CN218523054U - Index type regulating valve suitable for aerospace engine - Google Patents
Index type regulating valve suitable for aerospace engine Download PDFInfo
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- CN218523054U CN218523054U CN202220754493.8U CN202220754493U CN218523054U CN 218523054 U CN218523054 U CN 218523054U CN 202220754493 U CN202220754493 U CN 202220754493U CN 218523054 U CN218523054 U CN 218523054U
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Abstract
The utility model discloses an index type governing valve suitable for aerospace engine, include: the high-temperature section shell is provided with an L-shaped hollow cavity I; the low-temperature Duan Keti is detachably connected to one side of the high-temperature section shell, which is opposite to the outlet, and a hollow cavity II which is arranged along the axis direction is formed in the low-temperature section shell; the cooling chamber is positioned at the adjacent position of the low-temperature section shell and the high-temperature section shell; the index valve core is a revolving body which penetrates through the hollow chamber I and the hollow chamber II; and the displacement driving device is positioned in the hollow chamber II, is connected with the tail end of the index valve core, is used for driving the index valve core to reciprocate along the axis direction of the index valve core, and controls whether the inlet is communicated with the outlet or not by determining whether a gap is formed between the outer wall of the front end of the index valve core and the inner wall of the convergence section. The high-temperature fuel regulator can meet the requirement for regulating the flow of the engine, and has the flow metering range and the metering effect, so that the regulator has practical use value.
Description
Technical Field
The utility model belongs to the technical field of aerospace engine fuel and other medium measurement are adjusted, concretely relates to index type governing valve suitable for aerospace engine.
Background
The flight mach number of the aerospace craft is continuously increased, the flight environment of the aerospace craft is more and more severe, and higher requirements are put forward to the problem of active cooling of the craft. The active circulation regeneration cooling is used as a cooling system of the engine and provides possibility for adapting to worse working environment of various engines, the engine coolant of the active circulation regeneration cooling technology is generally fuel of the engine, and the fuel in the engine is in a supercritical state under ultrahigh pressure and ultrahigh heat flow. Experimental research on supersonic combustion shows that under the same inflow conditions and equivalence ratio, the combustion efficiency of the supercritical kerosene is improved by 10% -15% compared with that of liquid kerosene, and the combustion intensity and the combustion efficiency of the supercritical fuel can be remarkably improved.
The traditional regulator requires the adjustable venturi to have higher linearity due to the driving mode and the overall control requirement of the engine. According to the characteristics of aviation kerosene, when the temperature reaches 737 ℃ along with the rise of the medium temperature, the density of the high-temperature fuel regulator is only 1/20 of that of the normal-temperature state under the fixed pressure, so that the weight of the high-temperature fuel regulator increases in an exponential level along with the increase of the metering flow, and the high-flow high-temperature fuel regulator has no actual installed value.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an index type governing valve suitable for aerospace engine provides one kind and can satisfy the engine flow control demand, compromises the high temperature fuel regulator of flow measurement scope and measurement effect, ensures that the regulator has the in-service use and worth.
The utility model adopts the following technical scheme: an exponential type regulator valve suitable for use in an aerospace engine, comprising:
the high-temperature section shell is provided with an L-shaped hollow chamber I, one end of the hollow chamber I is an inlet of a high-temperature medium, the other end of the hollow chamber I is an outlet of the high-temperature medium, and the inner wall of the outlet is provided with a convergence section;
the low-temperature Duan Keti is detachably connected to one side of the high-temperature section shell, which is opposite to the outlet, and a hollow chamber II which is arranged along the axial direction of the hollow chamber II is arranged in the low-temperature section shell;
the cooling chamber is positioned at the adjacent position of the low-temperature section shell and the high-temperature section shell, is an independent space which is not communicated with the hollow cavity I and the hollow cavity II, and is internally used for circulating cooling liquid;
the index valve core is a revolving body which penetrates through the hollow chamber I and the hollow chamber II, and the generatrix of the index valve core is an index curve;
and the displacement driving device is positioned in the hollow chamber II, is connected with the tail end of the index valve core, is used for driving the index valve core to reciprocate along the axis direction of the index valve core, and controls whether the inlet is communicated with the outlet or not by determining whether a gap is formed between the outer wall of the front end of the index valve core and the inner wall of the convergence section.
