CN108688824A - Engine intake deicing system, internal combustion engine and aircraft - Google Patents
Engine intake deicing system, internal combustion engine and aircraft Download PDFInfo
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- CN108688824A CN108688824A CN201710228766.9A CN201710228766A CN108688824A CN 108688824 A CN108688824 A CN 108688824A CN 201710228766 A CN201710228766 A CN 201710228766A CN 108688824 A CN108688824 A CN 108688824A
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- 238000002485 combustion reaction Methods 0.000 title claims description 17
- 238000010438 heat treatment Methods 0.000 claims description 45
- 238000001514 detection method Methods 0.000 claims description 35
- 230000008859 change Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 230000008014 freezing Effects 0.000 description 4
- 238000007710 freezing Methods 0.000 description 4
- 239000007769 metal material Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000000428 dust Substances 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 239000003643 water by type Substances 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filtering Of Dispersed Particles In Gases (AREA)
- Filtering Materials (AREA)
Abstract
A kind of engine intake deicing system provided by the invention, wherein, the deicing system includes allowing air into the filter mantle of the engine intake, and the intrinsic frequency of the filter mantle tool is more than or equal to the vibration frequency of the engine when engine idling and is less than or equal to 150% of the vibration frequency of engine when 100% rotating speed of engine.Above-mentioned engine intake deicing system, with the filter mantle for allowing air into engine intake, the intrinsic frequency of filter mantle be more than or equal to engine idling when engine vibration frequency and less than or equal to 100% rotating speed of engine when engine vibration frequency 150%, when filter mantle freezes, filter mantle can generate resonance with engine, and the amplitude of filter mantle can become larger when resonance, and the ice sheet condensed on filter bowl vibration is fallen, achieve the purpose that deicing, does not reduce the gross efficiency of engine.
Description
Technical Field
The invention relates to the technical field of deicing of internal combustion engines, in particular to an engine air inlet deicing system, an internal combustion engine and an aircraft.
Background
In helicopters, operating in cold and high humidity environments, for example on mountains or close to waters, icing can occur on the protective grille of the engine intake, and the amount of ice accumulated can locally block the intake of the gas turbine, possibly causing complete or partial damage to the gas turbine.
The principle of a conventional de-icing system is to direct a portion of the compressed air from the outlet of the compressor to the engine air intake to heat and de-ice the area of the engine air intake. The main drawback of such de-icing systems is that they take up a lot of the thermodynamic cycle energy of the gas turbine engine, reducing the overall efficiency of the engine.
In addition, because the compressed air is rapidly expanded when it is introduced into the engine intake, it absorbs heat or its temperature is reduced, resulting in inefficient heating of the engine intake area. Meanwhile, when the air inlet of the engine is seriously iced, the air inflow is reduced, the outlet of the compressor cannot provide enough hot air capable of deicing at the moment, and the helicopter can only select to land on the ground to perform deicing operation.
Disclosure of Invention
In view of the above, there is a need for a new engine intake deicing system, an internal combustion engine and an aircraft, which addresses the technical problem of reduced overall engine efficiency by deicing the engine intake with compressed hot air.
The invention provides an engine air inlet deicing system, which comprises a filter cover of an engine air inlet, wherein the filter cover has a natural frequency which is more than or equal to the vibration frequency of the engine when the engine is idling and less than or equal to 150% of the vibration frequency of the engine when the engine rotates at 100%.
In one embodiment, the natural frequencies include an mth order natural frequency and an nth order natural frequency,
the mth order natural frequency is greater than or equal to the vibration frequency of the engine when the engine is idling and is less than or equal to the vibration frequency of the engine when the engine rotates at 100 percent;
the nth order natural frequency is equal to or higher than the vibration frequency of the engine when the engine is cruising and equal to or lower than 150% of the vibration frequency of the engine when the engine is rotating at 100%.
In one embodiment, the mth order natural frequency is 75% of the vibration frequency of the engine at 100% engine speed;
the nth order natural frequency is 105% of the vibration frequency of the engine at 100% of the engine speed.
In one embodiment, the deicing system further comprises a heating device for heating the filter hood.
