CN111852657A - Double-flow-path air-entraining mixing anti-icing device and method and aircraft engine - Google Patents
Double-flow-path air-entraining mixing anti-icing device and method and aircraft engine Download PDFInfo
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- CN111852657A CN111852657A CN202010539869.9A CN202010539869A CN111852657A CN 111852657 A CN111852657 A CN 111852657A CN 202010539869 A CN202010539869 A CN 202010539869A CN 111852657 A CN111852657 A CN 111852657A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
Abstract
The invention discloses a double-flow-path air-entraining mixing anti-icing device and method and an aircraft engine. And two air flows are mixed to form medium-temperature low-pressure air flows which are output to an anti-icing part, so that the air entraining temperature is ensured not to exceed the use temperature range of the air inlet device material, and the anti-icing temperature requirement is met. In addition, the air flow pressure ratio of the two sides of the throttling hole is controlled to be above the critical pressure ratio by arranging the throttling hole, the flow of the high-temperature high-pressure bleed air is not changed along with the adjustment of the flow area of the hydraulic drive butterfly valve, and the adjustment of the flow area of the hydraulic drive butterfly valve only changes the flow of the low-temperature low-pressure bleed air, so that the flow distribution proportion of the high-temperature high-pressure bleed air and the low-temperature low-pressure bleed air is effectively and accurately controlled.
Description
Technical Field
The invention relates to the technical field of an anti-icing function of an air inlet device of an aircraft engine, in particular to a double-flow-path air-entraining mixing anti-icing device, a double-flow-path air-entraining mixing anti-icing method and an aircraft engine adopting the double-flow-path air-entraining mixing anti-icing device.
Background
When the aircraft passes through a cloud layer with icing meteorological conditions, icing at the inlet of the engine can cause the section of the inlet to be reduced, so that the air flow is reduced, and simultaneously, the flow field at the inlet of the engine can be changed, so that the surge of a gas compressor and continuous power loss can be caused in severe cases; meanwhile, the ice blocks are possibly sucked into the flow channel by the engine after falling off, so that parts such as an engine compressor and the like are damaged, and a flight accident is caused. In order to ensure the flight safety of the airplane when the airplane passes through a cloud layer with icing meteorological conditions, the air inlet device of the engine generally has a hot air heating anti-icing function, and when anti-icing is required, a certain amount of hot air is extracted from the air compressor to heat the air inlet device, so that the icing of the air inlet device or the accumulation of over-thick ice is avoided.
Fig. 1 shows an anti-icing bleed air line of a european RTM322 engine, which is a single-location bleed air installation. The compressor of the engine adopts a combination mode, namely a combination mode of a 3-stage axial flow compressor and a single-stage centrifugal impeller, the anti-icing air-entraining position is positioned at the outlet of the centrifugal impeller, and the temperature and the pressure of the position are both higher. However, when the engine is in a high-power state, the bleed air temperature is relatively high (the bleed air temperature is as high as about 400 ℃), and if the air intake device is made of a lightweight aluminum material (the use temperature should be controlled below 200 ℃), the temperature of a local area of the air intake device may exceed the use range of the material. However, if the air-entraining position is placed in front of the inlet of the centrifugal impeller and behind the outlet of the axial-flow compressor, the problem of low air-entraining temperature exists, the air-entraining demand is greatly increased, and even in a small state (the air-entraining temperature is as low as about 30 ℃), even if the air-entraining amount is increased, the anti-icing can not be realized. If the bleed position is placed between the inlet and the outlet of the centrifugal impeller, although the bleed temperature is proper, the vibration problem caused by bleed may exist, and the safety of the engine is affected.
Disclosure of Invention
The invention provides a double-flow-path air-entraining mixing anti-icing device and method and an aircraft engine, and aims to solve the technical problem that the traditional air-entraining anti-icing device cannot meet the anti-icing temperature requirement, the heat resistance of air inlet device materials and the vibration of the engine caused by air entrainment.