Further, the displacement drive device includes:
the piston sleeve is of a sleeve structure fixedly arranged in the low-temperature section shell and the cooling chamber and is coaxially arranged with the index valve core;
the two sensing plates are arranged at the tail end of the index valve core in parallel at intervals; each sensing plate is perpendicular to the axis of the index valve core, and the two sensing plates are used for dividing the internal space of the piston sleeve into three parts; a cooling cavity is arranged between the two sensing plates, and a control oil accommodating cavity is formed at the outer sides of the two sensing plates respectively;
the electro-hydraulic conversion device is arranged on one side of the low-temperature section shell, and two control oil way pipelines are arranged in the electro-hydraulic conversion device and are respectively communicated with the two control oil containing cavities; and the electro-hydraulic conversion device is used for controlling the reciprocating movement position of the index valve core by regulating and controlling the delivery quantity of the control oil in the two control oil way pipelines to the two control oil containing cavities.
Furthermore, a displacement sensor is arranged on the low-temperature section shell and comprises a fixed end and a movable end, the fixed end is fixed on one side, away from the high-temperature section shell, of the low-temperature section shell, and the movable end is coaxially connected to the index valve core.
Further, the method comprises the following steps:
the drainage screw is coaxially arranged in the index valve core, one end of the drainage screw is connected with the moving end of the displacement sensor, and the other end of the drainage screw extends to the front end of the index valve core;
the drainage screw is internally provided with a channel A which is arranged along the axis of the drainage screw, a channel B is arranged between the outer wall of the drainage screw and the inner wall of the index valve core, and the cooling cavity is communicated to the cooling chamber through the channel A and the channel B in sequence and is used for injecting cooling liquid into the cooling chamber from the cooling cavity.
The utility model has the advantages that: the utility model uses the index type adjusting cone valve, which has high precision requirement and small volume when in small flow, short stroke when in large flow state, high speed and capability of well meeting the large flow lightweight requirement; the precision can be enhanced in small flow, and the product weight can be reduced in large flow. In order to meet the characteristics of wide metering range and high precision requirement in small flow of a high-temperature regulator, a regulating cone valve which is designed to have nonlinear flow characteristics and meet the fuel requirement of an engine is designed by combining the working principle of a product.
Drawings
Fig. 1 is a schematic structural view of an index type regulating valve for an aerospace engine according to the present invention;
fig. 2 is a schematic diagram showing the control oil flow path and the coolant flow path in the index type regulating valve of the aerospace engine according to the present invention.
Wherein, 1, a high-temperature section shell; 2. a low temperature section housing; 3. a cooling chamber; 4. an inlet; 5. an outlet; 6. an inlet of the fuel tank; 7. a displacement sensor, 8, a convergence section, 9, a control oil pipeline and 12, a drainage screw; 13. a piston sleeve; 14. index valve core, 15 sense plates, 16 cooling cavities, 17 control oil containing cavities, 18 channels A and 20 channels B.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
The utility model provides an index type governing valve suitable for aerospace engine, as shown in fig. 1, including high temperature section casing 1, low temperature section casing 2, cooling chamber 3, index case 14 and displacement drive arrangement. The high-temperature section shell 1 and the low-temperature section shell 2 can be sequentially arranged along the vertical direction or the horizontal direction, and the arrangement, the relative position relation and the whole use function of other related structures are not influenced no matter what direction. Now in order to set gradually high temperature section casing 1 and low temperature section casing 2 along the horizontal direction as the example, introduce in detail the utility model discloses.
The high-temperature section shell 1 is provided with an L-shaped hollow cavity I, a port of the hollow cavity I in the vertical direction is an inlet 4 of a high-temperature medium, and a port of the hollow cavity I in the horizontal direction is an outlet 5 of the high-temperature medium. The high temperature medium may be RP-3 aviation kerosene of aviation flight fuel. The inner wall at the outlet 5 has a convergent section 8, and the shape of the inner wall of the convergent section 8 is designed to match the shape of the index valve core 14. The shape of the inner wall at the outlet 5 is designed to be similar to the inner structure of the venturi. For example, the inner wall of the convergent section 8 may be inclined toward the axial center to form a step which is to cooperate with the non-linear profile of the index valve spool 14 to provide communication or isolation between the inlet 4 and the outlet 5.
