JPH0454485Y2 - - Google Patents

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a pressure control valve installed in an air bleed system of an air conditioner mounted on an aircraft.

[Prior Art] Air conditioners for aircraft include, for example, an axial flow compressor 10 of an engine, as shown in FIG.
The high-temperature, high-pressure bleed air B extracted from 1 is introduced into an air cycle machine (ACM) 102, and is subjected to adiabatic compression in a compressor C, heat exchange with ram air L (outside air) in a heat exchanger 103, and adiabatic expansion in a turbine T. After cooling through the process, this cold air is introduced into the mixer 104, and bleed air B from the compressor 101 is introduced into the mixer 104 to perform necessary dehumidification, temperature adjustment, etc. for the cold air. A system for supplying the pressurized chamber 105 such as the above is generally employed. A primary pressure control valve 106 is provided on the upstream side of the ACM 102 to adjust the high-pressure Brido air B to a predetermined operating pressure, and a secondary pressure control valve 107 is provided on the downstream side of the ACM 102. It is customary to control the downstream pressure required at 105. Conventionally, the pressure control valve 107 used for this secondary pressure regulation has a mechanism in which a diaphragm and a spring are combined to open and close the valve plate. Of a pair of chambers divided by a diaphragm, a set pressure (generally atmospheric pressure) is introduced into the chamber on the side where the spring is housed, and the outlet pressure of the pressure control valve is introduced into the chamber on the opposite side. If the pressure is lower than the set pressure, the diaphragm is driven in the direction of increasing the valve opening, and if the outlet pressure is higher than the set pressure, the diaphragm is driven in the direction of decreasing the valve opening. In other words, the pressure control valve merely drives a differential pressure to maintain the outlet pressure at the set pressure, and the outlet pressure is maintained at the initial set pressure from beginning to end, regardless of the flight altitude, according to the outside air. It's nothing more than that. In addition, there is no existing system that can control the downstream pressure as a function of the flight altitude of the aircraft.
In most cases, the system is consuming more bleed air than necessary. This is because the downstream pressure regulated by the pressure control valve is set to the maximum pressure required by the system, so extra bleed air is taken in during normal operation.

[Problems to be solved by the invention] However, the amount of bleed air required for an aircraft air conditioning system is normally required to be controlled linearly as a function of the flight altitude. This is because as the flight altitude increases, the temperature decreases, so less bleed air is needed for cooling, and bleed air that is more than necessary increases the drag loss of the aircraft, which is undesirable. However, on the other hand, it is also true that there are cases where extra air is required depending on the flight conditions (for example, when air is used to protect the pit wind from rainwater during navigation in the rain). In such a case, it must be possible to control the downstream pressure of the pressure control valve non-linearly with the flight altitude according to the conditions.

In consideration of the characteristics required for such aircraft air conditioning systems, the object of the present invention is to provide a pressure control valve for regulating secondary pressure that can normally control the downstream pressure linearly as a function of the flight altitude, and that has the function of being able to variably control the downstream pressure non-linearly with the flight altitude when necessary.

[Means for solving the problem] In order to achieve the above purpose, the present invention
Valve body 1 with a valve 2 that can be opened and closed
, a regulator 3 that reduces the upstream pressure introduced from the upstream side of the valve body 1 to generate control pressure, the control pressure generated by the regulator 3, the downstream pressure introduced from the downstream side of the valve body 1, and the main spring. The pressure control valve for an aircraft is composed of a combination of each element of a controller 4 which counterbalances the spring biasing force of 9 through a diaphragm 6 and opens and closes the valve 2 according to the balanced position of the diaphragm 6, a metering valve 11 that throttles the air introduced from the upstream side of the valve body 1 to lower the pressure of the regulator 3 to generate control pressure;
A vacuum bellows 13 that pulls the metering valve 11 in its opening direction in proportion to the ambient pressure, and a plurality of stages that pulls the metering valve 11 in its closing direction in response to control pressure generated in the metering valve 11. The metering valve 11 is configured to include diaphragms 12, 12 having different pressure receiving areas, and a control spring 18 that biases the metering valve 11 in its opening direction.
The diaphragm 12 has multiple stages with different pressure receiving areas.
, 12 is provided with a control pressure switching mechanism 14 for switching the sensing state of the control pressure.