According to one aspect of the invention, a double-flow-path bleed air blending anti-icing device is provided for providing hot air with moderate temperature for an anti-icing function of an air inlet device of an aircraft engine, and comprises:
the first air-entraining pipe is used for carrying out high-temperature and high-pressure air-entraining;
the second air-entraining pipe is used for carrying out low-temperature low-pressure air-entraining;
the air outlet pipe is respectively communicated with the first air guide pipe and the second air guide pipe, and high-temperature high-pressure gas introduced by the first air guide pipe and low-temperature low-pressure gas introduced by the second air guide pipe are mixed in the air outlet pipe to form medium-temperature low-pressure gas which is then output to the anti-icing part;
the hydraulic drive butterfly valve is arranged on the gas outlet pipe and is used for adjusting the flow of the output medium-temperature low-pressure gas;
the electric valve is arranged on the air outlet pipe and is used for controlling the on-off of the air outlet pipe;
and an orifice for controlling the air flow pressure ratio at two sides to be higher than the critical pressure ratio is arranged between the air entraining port of the first air entraining pipe and the air outlet pipe, and a one-way valve only allowing the air flow to flow from the second air entraining pipe to the air outlet pipe is arranged on the second air entraining pipe.
Further, the outlet duct sets up with the second bleed pipe is coaxial, double-flow-path bleed mixing anti-icing device still includes the gas collecting cavity that sets up with the second bleed pipe is coaxial, just the gas collecting cavity cover is established in the hookup location department of outlet duct and second bleed pipe, first bleed pipe and gas collecting cavity intercommunication, the orifice sets up the hookup location department of outlet duct and second bleed pipe just is the circumference equipartition, the orifice is the inclined hole and is partial to the flow direction of low temperature low pressure gas, the high temperature high pressure gas that first bleed pipe introduced gets into in the outlet duct and mixes with low temperature low pressure gas through the orifice entering circumference equipartition behind the gas collecting cavity.
Furthermore, the flow area of the air outlet pipe is 5-15 times of the flow area of the throttling hole, the flow area of the electric valve is 5-10 times of the flow area of the throttling hole, and the maximum flow area of the hydraulic drive butterfly valve is 3.5-10 times of the flow area of the throttling hole.
Furthermore, the flow area of the first air guide pipe is 1-5 times of the flow area of the throttle hole, the flow area of the second air guide pipe is 3-10 times of the flow area of the throttle hole, and the maximum flow area of the check valve is 2.5-10 times of the flow area of the throttle hole.
Furthermore, the hydraulic drive butterfly valve and the compressor guide vane share one hydraulic mechanism, and the electric valve is electrically connected with an electronic controller of the engine.
Further, when the aircraft engine adopts a combined compressor, the air-entraining position of the first air-entraining pipe is placed at the downstream of the outlet of the centrifugal impeller, and the inducing position of the second air-entraining pipe is placed in front of the inlet of the centrifugal impeller and behind the outlet of the axial compressor;
when the aircraft engine adopts a full axial-flow compressor, the air-entraining position of the first air-entraining pipe is placed at a certain stage of 70% -100% of the compressor stage, and the inducing position of the second air-entraining pipe is placed at a certain stage of 40% -70% of the compressor stage.
Further, the electrically operated valve is disposed upstream of the hydraulically driven butterfly valve.
Furthermore, the aperture of the throttling hole is 1.5 mm-5 mm, and the inclination angle is 10-45 degrees.
The invention also provides a double-flow-path air-entraining mixing anti-icing method, which adopts the double-flow-path air-entraining mixing anti-icing device and comprises the following steps:
step S1: detecting whether an anti-icing function needs to be started or not by using an anti-icing detector on the airplane;
step S2: after the anti-icing detector detects that the anti-icing function needs to be started, the electric valve is controlled to be opened, and the opening of the hydraulic drive butterfly valve is adjusted according to the adjustment rule of the hydraulic mechanism;
Step S3: and controlling the electric valve to be closed after the anti-icing detector detects that the anti-icing function does not need to be started.
The invention also provides an aircraft engine which adopts the double-flow-path air-entraining mixing anti-icing device.
