RU2620460C1 - Set to quench rocket engine solid fuel during the test - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: device for extinguishing a rocket engine on solid fuel during the test comprises a rotatable rod-tube connected with a drive of its movement, the spray nozzles, the coolant source and the sealing screen. On sealing the screen is placed coaxially with the spray nozzle ring ejector having a nozzle ejecting the gas ejection nozzle and gas diffuser. A gas ejection nozzle is formed by the outer surface of the spray nozzle and the spray nozzles is covering the outer surface of the gas ejection nozzle. In ejecting the gas supply line installed control valve, and on the sealing screen fitted with a pressure sensor. The spray nozzle is fixed on the diffuser inside pylons, pylons and are made channels connecting the spray nozzles to supply coolant manifold mounted to the outer side of the diffuser. The cavity is connected to the collector coolant source through post-tube.

EFFECT: provision of obtaining reliable information about the state of the material and performance SRM exposed after use in high-altitude conditions aftereffect.

2 cl, 6 dwg

Description

The invention relates to the field of rocket technology, and in particular to bench equipment used in firing bench tests of solid propellant rocket engines (RDTT), and is intended to extinguish solid propellant rocket engines during surface testing, including high-altitude solid propellant rocket engines exposed to aftereffects during the period after the end work.

In the process of working out solid propellant rocket motors, it becomes necessary to assess the state of the solid part of solid propellant rocket rocket metal by defecting it after firing bench tests. Based on the results of the defect detection of the solid propellant elements (body, nozzle), the following are determined: the condition of the heat-protective coatings, the degree of entrainment, destruction and destruction of materials. However, during the period from the end of operation of the solid propellant rocket solidifier to the detection of materials, structural materials are exposed to additional influences caused by the burning out of solid fuel residues in the combustion chamber, equalization of temperature across the wall thickness, and interaction with atmospheric oxygen and pyrolysis gases. The heat released during this period causes additional coking of heat-shielding materials, thermal damage to the structural elements of force - effects of aftereffect are manifested.

The most effective means of fixing the state of the solid part of a solid propellant solid propellant rocket after an AIS is quenching, when there is a rapid cessation of combustion processes in the engine and the aftereffects are eliminated or minimized. At the same time, quenching, which consists in isolating the volume of the combustion chamber and nozzle from the surrounding atmosphere, as well as quenching by actively influencing the combustion process using refrigerants, is of great practical interest (see Experimental methods for determining the parameters of special-purpose engines. I.M. Gladkov, BC Muhammedov , E.L. Valuev, V.I. Cherepanov.- M .: STC Inform-tekhnika, 1993. P. 68).

Additional extinguishing requirements may be imposed in the case when the solid propellant rocket engine ceases operation in high-altitude conditions and is located in rarefied atmospheres for some period of time before being separated from the rocket, while the aftereffects characteristic of high-altitude conditions manifest themselves, including thermal damage to power structural elements. With the AXI of such solid propellant rocket engines, in order to obtain reliable information on the state of the material part, the cancellation must be carried out combined in two stages:

- The first stage of extinguishing is carried out by isolating the volume of the combustion chamber and the nozzle from the surrounding atmosphere with the creation of a discharge pressure for the manifestation of aftereffect effects characteristic of high-altitude conditions for a required period of time;

- The second stage of extinguishing is carried out by an active effect on the combustion process with the help of refrigerants.

Known installations for extinguishing solid propellant rocket motors during testing (see Experimental methods for determining the parameters of special-purpose engines. I. M. Gladkov, BC Muhammedov, E. L. Valuev, V. I. Cherepanov. - M .: NTC Inform-tehnika, 1993. Page 69, Fig. 28; Design and testing of solid propellant rocket engines / Edited by AM Vinnitsky. - M.: Mashinostroenie, 1980. Page 117), which contain a device for supplying refrigerant (for example, water) with a compact jet or spray.