In one embodiment, the heating device comprises a heating ring, and the heating ring is matched with the filter cover and fixedly arranged on the filter cover.
In one embodiment, the heating ring comprises a resistance wire and a heat conducting insulating layer wrapped outside the resistance wire.
In one embodiment, the deicing system further comprises a detection device and a control device, the detection device is used for detecting the vibration state of the filter cover, and the control device is in signal connection with the detection device and obtains the state information of the filter cover according to the vibration state signal detected by the detection device.
In one embodiment, the detection device is elastically connected with the filter cover.
The invention also provides an internal combustion engine, wherein the internal combustion engine comprises the deicing system.
The invention also provides an aircraft, wherein the aircraft comprises the internal combustion engine.
The engine air inlet deicing system is provided with the filter cover allowing air to enter the engine air inlet, the natural frequency of the filter cover is more than or equal to the vibration frequency of the engine when the engine is idling and less than or equal to 150% of the vibration frequency of the engine when the engine rotates at 100%, when the filter cover is frozen, the filter cover can resonate with the engine, the amplitude of the filter cover is increased when the filter cover is resonated, and the ice layer condensed on the filter cover is vibrated, so that the deicing purpose is achieved; in addition, the total efficiency of the engine is not reduced, and energy is saved.
Drawings
In order to more clearly illustrate the embodiments of the present application or technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
FIG. 1 is a schematic illustration of the engine air intake de-icing system of the present invention;
FIG. 2 is a cross-sectional partial view of the engine air intake de-icing system of FIG. 1;
FIG. 3 is an intake schematic of the engine intake de-icing system of FIG. 2;
FIG. 4 is a schematic structural diagram of another embodiment of an engine air intake de-icing system of the present invention;
wherein,
100-engine air intake; 110-a supportable member; 200-a filter mantle; 300-a heating ring; 400-an elastic connector; 500-detection device.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the engine intake port deicing system, the internal combustion engine and the aircraft of the present invention are further described in detail by the embodiments in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 1 to 3, an engine air inlet deicing system according to an embodiment of the present invention includes a filter cover 200, a heating device, an elastic connector 400, a detection device 500, and a control device (not shown). The filter cover 200 covers the engine air inlet 100, the heating device is arranged on the filter cover 200, the detection device 500 is elastically connected with the filter cover 200 through the elastic connecting piece 400, and the control device is in signal connection with the detection device 500.
An internal combustion engine, such as a gas turbine engine, is provided with a filter housing 200 on an engine intake 100. The filter housing 200 is provided over the engine intake port 100 to prevent foreign matter from entering the engine. Further, the natural frequency of the filter cover 200 of the present invention is equal to or higher than the vibration frequency of the engine at the idling speed of the engine and equal to or lower than 150% of the vibration frequency of the engine at the 100% rotation speed of the engine. When the engine is in a mountain or a cold and high-humidity environment close to a water bath, the filter cover 200 is frozen, so that the natural frequency of the filter cover 200 falls within a range capable of generating resonance with the engine, and the filter cover can generate resonance with the engine. When the filter cover 200 resonates with the engine, the filter cover 200 will vibrate to remove the ice layer on the filter cover automatically, and the ice removing system will not consume the energy of the internal combustion engine and will remove the dust and other foreign matters from the filter cover 200.
For example, the natural frequency of the filter sock 200 may be equal to the frequency of vibration of the engine at 100% engine speed. When the engine runs at 100% of the rotating speed, the vibration frequency of the filter cover 200 is equal to that of the engine, the filter cover 200 and the engine generate resonance, and the amplitude of the filter cover 200 is increased during resonance, so that the ice layer condensed on the filter cover 200 can be prevented from being condensed, and the ice layer condensed on the filter cover 200 can be vibrated, so that the deicing purpose is achieved.