The invention has the following effects:
the double-flow-path air-entraining mixing anti-icing device only comprises three valves, namely an electric valve, a one-way valve and a hydraulic drive butterfly valve, and the three valves have simple and reliable structures and light weight, do not need complex control and execution mechanisms, and can not obviously increase the weight of an engine after being installed on the engine. And moreover, the high-temperature high-pressure air entraining and the low-temperature low-pressure air entraining are mixed to form medium-temperature low-pressure airflow which is output to the anti-icing part, so that the air entraining temperature is ensured not to exceed the use temperature range of the material of the air inlet device, the anti-icing temperature requirement is met, the air entraining temperature and the air flow change gently along with the power state of the engine, and the condition that the air entraining temperature and the air flow suddenly jump in a certain state can not occur. In addition, the air flow pressure ratio of the two sides of the throttling hole is controlled to be above the critical pressure ratio by arranging the throttling hole, the flow of the high-temperature high-pressure bleed air is not changed along with the adjustment of the flow area of the hydraulic drive butterfly valve, and the adjustment of the flow area of the hydraulic drive butterfly valve only changes the flow of the low-temperature low-pressure bleed air, so that the flow distribution proportion of the high-temperature high-pressure bleed air and the low-temperature low-pressure bleed air is effectively and accurately controlled.
In addition, the double-flow-path air-entraining, mixing and anti-icing method has the advantages that in addition, the opening of the hydraulic drive butterfly valve is adjusted based on the adjustment rule of the hydraulic mechanism, the opening control rule of the hydraulic drive butterfly valve is matched with the working state of the engine, the flow and the air-entraining temperature of the mixing air flow change slowly along with the power state of the engine, the situation that the air-entraining temperature and the flow suddenly jump in a certain state cannot occur, and the anti-icing effect of the mixing air flow is good.
In addition, the aircraft engine of the invention also has the advantages.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
figure 1 is a schematic diagram of the ice protection bleed air circuit of a prior art RTM322 engine.
FIG. 2 is a schematic illustration of the piping connections of the dual flow path bleed air blending anti-icing assembly of the preferred embodiment of the present invention.
Fig. 3 is a schematic partial sectional structure view of a double-flow-path bleed air blending anti-icing device provided with a gas collecting cavity according to the preferred embodiment of the invention.
Figure 4 is a schematic representation of the planar temperature distribution of the air flow when the dual flow path bleed air blending anti-icing assembly of the preferred embodiment of the present invention is provided with an air collection chamber.
Fig. 5 is a schematic diagram of the three-dimensional temperature distribution of the air flow when the double-flow-path bleed air blending anti-icing device is provided with the air collecting cavity according to the preferred embodiment of the invention.
Figure 6 is a schematic diagram of the velocity profile of the air flow when the dual flow path bleed air blending anti-icing assembly of the preferred embodiment of the present invention is provided with a plenum.
FIG. 7 is a schematic flow diagram of a dual flow path bleed air blending anti-icing method according to another embodiment of the present invention.
In addition, in order to fully embody the effects of the temperature distribution diagram and the velocity distribution diagram, the applicant additionally submits an accessory, wherein the accessory comprises a plurality of color effect diagrams, and the diagram numbers in the accessory correspond to the diagram numbers in the drawings in the specification in a one-to-one mode.