[Function] With a pressure control valve configured as described above, when the flight altitude changes and the ambient pressure increases or decreases, the vacuum bellows 13 changes the force pulling the metering valve 11 of the regulator 3 in proportion to the pressure change. Accordingly, the metering valve 11 increases the amount of air introduced from the upstream side of the valve body 1 in proportion to the altitude, and as a result, the regulator 3 increases the control pressure that is inversely proportional to the flight altitude. will occur. The control pressure generated by this regulator 3 is
The controller 4 changes the balance position of the diaphragm 6 so as to counteract the downstream pressure introduced from the downstream side of the valve body 1 with the spring biasing force of the main spring 9, and correspondingly changes the opening of the valve 2 of the valve body 1. Since the valve 2 is opened and closed, the downstream pressure of the valve 2 can be controlled linearly (inversely proportional to the flight altitude) as a function of the flight altitude. In addition, if it is desired to control the downstream pressure regardless of the flight altitude depending on the flight conditions, etc., the control pressure switching mechanism 14 can be used to sense the control pressure using the diaphragm 12.
, 12. In this way, since the pressure receiving areas are different between the multiple stages of diaphragms 12, 12, the traction force in the opening direction acting on the metering valve 11 in the regulator 3 can be changed in stages. As a result, the control pressure generated by the regulator 3 can be varied in stages, so the downstream pressure can be controlled non-linearly with the flight altitude by adjusting the valve opening from the controller 4. easily possible.

[Example] Hereinafter, the present invention will be described in more detail with reference to an example shown in the drawings.

FIG. 1 shows the system outline of the pressure control valve according to the present invention. A regulator 3 that generates control pressure by lowering the upstream pressure introduced from the upstream side of 1 according to a predetermined control law, and this regulator 3
The control pressure generated in the butterfly valve 2 is balanced with the downstream pressure of the valve body 1, etc.
It is constructed by combining each element of the controller 4 that opens and closes.

The valve body 1 is a cylindrical body having a bleed air inlet 1a at one end and an outlet 1b at the other end, and upstream and downstream bleed air pipes are connected in series to both ends, and serves to adjust the downstream pressure to a predetermined level by reducing the amount of bleed air according to the opening of the butterfly valve 2. An upstream pressure sensing port (filter assembly) 5 for introducing upstream pressure to the regulator 3 is attached to one side of the upstream pipe of the valve body 1.

Further, the controller 4 has a diaphragm 6 disposed within a chamber 4a erected on the valve body 1.
The diaphragm 6 is disposed so as to be movable up and down, the diaphragm 6 is moved to a balanced position where the forces acting from both sides of the diaphragm are balanced, and a mechanism is provided to open and close the butterfly valve 2 according to the amount of displacement. It is. That is, on the lower surface side of the diaphragm 6, there is a downstream pressure introduced from the downstream pressure sensing port 7 which is opened to the downstream side pipe line (not shown) of the valve body 1 via the pressure conduction pipe line 8, and the chamber 4.
While the spring biasing force of the main spring 9 interposed in a is applied, the regulator 3 is
The control pressure generated by the diaphragm 6 is introduced through the pressure conduits a, b, and c, so that the diaphragm 6 is held in a balanced position where the forces acting from both sides are balanced. The diaphragm 6 and the valve plate 2 are connected by a link 10 passing through the valve body 1, and the vertical movement of the diaphragm 6 is converted into the opening/closing movement of the valve plate 2. In other words, when the control pressure is dominant and the diaphragm 6 descends, the butterfly valve 2 rotates in the opening direction to increase the flow rate and increase the downstream pressure, and conversely, the downstream pressure and the spring biasing force of the main spring 9 are When the diaphragm 6 rises in a dominant manner, the operation opposite to the above is performed. In addition, 4b in the figure is an adjustment screw provided at the top of the chamber 4a, which comes into contact with the diaphragm 6 to regulate the upper limit of its rise, thereby setting the minimum closing angle of the butterfly valve 2 and the corresponding lower limit of the downstream pressure. .

The regulator 3 that generates the control pressure necessary for the controller 4 has the following configuration. The regulator 3 includes a main body (storage case) 3a that includes a metering valve 11, upper and lower diaphragms 12, 12, etc., a vacuum bellows 13 energized by the main body 3a, and the diaphragms 12, 12.
2, and a control pressure switching mechanism 14 that switches the sensing state of the control pressure to 2.