The disadvantage of the installations is the lack of isolation of the volume of the combustion chamber and the nozzle from the environment, and at the initial moment of the beginning of the solid-fuel exhaust gas quenching, the pressure drop in the combustion chamber due to a decrease in the temperature of the combustion products outstrips the increase in pressure due to the arrival of the mass of refrigerant, as a result of which there is a leak of ambient air into the nozzle and a solid propellant combustion chamber during extinction. The combustion processes are intensified until the flame exits onto the outer surface of the nozzle block, the effects of the aftereffect increase.

The closest technical solution to the proposed one is the installation for the suppression of solid propellant rocket motors during testing (see Experimental methods for determining the parameters of special-purpose engines. I. M. Gladkov, BC Muhammedov, E. L. Valuev, V. I. Cherepanov. - M .: STC Inform Technique, 1993. p. 70). The installation includes a rotary rod-pipe associated with the drive of its movement, spray nozzles, a source of refrigerant and a sealing screen. After actuating the displacement drive, the sealing screen closes the nozzle in order to isolate the volume of the combustion chamber and the nozzle from the environment, and the refrigerant is supplied through the spray nozzles from the source of refrigerant to the combustion chamber. The sealing screen provides periodic bleeding of the vaporous refrigerant.

The known installation for extinguishing a solid-propellant rocket engine during tests at the first stage of combined extinguishing does not allow creating a rarefaction pressure in the isolated volume of the combustion chamber and nozzle when the characteristic aftereffects are manifested, including thermal damage to the structural elements. Moreover, in the volume of the combustion chamber and the nozzle, isolated from the environment, excessive pressure is created due to the burning out of the solid fuel residues and the release of pyrolysis gases.

In the second stage of combined extinguishing using liquid refrigerant (eg water) in a known installation, the refrigerant is supplied with periodic bleeding of vaporous refrigerant. Moreover, in each subsequent period, the amount of supplied refrigerant is reduced and the holding time is increased after sealing the nozzle, which complicates the quenching cycle and increases the quenching time.

It should be noted that with increased requirements for the degree of drainage of the solid propellant solid propellant after extinction, the installation does not allow for additional drainage.

The objective of the invention is to obtain reliable information about the condition of the material part and the health of the solid propellant rocket engines exposed to after-effects after work in high-altitude conditions.

The technical result consists in the fact that the reliability of the information on the state of the material part and the performance of the solid propellant rocket motor is achieved by creating in the isolated volume of the combustion chamber and nozzle a vacuum pressure corresponding to the altitude conditions at the first stage of extinguishing, and effective extinguishing with intensive evaporation of the refrigerant at the second stage of extinguishing, as well as subsequent drainage of the solid propellant rocket engine.

The technical result is achieved by the fact that in the installation for extinguishing a solid propellant rocket engine during testing, comprising a rotary rod-pipe connected with its displacement drive, a spray nozzle, a refrigerant source and a sealing screen, an annular ejector is placed on the sealing screen coaxially to the spray nozzle, containing an ejection gas nozzle, an ejected gas nozzle and a diffuser, wherein the ejected gas nozzle is formed by the outer surface of the spray nozzle and surrounding the spray tion nozzle outer surface of the nozzle ejecting the gas, and propellant gas feed line control valve is mounted, wherein the screen is mounted on the sealing pressure sensor.

The spray nozzles can be mounted on the pylons inside the diffuser, and in the pylons channels are made connecting the spray nozzle with a refrigerant supply manifold mounted on the outside of the diffuser, the collector cavity being connected to the refrigerant source through a pipe rod.

Placement on the sealing screen coaxial to the spray nozzle of the annular ejector containing the nozzle of the ejection gas, the nozzle of the ejected gas and the diffuser, while the nozzle of the ejected gas is formed by the outer surface of the spray nozzle and surrounding the spray nozzle by the outer surface of the nozzle of the ejection gas, and an ejector gas supply line is installed on the supply line moreover, a pressure sensor is installed on the sealing screen, which allows the creation of an isolated Ohm volume of the combustion chamber and the nozzle, the vacuum pressure corresponding to the altitude conditions, and at the second stage of quenching, provides effective quenching with the organization of an axisymmetric flow characterized by intense heat and mass transfer, the refrigerant is fed along the axis of the solid-propellant rocket, intensively evaporates at the vacuum pressure in the combustion chamber, and vaporous refrigerant is removed by periphery through the nozzle of the ejected gas. At the same time, the control valve installed on the ejection gas supply line sets the operation mode of the ejector, and the pressure sensor installed on the sealing screen records the vacuum pressure in the nozzle cavity, which ensures high-altitude conditions.

