that the aforesaid swinging assembly is furnished with a bi-degree universal joint and the joint of the swinging assembly with the engine chamber and bent pipeline represents a flange coupling incorporating a metal T-shape gasket furnished with a load-bearing ring with two flexible springs provided with mountain-like ledges. Note also that the aforesaid one-piece bent pipeline is made from a heat-resistant nickel-alloy, while the bent pipeline flange represents a load-bearing belt with a developed end face surface for the engine frame support to be attached thereto. The aforesaid T-shape taper gasket springs feature the thickness varying over their length, while their length L-to-mean thickness δ ratio makes L/δ ˜8 to 10 and the angle α of the spring taper surface inclination to the flange coupling axis makes 1.5 to 2.5 degrees. The flexible spring OD including the aforesaid mountain-like ledges exceeds the ID of the flange coupling sealing surfaces by 0.1 to 0.2 mm. All parts of the gas duct are made from the EK-61 heat-resistant nickel alloy. The propose invention allows a higher tightness of the fixed joints and pipelines carrying high-temperature high-pressure oxidising medium.

EFFECT: improved performances due to ease of uncoupling gas duct from engine chamber and bent pipeline.

7 cl, 4 dwg

 

The technical field

This invention relates to the field of rocketry and, in particular, to gazivoda liquid-propellant rocket engine with afterburning.

Prior art

The basis of the present invention based on the principle of modular design LRE, according to which provides for the replacement and repair of individual elements of the engine during post-flight maintenance.

Known LRE (RD-253) with afterburning, in which the oxidizing gas after the drive of the turbine flows through gazivoda in the combustion chamber, where doregama with fuel, having passed the cooling channel. Gasovod rigidly and tightly connected to the output collector of the turbine and the inlet cone nozzle of the camera head (see Baulin V., Volodin, V.A. and others, "Design and design LRE), engineering, 1989, pp.92). RD-253 engine is disposable. The attachment of this rocket engine to the booster is carried out using a hinge, providing thrust vector control in one plane.

Famous rocket engine with afterburning (SSME), reusable, made of separate interchangeable blocks. This design facilitates replacement of individual elements of the engine without re-configuration. This engine gazivoda with welded joints pinned two core basic TNA, mixing head and the camera in General. TNA engine mounted on the mixing cylinder chamber at an angle to the longitudinal axis of the engine. This facilitates access to components of the engine during post-flight maintenance. Mount the engine to the booster by using cardan site that provides its swing to control pitch, rate and roll (see Baulin V., Volodin, V.A. and others, "Design and design LRE), engineering, 1989 s-352).

Engine mounting RD-253 and SSME to the booster through the PTO hosts swing causes a significant increase in their moment of friction under the action of axial loads due to the large friction coefficient of the sliding face of the contacting surfaces. In addition, when the swing motor, there is a considerable moment of unbalance due to the installation site swing above the center of mass of the engine, the load variation on the body swing, as leading to premature wear of the Central parts of the surfaces of host swing, and an increase in the mass of the node.

This design does not allow to replace the unit swing during post-flight maintenance.

Known two-chamber rocket engine (patent RF №2158838, IPC F02K 9/42, 10.11.2000 g) Main power element of the motor are Rama and hasbody. Every gasovod engine has isog UTY pipeline, which by welding connected to the output collector of the turbine main turbopump Assembly. The other end of this pipe is welded to the power ring bellows node swing. The bellows connection node of the swing with the camera of the engine is made of the flange. This technical solution adopted for the prototype of the invention.

In the prototype, the flange connection between the camera and bellows node swing contains massive flanges and dvuhseriynoy metal gasket with spring axial compression. This connection has a significant diametral and axial dimensions, which increases the mass characteristics of the engine.

In addition, the prototype of the curved pipe is made double-walled channels regenerative cooling. This complicates and increases the cost of manufacturing a bent pipe.