First, to explain the internal configuration of the main body 3a, a valve chamber 15 is provided in the lower part of the main body 3a to accommodate the metering valve 11 so as to be movable up and down. An inflow port 15a that introduces upstream pressure (upstream air) via the pressure conduit 16 is open, and at the center of its upper end, this inflow air is passed through a restriction by the metering valve 11 to reach the upper control pressure. An outflow port 15b that flows out into the generation chamber 17 is opened. In this valve chamber 15, the metering valve 11 has a vacuum bellows 13 and a diaphragm 12 in opposite directions.
, 12, etc., and throttle the amount of air flowing out from the outflow port 15b in accordance with that position, and reduce the upstream pressure on the control pressure generation chamber 17 side in accordance with the amount of restriction. Generates control pressure. Specifically, when the metering valve 11 is displaced downward and the opening degree of the outflow port 15b increases (the amount of restriction decreases), the control pressure obtained on the pressure generation chamber 17 side increases, and conversely, the metering valve 11 increases. Valve 11
is displaced upward and the opening degree of the outflow port 15b decreases (the amount of throttling increases), the control pressure obtained on the pressure generating chamber 17 side decreases. In addition, on the control pressure generation chamber 17 side,
Upper and lower two diaphragms 12, 12 are interposed so as to face the outflow port 15b, airtightly partitioning each chamber. These diaphragms 12, 12 have different pressure receiving areas, and the upper diaphragm 12 is larger than the lower diaphragm 12.
The pressure receiving area is larger than that of the previous model. Which of the diaphragms 12, 12 is made to sense the control pressure can be freely switched by a control pressure switching mechanism 14, which will be described later. And also these diaphragms 12,1
A control spring 18 is interposed in the chamber 17a between the control spring 2 and the inner surface of the top of the main body 3a, and the spring biasing force expressed as the product of the spring constant and the displacement amount acts as a force that constantly pushes the diaphragms 12, 12 downward. be acted upon. These two upper and lower diaphragms 12, 12 and the metering valve 11 are connected by a connecting rod 19 inserted through the outflow port 5b, and act on the diaphragms 12, 12 as described later. The resultant force of the control pressure and the spring biasing force of the control spring 18 gives an upward traction force to the metering valve 11. Note that the air discharged from the outflow port 5b to the control pressure generation chamber 17 is discharged to the outside from an orifice 20 provided on one side of the pressure generation chamber 17; The pressure conduit a is connected to the pressure generating chamber 17, and the control pressure generated in the pressure generation chamber 17 is introduced from the pressure conduit a to the controller 4 via the conduits b and c. It will be applied to the upper surface side. Further, a vent 21 is provided at the center of the top of the main body 3a to communicate the upper chamber 17a of the diaphragm 12 with the outside.

Next, the vacuum bellows 13 will be explained. The vacuum bellows 13 is located below the main body 3a of the regulator 3, and its lower surface side is fixed to the base 22. This vacuum bellows 13 receives ambient pressure (external air pressure) on its outer peripheral surface and tends to contract in proportion to the ambient pressure. The ambient pressure acting on the vacuum bellows 13 changes in accordance with the flight altitude of the aircraft. The upper end of this vacuum bellows 13 and the metering valve 11 in the main body 3a are connected by a connecting rod 23, and the vacuum bellows 1
3 applies a downward traction force to the metering valve 11 in its opening direction through its contraction. In addition, in response to the downward pulling force of the vacuum bellows 13, the diaphragm 12 or 12 applies an upward pulling force in the closing direction of the metering valve 11 via the connecting rod 19, and the control spring 18 also applies an upward pulling force to the metering valve 11 through the connecting rod 19. A spring biasing force in the same direction as the traction force of the vacuum bellows 13 is applied to the metering valve 11 via.
Therefore, the metering valve 11 in the regulator body 3a has a traction force (ambient pressure) of the vacuum bellows 13 acting in the valve opening direction and a control spring 18 within its valve chamber 15.
The metering valve 11 is held at a position where the spring biasing force and the traction force (generated control pressure) of the diaphragm 12 or 12 acting in the valve closing direction are balanced, and the metering valve 11 is held at a position where the control pressure corresponding to the valve opening degree is maintained. will be generated on the control pressure generation chamber 17 side.