Thus, the creation in an isolated volume of the combustion chamber and nozzle of the vacuum pressure with the manifestation of aftereffect effects corresponding to high-altitude conditions in the first stage of extinguishing, and effective extinguishing with intensive evaporation of the refrigerant in the second stage ultimately ensure the reliability of the results of assessing the condition of the materiel and the performance of the solid propellant rocket engine, including solid propellant rocket engines ceasing to work in high-altitude conditions and before being separated from the rocket for a certain period of time, located in rarefied atmospheres, yes manifest themselves aftereffects characteristic for high altitude conditions, including structural damage to the thermal power cells.

Fastening the spray nozzle to the pylons inside the diffuser when the channels are made in the pylons connecting the spray nozzle to the refrigerant supply manifold installed on the outside of the diffuser, the collector cavity being connected to the refrigerant source through a pipe-rod, which ensures the supply of refrigerant to the spray nozzle without breaking the required geometry flowing gas part of the ejector diffuser.

It should be noted that the traction force created by the ejector further compresses the sealing screen to the plane of the nozzle and increases the contact pressure of the seal.

In addition, after quenching using liquid refrigerant (eg, water), the vacuum generated by the ejector increases the rate of evaporation of refrigerant residues from the surface of the combustion chamber construction materials that have absorbed this refrigerant, and allows for additional drying to obtain reliable information on quantitative assessment degree of entrainment, destruction and destruction of materials.

The developed set of essential features of the proposed technical solution is new and allows you to obtain the required technical result.

In FIG. Figure 1 shows a general view of an RDTT quenching installation during tests in the initial position outside the zone of a high-temperature gas jet.

In FIG. Figure 2 shows a general view of the solid-state solid-fuel exhaust damping installation in the operating position after the solid-fuel solid-fuel exhaust is closed.

In FIG. 3 shows a view A of FIG. 2. Installation of extinguishing of solid propellant solid propellant in the working position after the end of solid propellant solid propellant with quenching by the insulation of the volume of the combustion chamber and nozzle with the creation of a vacuum pressure.

In FIG. 4 shows a view A of FIG. 2. Installation of solid rocket solid fuel quenching in the working position after the solid fuel solid rocket motor is finished when quenching using refrigerant.

In FIG. 5 shows a view B of FIG. 2.

In FIG. 6 shows a cross-section BB of FIG. four.

The installation for extinguishing solid propellant rocket engines, including the combustion chamber 1 and nozzle 2, at the AXIS contains a rotary rod-pipe 3 connected to the drive of its movement 4. A sealing screen 5 is installed on the rotary rod-pipe 3. The refrigerant source 6 is connected through the rod-pipe 3, a valve 7 and a manifold 8 with a spray nozzle 9. The pressure in the solid propellant combustion chamber is controlled by a pressure sensor 10. An annular ejector 11 with an ejection gas nozzle 12 and a diffuser 13 is placed on the sealing screen 5 coaxially with the spray nozzle 13. The outer surface of the pylitelnogo nozzle 9 and covering the spray nozzles 9, the outer surface 12 of the ejection gas nozzle 14 form an ejection gas nozzle. A control valve 16 is installed on the line 15 for supplying ejection gas, and a pressure sensor 17 is installed on the sealing screen 5.

The spray nozzles 9 can be mounted in the diffuser 13 of the ejector on the pylons 18, in which the supply channels of the refrigerant from the manifold 8 to the spray nozzle 9 are made.

The operation of the blanking installation is as follows.