Description of the reference numerals
11. A first bleed air duct; 12. a second bleed air duct; 13. an air outlet pipe; 14. an orifice; 15. a one-way valve; 16. an electrically operated valve; 17. a hydraulically driven butterfly valve; 18. a gas collection cavity.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
As shown in fig. 2, a preferred embodiment of the present invention provides a dual flow path bleed air dilution anti-icing assembly for providing hot gas at moderate temperatures for anti-icing functions of an aircraft engine air induction unit, the dual flow path bleed air dilution anti-icing assembly comprising:
the first air-entraining pipe 11 is used for carrying out high-temperature and high-pressure air-entraining;
a second bleed air pipe 12 for low-temperature and low-pressure bleed air;
the air outlet pipe 13 is respectively communicated with the first air guiding pipe 11 and the second air guiding pipe 12, and high-temperature high-pressure gas introduced by the first air guiding pipe 11 and low-temperature low-pressure gas introduced by the second air guiding pipe 12 are mixed in the air outlet pipe 13 to form medium-temperature low-pressure gas which is then output to an anti-icing part;
a hydraulic drive butterfly valve 17 which is arranged on the gas outlet pipe 13 and is used for adjusting the flow of the output medium-temperature low-pressure gas;
the electric valve 16 is arranged on the air outlet pipe 13 and is used for controlling the on-off of the air outlet pipe 13;
an orifice 14 for controlling the air flow pressure ratio on both sides above the critical pressure ratio is arranged between the bleed port of the first bleed air pipe 11 and the air outlet pipe 13, and a check valve 15 for only allowing the air flow to flow from the second bleed air pipe 12 to the air outlet pipe 13 is arranged on the second bleed air pipe 12.
It can be understood that the electric valve 16 has only two opening and closing gears, the opening of the valve does not need to be adjusted, the structure is simple and reliable, the weight is light, the weight of the engine is not obviously increased, the electric valve 16 is electrically connected with an electronic controller of the engine, and the opening or the closing of the electric valve 16 is controlled by the electronic controller. The electric valve 16 may be an electric butterfly valve, an electric ball valve or an electromagnetic valve. In addition, the one-way valve 15 can be automatically opened and closed according to the pressure on two sides, external force transmission input is not needed, and the one-way valve is simple and reliable in structure and lighter in weight. The hydraulic drive butterfly valve 17 and the compressor guide blade share one hydraulic mechanism, and the hydraulic mechanism belongs to equipment carried by the engine, so that the weight of the engine cannot be obviously increased, and specifically, the opening degree of the hydraulic drive butterfly valve 17 can be adjusted by structurally connecting a movable ring on the hydraulic mechanism for controlling the compressor guide blade and a movable disc of the hydraulic drive butterfly valve 17. Moreover, the opening control rule of the hydraulic drive butterfly valve 17 is matched with the working state of the engine, when the engine works in a low-power state, because the pressure of the medium-temperature low-pressure airflow formed after mixing is small and the temperature is low, the flow resistance of the hydraulic drive butterfly valve 17 is reduced to meet the anti-icing requirement, and therefore the flow area of the hydraulic drive butterfly valve 17 is increased; when the engine works in a high-power state, the pressure and the temperature of the mixing airflow are high, so that the flow resistance of the hydraulic drive butterfly valve 17 is properly improved to limit the anti-icing air-entraining quantity, and the flow area of the hydraulic drive butterfly valve 17 is reduced. In addition, the control law of the hydraulic drive butterfly valve 17 is completely opposite to that of the guide vanes of the compressor, and when the engine works in a low-power state, the flow area of the guide vanes of the compressor needs to be reduced in order to avoid surge of the compressor; along with the increase of the power state of the engine, the flow area of the guide vane of the compressor needs to be gradually enlarged. Because of the hydraulic mechanism of the engine, the hydraulic drive butterfly valve 17 only needs to be additionally provided with a pipeline with a movable disc and a dowel bar connected with the movable ring, and has simple and reliable structure and light weight. Therefore, the double-flow-path bleed air mixing anti-icing device only comprises three valves, namely the electric valve 16, the check valve 15 and the hydraulic drive butterfly valve 17, and the three valves are simple and reliable in structure, light in weight, free from obviously increasing the weight of the engine after being installed on the engine and convenient to control. Alternatively, a hydraulic mechanism may be provided separately for the hydraulically driven butterfly valve 17 for individual control.