Furthermore, to explain the control pressure switching mechanism 14, this switching mechanism 14 is an element for selecting which of the two upper and lower diaphragms 12, 12 should receive the control pressure generated by the regulator 3. A solenoid valve 25 is installed in a branch pressure conduit 24 that leads control pressure from the pressure conduit a to the chamber 17b formed between the diaphragms 12 and 12.
It is constructed by intervening. That is, as shown in the figure, when the solenoid valve 25 is turned ON and the high pressure is set, the control pressure is felt only by the lower diaphragm 12, while when the solenoid valve 25 is turned OFF and the low pressure is set, the control pressure is felt by the chamber 17b. The control pressure is applied to both diaphragms 12, 12, and in this state it is equivalent to the control pressure being felt only by the upper diaphragm 12. The diaphragms 12 and 12 have different pressure-receiving areas, and the upper diaphragm 12 is set larger. Therefore, the traction force for the metering valve 11 is small when the pressure is set to high, and the traction force is large when the pressure is set to low. , Therefore, in the former setting state, the generated control pressure increases,
In the latter setting state, the generated control pressure is small, and the stepwise switching of this pressure setting state can be instantaneously performed by switching the solenoid valve 25 ON/OFF.

In the illustrated embodiment, reference numeral 26 is a relief valve assembly provided at the connection between the pressure conduit a and b, which releases the relief valve when a control pressure of a certain level or more is generated in the conduit a, etc. fulfill one's role. Reference numeral 27 is a solenoid valve installed at the connection between the pressure conduits b and c, which is turned off during pressure control, but when turned on, disconnects the pressure conduit b and c. The introduction of control pressure to the controller 4 is cut off, and the butterfly valve 2 of the valve body 1 is placed in a normally closed state. and d is the pressure conduit 10
A pressure conduction conduit branched from b and selectively connected to the pressure conduit conduit 8 to the downstream pressure sensing port 7 side via a shuttle valve 28, which is connected to the regulator 3 when the solenoid valve 27 is ON. The control pressure generated by the controller 4 is guided to the lower surface side of the diaphragm 6 of the controller 4 to keep the butterfly valve 2 in a closed state.

Next, the operation of the pressure control valve configured as described above will be explained. The outline of the pressure control will now be described assuming a high pressure setting state as shown in the figure. When the flight altitude of the aircraft changes under the pressure control state of the air conditioning system and the ambient pressure increases or decreases accordingly, the vacuum bellows 13 of the regulator 3
The force that pulls the metering valve 11 in the opening direction changes in proportion to the pressure change. That is, the metering valve 11 increases the throttle amount of air introduced from the upstream side of the valve body 1 in proportion to the altitude, and as a result, the regulator 3 generates a control pressure that is inversely proportional to the flight altitude. However, the controller 4 that adjusts the butterfly opening degree of the valve body 1 maintains a balance between the control pressure generated by the regulator 4, the downstream pressure introduced from the downstream side of the valve body 1, and the spring biasing force of the main spring 9. Since the displacement of the diaphragm 6 is converged to this position, and the butterfly opening degree is controlled within the valve body 1 in accordance with the balanced position of the diaphragm 6, the downstream pressure of the valve body 1 (valve plate 2) is eventually controlled. can be controlled linearly as a function of the flight altitude as shown by the solid line in FIG. 2, that is, in inverse proportion to the flight altitude.

The above is a control law for a high pressure setting state in which the solenoid valve 25 energized by the regulator 3 is turned ON, but the content of control that linearly controls the downstream pressure as a function of flight altitude is as follows by turning the solenoid valve 25 OFF. The same procedure is carried out in the case of the low pressure setting state, and in this case, the relationship between the flight altitude and the downstream pressure as shown by the dotted line in FIG. 2 is obtained. That is, in this case, the diaphragm 1 whose control pressure is sensed within the regulator 3
2 has a relatively large pressure receiving area, the regulator 3 generates a control pressure that is one step lower than when the high pressure is set, and therefore the controller 4 controls the downstream pressure at a one step lower level. The pressure control based on these high pressure settings, the low pressure control, and the pressure control are the solenoid valve 2 that constitutes the control pressure switching mechanism 14.
5 ON/OFF switching operations allow mutual compatibility whenever necessary. In detail, not only can downstream pressure be controlled linearly according to flight altitude, but if you want to control downstream pressure regardless of flight altitude due to changes in flight conditions, etc., you can use the control pressure switch. Mechanism 14 (Solenoid valve 2
By switching 5), the downstream pressure can be increased or decreased in stages. In other words, flight altitude and non-linear pressure control are also possible.