During the operation of the solid propellant rocket engine, the solid fuel quencher is located outside the high-temperature gas stream. Upon completion of the operation of the solid propellant rocket motor at the time of the pressure drop in the combustion chamber 1, the pressure sensor 10 up to a predetermined quenching start signal gives a signal to activate the displacement actuator 4 of the rotary rod-pipe 3. At the same time, a signal is issued to open the control valve 16 for supplying ejection gas (for example, compressed air) on the highway 15, the annular ejector 11 is turned on, the traction of which helps to reduce the turn time. At the end of the rotation, the sealing screen 5 is pressed against the plane of the end face of the nozzle 2 and isolates the volume of the nozzle 2 and the combustion chamber 1 from the environment.

At the first stage of extinguishing, the annular ejector 11 removes the products of burning of solid fuel and creates a vacuum pressure corresponding to high-altitude conditions. In this case, the degree of rarefaction is controlled by a pressure sensor 17, by the signal of which commands to the control valve 16 are generated, which sets the operation mode of the ejector 11. The traction force created by the ejector 11 additionally compresses the sealing screen 5 to the end surface of the nozzle exit 2, increasing the contact pressure of the seal. The ejection gas (for example, compressed air) flows around the pylons 18 and the spray nozzles 9 mounted on them and cools them.

In the second stage of extinguishing, a signal is received to open the valve 7 for extinguishing solid propellant solid-propellant rocket with the use of refrigerant. When valve 7 is open, refrigerant (for example, water) is supplied from the refrigerant source 6 through the rotary rod-pipe 3, the collector 8 and the channels in the pylons 18 through the spray nozzles 9 to the area of the combustion chamber 1. The vapor-gas mixture formed in the combustion chamber 1 is removed through the nozzle 2 an annular ejector 11 located coaxially relative to the spray nozzle 9. The pressure of the vapor-gas mixture is controlled by a pressure sensor 17, the signal of which generates commands to the control valve 16, which sets the operation mode of the ejector. An effective quenching scheme is implemented with the organization of an axisymmetric flow characterized by intense heat and mass transfer - the refrigerant is supplied along the solid propellant axis, and the high-heat vapor-gas mixture is removed along the periphery with a continuous cycle of the ring ejector. At the same time, the vacuum created by the annular ejector 11 contributes to a more complete evaporation of the refrigerant (for example, water) to prevent its accumulation in the lower part of the solid propellant rocket motor, which is one of the basic requirements for the solidification of solid propellant rocket engines (see Design and testing of solid propellant rocket motors. / Ed. AM Vinitsky. - M.: Mechanical Engineering, 1980. - P. 118).

In the case of increased requirements for the degree of dehumidification of the solid propellant rocket motor, the annular ejector 11 continues to operate to the required degree of dehumidification of the solid propellant rocket motor after the supply of refrigerant through the spray nozzle 9 is stopped.

Thus, the proposed installation for extinguishing a solid propellant rocket engine during testing allows isolating the volume of the combustion chamber and nozzle from the environment at the first stage of extinguishing and creating a vacuum pressure in it corresponding to high-altitude conditions, and at the second stage of extinguishing provides efficient quenching with intensive evaporation refrigerant and subsequent additional drainage. As a result, it is possible to obtain reliable information about the state of the material part and the performance of the solid propellant rocket engines, which, after completion of work in high-altitude conditions, undergo the characteristic effects of the aftereffect, including thermal damage to the structural elements.

Claims (2)

1. Installation for extinguishing a solid propellant rocket engine during testing, comprising a rotary rod-pipe associated with its displacement drive, a spray nozzle, a refrigerant source and a sealing screen, characterized in that an annular ejector containing a nozzle is placed on the sealing screen coaxially with the spray nozzle an ejection gas, an ejected gas nozzle and a diffuser, wherein the ejected gas nozzle is formed by the outer surface of the spray nozzle and surrounding the spray nozzle hydrochloric gas ejecting surface of the nozzle, and the propellant gas feed line control valve is mounted, wherein the screen is mounted on the sealing pressure sensor. 2. Installation for extinguishing a solid propellant rocket engine during the tests of claim 1, characterized in that the spray nozzle is mounted on the pylons inside the diffuser, and the channels connecting the spray nozzle to the refrigerant supply manifold mounted on the outside of the diffuser are made in the pylons, moreover the collector cavity is connected to a source of refrigerant through a rod-pipe.

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