Disclosure of inventions

The present invention is the creation of gazivoda, having in its composition a host of swing that can be easily undocked from the camera and bent the pipeline.

The problem is solved due to the fact that gazivode liquid-propellant rocket engine with afterburning, which includes the output collector of the turbine main turbopump Assembly, curved pipe, and a host of swing, while the curved pipe is connected with the output of collector the turbine, and the node swing with camera motor, and the connection node of the swing with the engine chamber and a curved line made in the form of a flange connection in which a metal strip having a cross section is T-shaped and which includes a power ring with two elastic springs having a sealing ledges toroidal shape, and a curved line made of metal heat-resistant Nickel alloy, and a flange bent pipe made in the form of power belts with advanced frontal surface for mounting supports of the frame of the engine. Other distinctions of the invention are:

- spring sealing gasket is made conical and are variable in their length, the thickness, the ratio of length L to an average thickness δ is L/δ ˜8-10, with angle α the slope of the conical surface of the leaf springs to the axle flange is 1.5-2.5 degrees;

- outer diameter of the elastic springs, including toroidal protrusions, larger than the inner diameter of the sealing surfaces of flange connections 0.1-0.2 mm;

as host of swing applied bellows node swing;

as host of swing used spherical movable sealing connection;

curved pipe made of heat resisting celevoke alloy grades EC;

the flanges that connect a node swing with a camera and a curved pipe, and a metal gasket in these compounds are made of heat-resistant Nickel alloy grades EC.

The technical result from the use of the invention is that during post-flight maintenance of the engine can inspect and repair site swing and his replacement.

Brief description of drawings

Figure 1 shows gasovod in section; figure 2 and 3 shows the parts of a zoomed section of flange connections node swing with curved pipe (fragment I) and the engine compartment (fragment 2); figure 4 presents an enlarged cross section of the metal strip.

An example implementation of the invention

Gasovod 1 (figure 1) includes output collector 2 turbine main turbopump Assembly and the curved pipe 3. Between the chamber 4 of the engine and a curved pipe 3 has a bellows node swing 5. Site swing 5 is equipped with two-stage shaft 6, which allows to reject chamber of the engine within an angular cone with angle polarstar 8°by controlling the thrust vector through the channels of "pitch" and "yaw". The connection of the curved pipe 3 to the collector of the turbine 2 main turbopump Assembly made using weld 7. Connected to the e (2, fragment 1) bellows node swing with curved pipeline consists of a flange 8, a metal strip 9 having a cross-section of T-shape, and the flange 10. The flanges 8 and 10 are connected via pins 11 and nuts 12. Metal strip 9 (figure 4) includes the power ring 13 and two elastic springs 14 and 15 with the sealing protrusions 16 toroidal shape. Springs 14 and 15 are made conical and are variable in their length thickness. The ratio of the length L of the springs to their average thickness δ is L/δ ˜8-10. Angle α the slope of the conical surface of the leaf springs to the axis Of1-On1the flange is 1.5-2.5 degrees. This embodiment of springs can improve their flexible properties.

The flange 8 (2) performed the sealing surface 17 has a cylindrical shape and a circular groove 18 under power ring 13 metal strip 9. The end 19 of the power of the ring 13 is in contact with the end surface 20 of the annular groove 18. The flange 10 has a sealing surface 21 of cylindrical shape which is coaxial with the cylindrical sealing surface 17 of the flange 8.

Outer diameter D1(figure 4) elastic springs 14 and 15, including toroidal protrusions 16 larger than the inner diameter D2(3) sealing the cylindrical surface 17 on the value ˜0.1 to 0.2 mm, in case of ustanovke.dalshe strip 9 in the flange connection 8 to create a preliminary contact pressure on the torus sealing protrusions 16 of these springs.

The flange 8 of the curved pipe 3 made in the form of a power belt 22 with developed end surface 23 for fastening it supports the motor frame (not shown).