The low temperature section shell 2 is detachably connected to the high temperature section shell 1, and is arranged on one side opposite to the outlet 5, and a hollow chamber II arranged along the axial direction of the low temperature section shell is arranged in the low temperature section shell. The two sides of the high-temperature section shell 1 along the horizontal direction are respectively a low-temperature section shell 2 and an outlet 5 of a high-temperature medium.
The cooling chamber 3 is located at the adjacent position of the low-temperature section shell 2 and the high-temperature section shell 1, is an independent space which is not communicated with the hollow cavity I and the hollow cavity II, and is internally used for circulating cooling liquid.
The index valve core 14 is a revolving body which penetrates through the hollow chamber I and the hollow chamber II, the front end of the index valve core is a revolving body formed by the rotation of an index type bus, and different flow curves can be designed according to requirements. The outer wall of the end face of the index valve core 14 is matched with the shape design of the convergent section 8, so that the communication or the partition of the inlet 4 and the outlet 5 is controlled by mutual distance and approach and contact.
And the displacement driving device is positioned in the hollow chamber II, is connected with the tail end of the index valve core 14, and is used for driving the index valve core 14 to reciprocate along the axial direction of the index valve core and controlling whether the inlet 4 is communicated with the outlet 5 or not by determining whether a gap is formed between the end surface step of the index valve core 14 and the inner wall of the convergence section 8 of the outlet 5.
The displacement driving device is used for realizing the switching of the following two states:
in the first state, a gap is formed between the outer wall of the index valve core 14 and the inner wall of the convergence section of the outlet 5, so that the inlet 4 is communicated with the outlet 5, and a high-temperature medium passes through the gap;
in the second state, the outer wall of the index valve core 14 is contacted with the inner wall of the convergent section of the outlet 5, so that the inlet 4 is not communicated with the outlet 5, and high-temperature media are prevented from passing through.
In some embodiments, the displacement driving means comprises a piston sleeve 13, which is a sleeve structure fixedly installed in the low temperature section housing 2 and the cooling chamber 3, and is coaxially disposed with the index valve core 14. The two sensing plates 15 are arranged at the tail end of the index valve core 14 in parallel at intervals; each sense plate 15 is perpendicular to the axis of the index spool 14, and the outer dimensions of each sense plate 15 are the same as the inner dimensions of the piston sleeve 13. The two sensing plates 15 are used for dividing the internal space of the piston sleeve 13 into three parts; a cooling cavity 16 is formed between the two sensing plates 15, and a control oil accommodating cavity 17 is formed outside each of the two sensing plates 15.
The device also comprises an electro-hydraulic conversion device, wherein the electro-hydraulic conversion device is arranged on one side of the low-temperature section shell 2, two control oil way pipelines 9 are arranged in the electro-hydraulic conversion device, and the two control oil way pipelines 9 are respectively communicated to the two control oil containing cavities 17; and the electro-hydraulic conversion device is used for controlling the reciprocating movement position of the index valve core 14 by regulating and controlling the delivery amount of the control oil in the two control oil way pipelines 9 to the two control oil containing cavities 17. The electro-hydraulic conversion device 9 controls the two sensing plates 15 to horizontally reciprocate simultaneously by regulating and controlling the oil output of the control oil in the two control oil pipelines 91, so as to control the driving piston 11 to horizontally reciprocate.
In some embodiments, a displacement sensor 7 is disposed on the low temperature section casing 2, and the displacement sensor 7 includes a fixed end and a movable end, the fixed end is fixed on a side of the low temperature section casing 2 away from the high temperature section casing 1, and the movable end is coaxially connected to the index valve core 14. The displacement sensor is used for transmitting the position of the index valve core 14 to the controller, and then the position of the index valve core 14 is subjected to closed-loop control.