The working principle of the double-flow-path air-entraining mixing anti-icing device in the embodiment is as follows:
when anti-icing air entraining is needed, an electronic controller of the engine controls an electric valve 16 to be opened, the pressure at the third position (namely the communication position of the air outlet pipe 13, the first air entraining pipe 11 and the second air entraining pipe 12) is lower than the pressure at the first position (namely the air entraining position of the first air entraining pipe 11) and the second position (namely the air entraining position of the second air entraining pipe 12), the two air flows of high temperature, high pressure, low temperature and low pressure are simultaneously entrained, and are mixed at the third position to form the air flow of medium temperature and low pressure, the flow of the mixed air flow is adjusted when a butterfly valve 17 is driven through hydraulic pressure, and the total flow of the two air flows is controlled in a proper range. When the anti-icing design is carried out, the bleed air flow corresponding to the opening degree of the hydraulic drive butterfly valve 17 is analyzed, and the bleed air flow is ensured to meet the heating anti-icing requirement of the air inlet device. In order to avoid the situation that the pressure at the third position is larger than that at the second position, so that the single-strand air flow with high temperature and high pressure enters the oil to bleed the air, an orifice 14 is arranged between the first position and the third position, and the orifice 14 can control the air flow pressure ratio at two sides to be above the critical pressure ratio, namely, the flow of the orifice 14 cannot be increased no matter how the pressure at the third position is reduced. In addition, the flow areas of the air outlet pipe 13, the electric valve 16 and the hydraulic drive butterfly valve 17 between the third position and the fourth position are larger than the flow area of the orifice 14, so that the pressure relief can be performed to a certain degree at the third position, and the check valve 15 is ensured to be in a forward flow state. The flow distribution ratio of the two air flows is controlled, because the air flow pressure ratio at two sides of the throttling hole 14 is higher than the critical pressure ratio, the flow of the high-temperature and high-pressure air flow is controlled by the throttling hole 14, the flow is basically not influenced by the flow area of the hydraulic driving butterfly valve 17, the flow area of the hydraulic driving butterfly valve 17 only influences the flow of the low-temperature and low-pressure air flow, and the flow of the low-temperature and low-pressure air flow can be controlled by adjusting the flow area of the hydraulic driving butterfly valve 17, so that the flow of the mixed air flow is controlled.
When the ice prevention and air entraining are not needed, the electronic controller of the engine controls the electric valve 16 to close, the pressure of the first position and the third position are basically the same, the two positions are in a high-pressure state, and the pressure of the two positions is greater than that of the second position, so that the one-way valve 15 is in a reverse cut-off state, low-temperature and low-pressure air flow cannot be continuously introduced, and the high-temperature and high-pressure air flow at the first position is prevented from flowing to the second position. Meanwhile, because the electric valve 16 is in a closed state, the air delivery pipe is closed, and no air flow flows to the anti-icing part.
It can be understood that the double-flow-path bleed air mixing anti-icing device of the embodiment only comprises three valves, namely the electric valve 16, the check valve 15 and the hydraulic drive butterfly valve 17, and the three valves are simple and reliable in structure, light in weight, free of complex control and execution mechanisms and cannot obviously increase the weight of an engine after being installed on the engine. And moreover, the high-temperature high-pressure air entraining and the low-temperature low-pressure air entraining are mixed to form medium-temperature low-pressure airflow which is output to the anti-icing part, so that the air entraining temperature is ensured not to exceed the use temperature range of the material of the air inlet device, the anti-icing temperature requirement is met, the air entraining temperature and the air flow change gently along with the power state of the engine, and the condition that the air entraining temperature and the air flow suddenly jump in a certain state can not occur. In addition, the air flow pressure ratio at the two sides of the throttle hole 14 is controlled to be above the critical pressure ratio by arranging the throttle hole, the flow of the high-temperature and high-pressure bleed air is not changed along with the adjustment of the flow area of the hydraulic drive butterfly valve 17, and the adjustment of the flow area of the hydraulic drive butterfly valve 17 only changes the flow of the low-temperature and low-pressure bleed air, so that the flow distribution proportion of the high-temperature and high-pressure bleed air and the low-temperature and low-pressure bleed air can be effectively and accurately controlled. In addition, the hydraulic driving butterfly valve 17 uses a hydraulic mechanism of the guide vanes of the air compressor, an additional adjusting control mechanism is not needed, and the hydraulic driving butterfly valve is simple in structure and accurate in control.