Flange connection (figure 3, fragment 2) consists of the flanges 24, 25 and the metal strip 26. The flanges 24 and 25 are connected by pins 27 and nuts 28. The metal strip 26 of this flange is no different from a metal strip 9, is shown in figure 4.

The flanges 8, 10, 24 and 25, and the metal strip 9 and 26 are made of heat-resistant Nickel alloy, alloy grades EC.

It should be noted that, as the host of the swing, you can use the spherical movable sealing the connection.

To ensure operability at high pressures (up to 25 MPa) and high temperatures (up to 600° (C) in the presence of oxygen-containing environment curved line made of metal heat-resistant Nickel alloy grades EC-61. This allows to simplify the design of gazivoda and reduce its cost.

The operation of the device

First on the flange 8 is installed metal strip 9. This power ring 13 is moved along the cylindrical surface 17 up until the end 19 will rest against the end face 20 of the ring groove 18. However due to the fact that the external diameter D1elastic springs 14 pain what s inside diameter D 2the sealing surface 17 there is an increase in the contact pressure on the sealing toroidal ledge 16 of the elastic spring 14. Then an elastic spring 15 is mounted to the flange 10. While the flange 10 will move along the axis of the flanged connections up until the end surface of the flange 10 abuts the other end of the power ring 13. This is followed by tightening device pins 11 and nuts 12.

Thus, when assembling the specified flange is radial elastic compression springs 14 and 15.

Assembly flange, shown in fragment 2, no different from the Assembly flange, shown in fragment 1.

When the supply pressure of the sealing medium contact pressure on the sealing torus ledges 16 of the elastic leaf springs 14 and 15 increases. Maintaining the desired value of the contact pressure on the sealing surfaces during operation of the device is provided by a radial preload of the elastic springs from the action of internal pressure, and the longer the spring, the higher comopletely effect, i.e. higher sealing ability.

Thus, through the use in the above-described construction of the metal strip with elastic springs radial compression is made possible opensiteadmin flange dimensions, that has allowed to reduce the weight of gazivoda. In addition, the detachable connection of the swing with the engine chamber and a curved pipeline allows you to replace the unit swing during post-flight maintenance.

Industrial application

The invention is intended for sealing immovable joints and arteries, through which is transported by a high-temperature oxidizing environment of high pressure. This device is more appropriate to use when designing gazovozov liquid-propellant rocket engine with afterburning.

1. Gasovod liquid-propellant rocket engine with afterburning, including the collector outlet of the turbine main turbopump Assembly, curved pipe and node swing with two-stage shaft, while the curved pipe is connected to the collector output of the turbine, and the node swing - chamber of the engine, characterized in that the connection node of the swing with the engine chamber and a curved line made in the form of a flange connection in which a metal strip having a cross section is T-shaped and which includes a power ring with two elastic springs having a sealing ledges veroobrazno shape, and a curved line made from heat-resistant Nickel-metal alloy, and a flange bent pipe is the wires made in the form of power belts with advanced frontal surface for mounting supports of the frame of the engine.

2. Gasovod according to claim 1, characterized in that the spring sealing gasket is made conical and are variable in their length, the thickness, the ratio of length L to an average thickness δ is L/δ ˜8-10, with angle α the slope of the conical surface of the leaf springs to the axle flange is 1.5-2.5°.

3. Gasovod according to claim 1, characterized in that the outer diameter of the elastic springs, including gorbalenya ledges, larger than the inner diameter of the sealing surfaces of flange connections 0.1-0.2 mm

4. Gasovod according to claim 1, characterized in that the host swing applied bellows node swing.

5. Gasovod according to claim 1, characterized in that the host swing used spherical movable sealing the connection.

6. Gasovod according to claim 1, characterized in that the curved pipe made of heat-resistant Nickel alloy grades EC.

7. Gasovod according to claim 1, characterized in that the flanges that connect a node swing with a camera and a curved pipe, and a metal gasket in these compounds are made of heat-resistant Nickel alloy grades EC.



 

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