In some embodiments, the index valve core 14 is hollow, a drainage screw 12 is coaxially disposed inside the index valve core 14, one end of the drainage screw 12 is connected to the moving end of the displacement sensor 7, and the other end of the drainage screw 12 extends to the front end of the index valve core 14. The low-temperature section shell 2 is provided with an oil tank inlet 6, the drainage screw 12 is internally provided with a channel A18 arranged along the axis of the drainage screw, and a channel B20 is arranged between the outer wall of the drainage screw 12 and the inner wall of the index valve core 14. The cooling cavity 16 is communicated with the cooling chamber 3 through a channel A18 and a channel B20 in sequence, and is used for injecting cooling liquid into the cooling chamber 3 from the cooling cavity 16. The cooling chamber 16 communicates with a tank inlet 6, and the cooling chamber 3 can be filled with the cooling liquid from the tank inlet 6. The tank inlet 6 may be provided with a control solenoid valve to close the cooling fuel when cooling is not required.
As shown in fig. 2, the utility model is suitable for an operating method of the exponential type governing valve of aerospace engine does:
1. the conveying amount of the control oil in the two control oil way pipelines 9 to the two control oil containing cavities 17 is regulated and controlled through an electro-hydraulic conversion device, so that the reciprocating movement position of the index valve core 14 is controlled. When the index valve core 14 moves towards the direction far away from the outlet 5, a gap is formed between the end surface step of the index valve core 14 and the inner wall of the convergence section of the outlet 5, so that the inlet 4 is communicated with the outlet 5, and high-temperature medium passes through the gap. When the index valve core 14 moves towards the direction close to the outlet 5, the end surface step of the index valve core 14 is contacted with the inner wall of the convergent section of the outlet 5, so that the inlet 4 is not communicated with the outlet 5, and the high-temperature medium is prevented from passing through.
2. The cooling fluid is injected from the tank inlet 6 and passes through the cooling chamber 16, the channel a18 and the channel B20 in that order to the cooling chamber 3 and finally back to the tank. The cooling liquid is injected into the cooling chamber 3, so that the cooling of parts and the high-temperature section shell 1 in the whole device can be realized.
In a metering adjustment mechanism of an engine, a common valve is a linear valve core, the linear valve core is a rotary body with a straight line as a generatrix, and for example, the front end of a valve body is conical. According to the prior art, the taper angle theta of the cone valve ranges from 20 degrees to 30 degrees, under the condition that other conditions are not changed, a smaller taper angle has a longer stroke, a larger throat area and a higher resolution, and vice versa, and the proper taper angle theta of the cone valve can be selected according to the requirement of an engine in the actual design process.
According to the characteristics of aviation kerosene, when the temperature reaches 737 ℃ along with the rise of the medium temperature, the density of the high-temperature fuel regulator is only 1/20 of that of the normal-temperature state under the fixed pressure, so that if the large-flow light-weight engineering design is not carried out, the weight of the high-temperature fuel regulator increases exponentially along with the increase of the metering flow, and the large-flow high-temperature fuel regulator has no actual installed value.
According to the working principle of the engine, the fuel flow demand is small and the precision requirement is high in the ignition state of the engine; the requirement on the flow is higher when the thrust is high, and the precision requirement can be properly reduced. In order to meet the design requirements of wide metering range and light weight, according to the Venturi metering principle, under the condition that the inlet pressure is constant, the metering flow rate is only related to the area, the Venturi metering area formula is exponentially increased, and the valve metering flow rate is also exponentially increased. Therefore, the adjusting cone valve designed by the utility model uses the index valve core, the index type adjusting cone valve has high precision requirement and small volume when in small flow, the stroke of changing into a large flow state is short, the speed is high, and the large flow lightweight requirement can be well met; the precision can be enhanced in small flow, and the product weight can be reduced in large flow.