Therefore, by using a pressure control valve with such a configuration and operating mechanism, the amount of bleed air required for the air conditioning system can be constantly controlled to the minimum necessary amount regardless of changes in flight conditions or functional requirements. This eliminates waste in the operation of the air conditioning system and eliminates negative effects on the flight performance of the aircraft.

Although the present invention has been described above based on one embodiment, it goes without saying that the application of the present invention is not limited to only the configuration shown in the drawings and detailed above.
For example, the type of the valve 2 interposed in the valve body 1, the specific structure of the controller 4, the opening/closing mechanism of the valve plate 2 using its diaphragm 6, the internal structure of the regulator 3, the arrangement of elements, etc. may vary. There is room for change.
Further, the diaphragms installed in the main body 3a of the regulator 3 may be arranged in three or more stages with different pressure receiving areas in order to make it possible to vary the downstream pressure in multiple stages. The structure of the control pressure switching mechanism 14 that switches the sensitive state of the pressure can be modified as necessary.

[Effects of the invention] Conventional pressure control valves for air conditioning systems always adjust the downstream pressure to a set pressure, regardless of the flight altitude. The set pressure at that time was determined to be the pressure required when the largest amount of air was needed, such as when aiming during takeoff and landing, and when the air was used to protect the pit wind from rain. Therefore, when the flight altitude increases and the absolute amount of air required for air conditioning decreases, and when the air is not being used for rainwater protection, a large amount of wasted air is extracted from the engine bleed air. There was a problem that the

On the other hand, according to the pressure control valve of the present invention,
The downstream pressure required by the system is normally controlled linearly as a function of flight altitude, but can also be controlled in non-linear steps when necessary, so that the engine bleed air extracted for air conditioning is always controlled. It has the excellent effect of being able to control it to the minimum necessary, preventing drag loss, and when using air to protect against rainwater, it can be done simply by changing the set pressure. be.

[Brief explanation of the drawing]

FIG. 1 is a schematic sectional view of a pressure control valve showing an embodiment of the present invention. FIG. 2 is a diagram showing the relationship between the downstream pressure caused by the pressure control valve of this embodiment and the flight altitude, and FIG. 3 is a system diagram showing a conventional air conditioner for an aircraft. 1... Valve body, 2... Valve (valve plate), 3... Regulator, 4... Controller, 5... Upstream pressure sensitive port, 6... Diaphragm, 7... Downstream pressure sensitive port, 8... Pressure continuity Conduit, 9... Main spring, 10... Link, 1
1... Metering valve, 12, 12...
Diaphragm, 13... Vacuum bellows, 14...
Control pressure switching mechanism, 15...valve chamber,
15a...Inflow port, 15b...Outflow port,
16...Pressure communication pipe line, 17...Control pressure generation chamber, 18...Control spring, 1
9... Connecting rod, 20... Orifice, 21... Vent, 22... Base, 23... Connecting rod, 24...
...Branch pressure conduit, 25...Solenoid valve, a to d...Pressure conduit.

Claims (1)

[Scope of utility model registration request] Valve body 1 with a valve 2 that can be opened and closed
, a regulator 3 that reduces the upstream pressure introduced from the upstream side of the valve body 1 to generate control pressure, the control pressure generated by the regulator 3, the downstream pressure introduced from the downstream side of the valve body 1, and the main spring. The pressure control valve for an aircraft is composed of a combination of each element of a controller 4 which counterbalances the spring biasing force of 9 through a diaphragm 6 and opens and closes the valve 2 according to the balanced position of the diaphragm 6, a metering valve 11 that throttles the air introduced from the upstream side of the valve body 1 to lower the pressure of the regulator 3 to generate control pressure;
A vacuum bellows 13 that pulls the metering valve 11 in its opening direction in proportion to the ambient pressure, and a plurality of stages that pulls the metering valve 11 in its closing direction in response to control pressure generated in the metering valve 11. The metering valve 11 is configured to include diaphragms 12, 12 having different pressure receiving areas, and a control spring 18 that biases the metering valve 11 in its opening direction.
The diaphragm 12 has multiple stages with different pressure receiving areas.
, 12. A pressure control valve characterized in that a control pressure switching mechanism 14 is provided for switching a sensing state of the control pressure with respect to , 12.