It will be appreciated that the outlet duct 13 is arranged coaxially with the second bleed air duct 12 or the axial direction of the two intersects, and preferably, the two ducts are arranged coaxially to improve the flow efficiency of the air flow. As shown in fig. 3, the dual-flow-path air-entraining mixing anti-icing device further includes a gas-collecting cavity 18 coaxially disposed with the second air-entraining pipe 12, the gas-collecting cavity 18 is sleeved at the connection position of the air outlet pipe 13 and the second air-entraining pipe 12, the first air-entraining pipe 11 is communicated with the gas-collecting cavity 18, the orifice 14 is disposed at the connection position of the air outlet pipe 13 and the second air-entraining pipe 12 and is circumferentially and uniformly distributed, and the orifice 14 is an inclined hole and is biased to the flow direction of the low-temperature and low-pressure gas. The high-temperature high-pressure gas introduced by the first air guide pipe 11 is firstly introduced into the gas collection cavity 18, and is buffered to a certain extent in the gas collection cavity 18, so that the flow rate and pressure of the high-temperature high-pressure gas flow are reduced, and then the high-temperature high-pressure gas enters the gas outlet pipe 13 through the orifices 14 uniformly distributed in the circumferential direction to be mixed with the low-temperature low-pressure gas, so that the temperature distribution and the speed distribution of the medium-temperature low-pressure gas flow formed after mixing are more uniform when the medium-temperature low-pressure gas flow circulates in the gas outlet pipe 13, and the mixing effect of the two gas flows is better, and the anti-icing effect is better, as shown in fig. 4 to 6 in particular, it can be obviously. The number of the orifices 14 is preferably 12-24, the hole shape is preferably a round hole, the aperture of a single orifice 14 is 1.5-5 mm, the inclination angle is 10-45 degrees, when the size of the orifice 14 is designed in the range, the airflow pressure ratio on two sides can be stably controlled above the critical pressure ratio, and the reliability is good.
Preferably, in order to ensure that the check valve 15 always maintains a forward flow state when the electric valve 16 is opened, the flow area of the outlet pipe 13 is 5 to 15 times the flow area of the orifice 14, the flow area of the electric valve 16 is 5 to 10 times the flow area of the orifice 14, and the maximum flow area of the hydraulically driven butterfly valve 17 is 3.5 to 10 times the flow area of the orifice 14, thereby effectively relieving the pressure at the third position. It will be appreciated that the outlet duct 13 has a larger flow area than the electric valve 16 and that the electric valve 16 has a larger flow area than the maximum flow area of the hydraulically actuated butterfly valve 17. More preferably, in order to ensure the flow efficiency of the high-temperature and high-pressure bleed air and the low-temperature and low-pressure bleed air, the flow area of the first bleed air pipe 11 is 1 to 5 times the flow area of the orifice 14, the flow area of the second bleed air pipe 12 is 3 to 10 times the flow area of the orifice 14, and the maximum flow area of the check valve 15 is 2.5 to 10 times the flow area of the orifice 14. In addition, the flow area of the outlet duct 13 is larger than the flow area of the second bleed air duct 12, and the flow area of the second bleed air duct 12 is larger than the flow area of the first bleed air duct 11.
It will be understood that when the aircraft engine uses a combined compressor, the bleed position of the first bleed air duct 11 is placed downstream of the centrifugal impeller outlet, and the bleed position of the second bleed air duct 12 is placed before the centrifugal impeller inlet and after the axial compressor outlet; when the aircraft engine adopts a full axial-flow compressor, the air-entraining position of the first air-entraining pipe 11 is placed at a certain stage of 70% -100% compressor stage, and the inducing position of the second air-entraining pipe 12 is placed at a certain stage of 40% -70% compressor stage. By arranging the air-entraining positions of the first air-entraining pipe 11 and the second air-entraining pipe 12 at the positions, high-temperature high-pressure gas and low-temperature low-pressure gas can be respectively introduced conveniently, and the vibration problem caused by air-entraining can be avoided, so that the safety of the engine is ensured.