Claims (4)
1. An exponential type governing valve suitable for aerospace engine, its characterized in that includes:
the high-temperature section shell (1) is provided with an L-shaped hollow chamber I, one end of the hollow chamber I is an inlet (4) of a high-temperature medium, the other end of the hollow chamber I is an outlet (5) of the high-temperature medium, and the inner wall of the outlet (5) is provided with a convergent section (8);
the low-temperature Duan Keti (2) is detachably connected to one side of the high-temperature section shell (1) opposite to the outlet (5), and a hollow chamber II arranged along the axial direction of the low-temperature section shell is formed in the low-temperature section shell;
the cooling chamber (3) is positioned at the adjacent position of the low-temperature section shell (2) and the high-temperature section shell (1), is an independent space which is not communicated with the hollow cavity I and the hollow cavity II, and is internally used for circulating cooling liquid;
the index valve core (14) is a rotary body which penetrates through the hollow chamber I and the hollow chamber II, and the generatrix of the index valve core is an exponential curve;
and the displacement driving device is positioned in the hollow chamber II, is connected with the tail end of the index valve core (14), and is used for driving the index valve core (14) to reciprocate along the axial direction of the index valve core, and controlling whether the inlet (4) is communicated with the outlet (5) or not by determining whether a gap is formed between the outer wall of the front end of the index valve core (14) and the inner wall of the convergence section (8).
2. An exponential-type modulation valve suitable for use in an aerospace engine according to claim 1, wherein the displacement drive means comprises:
the piston sleeve (13) is of a sleeve structure fixedly arranged in the low-temperature section shell (2) and the cooling chamber (3) and is coaxially arranged with the index valve core (14);
the two sensing plates (15) are arranged at the tail end of the index valve core (14) in parallel at intervals; each sensing plate (15) is perpendicular to the axis of the index valve core (14), and the two sensing plates (15) are used for dividing the inner space of the piston sleeve (13) into three parts; a cooling cavity (16) is arranged between the two sensing plates (15), and the outer sides of the two sensing plates (15) form a control oil accommodating cavity (17) respectively;
the electro-hydraulic conversion device is arranged on one side of the low-temperature section shell (2), two control oil way pipelines (9) are arranged in the electro-hydraulic conversion device, and the two control oil way pipelines (9) are respectively communicated with two control oil containing cavities (17); the electro-hydraulic conversion device is used for controlling the reciprocating movement position of the index valve core (14) by regulating and controlling the delivery amount of control oil in the two control oil way pipelines (9) to the two control oil containing cavities (17).
3. The exponential type modulation valve for an aerospace engine according to claim 2, wherein a displacement sensor (7) is disposed on the low temperature section casing (2), and the displacement sensor (7) comprises a fixed end and a movable end, the fixed end is fixed on the side of the low temperature section casing (2) far away from the high temperature section casing (1), and the movable end is coaxially connected to the exponential valve core (14).
4. An exponential-type modulation valve suitable for use in an aerospace engine according to claim 3, comprising:
the drainage screw (12) is coaxially arranged inside the index valve core (14), one end of the drainage screw is connected with the moving end of the displacement sensor (7), and the other end of the drainage screw extends to the front end of the index valve core (14);
the guide screw (12) is internally provided with a channel A (18) arranged along the axis of the guide screw, a channel B (20) is arranged between the outer wall of the guide screw (12) and the inner wall of the index valve core (14), and the cooling cavity (16) is communicated to the cooling chamber (3) through the channel A (18) and the channel B (20) in sequence and is used for injecting cooling liquid into the cooling chamber (3) from the cooling cavity (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220754493.8U CN218523054U (en) | 2022-03-31 | 2022-03-31 | Index type regulating valve suitable for aerospace engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220754493.8U CN218523054U (en) | 2022-03-31 | 2022-03-31 | Index type regulating valve suitable for aerospace engine |
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| CN218523054U true CN218523054U (en) | 2023-02-24 |
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| CN202220754493.8U Active CN218523054U (en) | 2022-03-31 | 2022-03-31 | Index type regulating valve suitable for aerospace engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114719023A (en) * | 2022-03-31 | 2022-07-08 | 陕西空天动力研究院有限公司 | High-temperature adjusting stop valve suitable for aerospace engine |
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2022
- 2022-03-31 CN CN202220754493.8U patent/CN218523054U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114719023A (en) * | 2022-03-31 | 2022-07-08 | 陕西空天动力研究院有限公司 | High-temperature adjusting stop valve suitable for aerospace engine |
| CN114719023B (en) * | 2022-03-31 | 2023-11-28 | 陕西空天动力研究院有限公司 | High-temperature adjusting stop valve suitable for aerospace engine |
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