As another example, the natural frequency of the filter sock 200 may be slightly greater than the vibration frequency of the engine at 100% engine speed, for example, the natural frequency of the filter sock 200 may be 150% of the vibration frequency of the engine at 100% engine speed. When the engine runs at 100% of the rotating speed, if the filter cover 200 does not have the condensed ice layer, the vibration frequency of the filter cover 200 is not equal to that of the engine, and resonance cannot be generated; if a condensed ice layer is formed on the filter cover 200, the weight of the filter cover 200 is increased due to the ice layer, the vibration frequency of the filter cover 200 is reduced, when the vibration frequency of the filter cover 200 is reduced to be equal to the vibration frequency of the engine when the engine rotates at 100%, the filter cover 200 and the engine generate resonance, the vibration amplitude of the filter cover 200 is large during resonance, the condensed ice layer on the filter cover 200 can be vibrated, and accordingly deicing is achieved; when the ice layer condensed on the filter cage 200 is shaken off, the weight of the filter cage 200 is reduced and is restored to the natural frequency of the filter cage 200, and the filter cage 200 and the engine will not resonate any more. By setting the natural frequency of the filter cover 200 to be slightly greater than the vibration frequency of the engine when the engine rotates at 100% of the rotation speed, resonance is avoided when the filter cover 200 is not frozen, connection looseness between the filter cover 200 and the engine air inlet 100 caused by overlarge amplitude is prevented, resonance is generated when the filter cover 200 is frozen to a certain degree, an ice layer condensed on the filter cover 200 is removed in time, and blockage of the air inlet of the transmitter is avoided, so that performance reduction or partial damage of the engine is caused.
As another example, the natural frequency of the filter sock 200 may be slightly less than the vibration frequency of the engine at 100% engine speed, for example, the natural frequency of the filter sock 200 may be 90% of the vibration frequency of the engine at 100% engine speed. The engine is not always operated at 100%, for example, the engine may be often operated at 85% or 90% of the engine speed, when the vibration frequency of the filter cover 200 is equal to or slightly higher than the vibration frequency of the engine during operation, the filter cover 200 can resonate with the engine or the filter cover 200 can resonate with the engine after being frozen, so that a larger amplitude can be formed by the resonance to perform deicing.
The natural frequency of the filter sock 200 when not frozen is not equal to the vibration frequency of the engine at idle, cruise, or 100% speed, optionally at a frequency above 10%, to avoid resonance of the filter sock 200, which would affect the performance of the engine.
As an alternative embodiment, the natural frequency has an mth order natural frequency and an nth order natural frequency, and the mth order natural frequency may be greater than or equal to the vibration frequency of the engine when the engine is idling and less than or equal to the vibration frequency of the engine when the engine is at 100% of the rotation speed; the nth order natural frequency may be equal to or higher than a vibration frequency of an engine when the engine is cruising and equal to or lower than a vibration frequency of 150% of the vibration frequency of the engine at 100% of a rotation speed of the engine.
Specifically, the filter housing 200 is made of a metal material, which may be a metal material that satisfies the strength requirement of the filter housing 200. For certain metal materials with confirmed Young's modulus, the natural frequency of the filter cage 200 can be set by adjusting the thickness of the filter cage 200, and further, the m-th order natural frequency and the n-th order natural frequency of the filter cage 200 can be set by adjusting the thickness of the filter cage 200. For example, the material and corresponding configuration of the filter sock 200 may be determined by calculation and experimentation.
For example, engines used in helicopters typically include three primary operating states, take-off, cruise, and idle. If the engine is operated at 100% speed at takeoff, 90% speed at cruise and 60% speed at idle, the filter sock 200 may be set to have an mth order natural frequency that is 60% to 100%, such as 75%, of the vibration frequency of the engine at 100% speed, and an nth order natural frequency that is 90% to 150%, such as 105%, of the vibration frequency of the engine at 100% speed.
When the helicopter is in an air cruising working state, the rotating speed of the engine is 90%, if the filter cover 200 is frozen, the weight of the filter cover 200 is increased due to the existence of the ice layer, the filter cover 200 starts to be reduced from the nth order natural frequency, when the freezing degree is gradually increased, along with the increase of the weight of the ice layer, the vibration frequency of the filter cover 200 is reduced to be equal to the frequency of 90% of the rotating speed of the engine, the filter cover 200 and the engine generate resonance, the vibration amplitude of the filter cover 200 is increased during the resonance, and the ice layer condensed on the filter cover 200 can be vibrated, so that the deicing is realized; when the ice layer condensed on the filter cage 200 is vibrated away, the weight of the filter cage 200 is reduced, the vibration frequency of the filter cage 200 is restored to the nth-order natural frequency of the filter cage 200, and the filter cage 200 and the engine do not resonate with each other.