In addition, the electric valve 16 is preferably arranged upstream of the hydraulic drive butterfly valve 17, so as to rapidly control the make-and-break of the blending gas flow and to adjust the hydraulic drive butterfly valve 17.
In addition, as shown in fig. 7, another embodiment of the present invention further provides a dual-flow-path bleed air blending anti-icing method, preferably using the dual-flow-path bleed air blending anti-icing apparatus, including the following steps:
Step S1: detecting whether an anti-icing function needs to be started or not by using an anti-icing detector on the airplane;
step S2: after the anti-icing detector detects that the anti-icing function needs to be started, the electric valve 16 is controlled to be opened, and the opening of the hydraulic drive butterfly valve 17 is adjusted according to the adjustment rule of the hydraulic mechanism;
step S3: the electric valve 16 is controlled to close after the anti-icing detector detects that the anti-icing function does not need to be started.
It can be understood that, in step S1, an anti-icing detector on the aircraft is used to detect whether the anti-icing bleed air needs to be opened, where the anti-icing detector belongs to an existing product on the aircraft engine, a specific working principle is not specifically limited herein, the anti-icing detector is electrically connected to an electronic controller of the engine, when the anti-icing detector detects that the anti-icing bleed air needs to be opened or the anti-icing bleed air does not need to be opened, the anti-icing detector generates a feedback signal and transmits the feedback signal to the electronic controller, or the anti-icing detector directly transmits a detection result to the electronic controller, and the electronic controller determines whether the anti-icing bleed air needs to be opened.
In addition, in the step S2, since the adjustment rule of the hydraulic mechanism is already matched with the rotation speed of the engine, that is, the adjustment rule of the hydraulic mechanism is already matched with the power state of the engine, the adjustment of the opening degree of the hydraulic drive butterfly valve 17 based on the adjustment rule of the hydraulic mechanism can realize the adjustment of the blending airflow flow rate to be matched with the current power state of the engine, when the engine is in a low power state, the opening degree of the hydraulic drive butterfly valve 17 is increased, and when the engine is in a high power state, the opening degree of the hydraulic drive butterfly valve 17 is decreased. The opening of the hydraulic drive butterfly valve 17 is adjusted by controlling a hydraulic mechanism of the guide vanes of the air compressor through the electronic controller, the electric valve 16 is controlled to be opened or closed through the electronic controller, the whole process is automatically controlled, and the control mode is simple and accurate.
The double-flow-path air-entraining, mixing and anti-icing method has the advantages that besides the advantages of the double-flow-path air-entraining, mixing and anti-icing device, the opening of the hydraulic drive butterfly valve 17 is adjusted based on the adjustment rule of the hydraulic mechanism, the opening control rule of the hydraulic drive butterfly valve 17 is matched with the working state of an engine, the flow and the air-entraining temperature of the mixing air flow are gently changed along with the power state of the engine, the situations that the air-entraining temperature and the flow suddenly jump in a certain state cannot occur, and the anti-icing effect of the mixing air flow is good.
In addition, the invention also provides an aircraft engine which adopts the double-flow-path air-entraining mixing anti-icing device.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A double-flow-path air-entraining mixing anti-icing device is used for providing hot air with moderate temperature for the anti-icing function of an air inlet device of an aircraft engine and is characterized in that,
the method comprises the following steps:
The first air-entraining pipe (11) is used for carrying out high-temperature and high-pressure air-entraining;
a second bleed air pipe (12) for low-temperature and low-pressure bleed air;
the air outlet pipe (13) is respectively communicated with the first air guide pipe (11) and the second air guide pipe (12), and high-temperature and high-pressure gas introduced by the first air guide pipe (11) and low-temperature and low-pressure gas introduced by the second air guide pipe (12) are mixed in the air outlet pipe (13) to form medium-temperature and low-pressure gas which is then output to an anti-icing part;
the hydraulic drive butterfly valve (17) is arranged on the gas outlet pipe (13) and is used for adjusting the flow of the output medium-temperature low-pressure gas;
the electric valve (16) is arranged on the air outlet pipe (13) and is used for controlling the on-off of the air outlet pipe (13);
an orifice (14) used for controlling the air flow pressure ratio at two sides to be higher than the critical pressure ratio is arranged between the air inlet of the first air guiding pipe (11) and the air outlet pipe (13), and a one-way valve (15) only allowing the air flow to flow from the second air guiding pipe (12) to the air outlet pipe (13) is arranged on the second air guiding pipe (12).
2. The dual flow path air entraining admixture anti-icing assembly of claim 1,
outlet duct (13) and second bleed pipe (12) coaxial arrangement, double-flow-path bleed mixing anti-icing device still includes gas collection chamber (18) with the coaxial arrangement of second bleed pipe (12), just gas collection chamber (18) cover is established in the hookup location department of outlet duct (13) and second bleed pipe (12), first bleed pipe (11) and gas collection chamber (18) intercommunication, orifice (14) set up the hookup location department of outlet duct (13) and second bleed pipe (12) and be the circumference equipartition, orifice (14) are the inclined hole and are partial to in the gaseous flow direction of low temperature low pressure, the high temperature high pressure gas that first bleed pipe (11) introduced lets in gas collection chamber (18) back through orifice (14) entering outlet duct (13) of circumference equipartition and mixes with low temperature low pressure gas.
3. The dual flow path air entraining admixture anti-icing assembly of claim 1,
the flow area of the air outlet pipe (13) is 5-15 times of the flow area of the throttling hole (14), the flow area of the electric valve (16) is 5-10 times of the flow area of the throttling hole (14), and the maximum flow area of the hydraulic drive butterfly valve (17) is 3.5-10 times of the flow area of the throttling hole (14).
4. The dual flow path air entraining admixture anti-icing assembly of claim 3,
the flow area of the first air guide pipe (11) is 1-5 times of the flow area of the throttling hole (14), the flow area of the second air guide pipe (12) is 3-10 times of the flow area of the throttling hole (14), and the maximum flow area of the one-way valve (15) is 2.5-10 times of the flow area of the throttling hole (14).
5. The dual flow path air entraining admixture anti-icing assembly of claim 1,
the hydraulic drive butterfly valve (17) and the guide blades of the air compressor share one hydraulic mechanism, and the electric valve (16) is electrically connected with an electronic controller of the engine.
6. The dual flow path air entraining admixture anti-icing assembly of claim 1,
when the aircraft engine adopts a combined compressor, the air-entraining position of the first air-entraining pipe (11) is placed at the downstream of the outlet of the centrifugal impeller, and the inducing position of the second air-entraining pipe (12) is placed in front of the inlet of the centrifugal impeller and behind the outlet of the axial compressor;
When the aircraft engine adopts a full axial-flow compressor, the air-entraining position of the first air-entraining pipe (11) is placed at a certain stage of 70% -100% compressor stage, and the inducing position of the second air-entraining pipe (12) is placed at a certain stage of 40% -70% compressor stage.
7. The dual flow path air entraining admixture anti-icing assembly of claim 1,
the electric valve (16) is arranged upstream of the hydraulically driven butterfly valve (17).
8. The dual flow path air entraining admixture anti-icing assembly of claim 2,
the aperture of the throttling hole (14) is 1.5 mm-5 mm, and the inclination angle is 10-45 degrees.
9. A double-flow-path air-entraining blending anti-icing method is characterized in that the double-flow-path air-entraining blending anti-icing device as claimed in any one of claims 1 to 8 is adopted, and the method comprises the following steps:
step S1: detecting whether an anti-icing function needs to be started or not by using an anti-icing detector on the airplane;
step S2: after the anti-icing detector detects that the anti-icing function needs to be started, the electric valve (16) is controlled to be opened, and the opening of the hydraulic drive butterfly valve (17) is adjusted according to the adjustment rule of the hydraulic mechanism;
step S3: and controlling the electric valve (16) to be closed after the anti-icing detector detects that the anti-icing function is not required to be started.
10. An aircraft engine, characterized in that a double flow path bleed air blending anti-icing arrangement as claimed in any one of claims 1 to 8 is employed.
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