When the takeoff working state or cruise working state of the helicopter is converted with the idling working state, the rotating speed of the engine is converted from 100% rotating speed or 90% rotating speed to 60% rotating speed, the engine passes 75% rotating speed in the conversion process, when the engine passes 75% rotating speed, the rotating speed is equal to the mth order natural frequency of the filter cover 200, at the moment, the filter cover 200 will resonate, and a large amplitude is generated through the resonance, so that foreign matters such as ice layers or dust on the filter cover 200 are vibrated.
As an alternative embodiment, the engine intake de-icing system of the present invention may be provided with a heating device disposed on the filter sock 200 for heating the filter sock 200. When the engine is not started, the engine and the filter cover 200 cannot resonate, and the air inlet cannot be deiced, at the moment, the filter cover 200 can be heated by the heating device, the ice layer condensed on the filter cover 200 is melted by the heat energy generated by heating, and the filter cover 200 is assisted to deice in a resonant deicing mode, so that the deicing system can achieve the deicing purpose in each working state. When the engine is in operation, if the icing degree is heavy, the ice can not be well removed through the resonance of the filter cover 200, at the moment, the heating device can be started, the filter cover 200 is heated, so that the joint of the ice layer and the filter cover 200 is melted, the resonance ice removal effect of the filter cover 200 can be improved, the filter cover 200 is assisted to remove the ice, and the ice removal effect is further improved. In addition, the auxiliary heating device may be activated to heat the filter sock 200 when the filter sock 200 starts to resonate, so that the junction of the ice layer and the filter sock 200 is melted, and the ice layer is more easily removed by the filter sock 200.
Further, the heating device is provided with a heating ring 300, the heating ring 300 is matched with the filter housing 200 and is fixedly arranged on the filter housing 200, and the number of the heating rings 300 can be one, two or more. The strength of the filter cage 200 can be enhanced by the heating ring 300 to prevent damage to the filter cage 200 due to freezing or vibration. Still further, the heating ring 300 is provided with a resistance wire and a heat conducting insulating layer wrapped outside the resistance wire. The heating ring 300 can enhance the strength of the filter housing 200 and also heat the filter housing 200. Of course, in different embodiments, the strength enhancing and heating effects may be achieved by different means, such as using the heating ring 300 to enhance the strength of the filter cap 200 and using an electric heating means to heat the filter cap 200.
As an alternative embodiment, the engine intake de-icing system of the present invention may further be provided with a detection device 500, the detection device 500 being configured to detect a vibration state of the filter sock 200, the vibration state being visually displayed as a vibration waveform, including a vibration frequency and an amplitude. In particular, the detection device 500 may be a load cell, and in other embodiments, the detection device 500 may also be a gravity sensor or a vibration sensor. The detection device 500 is secured to the supportable member 110 adjacent the air inlet and is coupled to the filter housing 200. Optionally, the supportable member 110 is an extension of the air inlet wall. Each order of fixed frequency corresponds to one vibration state, different vibration frequencies will generate different vibration states, and the amplitude of the vibration state will increase when resonance occurs. The engine air inlet deicing system is further provided with a control device, the control device obtains the state information of the filter cover 200 according to the waveform and the waveform change detected by the detection device 500, that is, the state information of whether the filter cover 200 is frozen or not, whether the filter cover 200 generates resonance or not and the like can be obtained, and further, corresponding measures can be taken according to the state information, such as feeding back a freezing signal, controlling and starting a heating device and the like.
For example, the nth order natural frequency of the filter cover 200 is 105% of the vibration frequency of the engine at 100% engine speed.
When the filter housing 200 is not frozen, the filter housing 200 vibrates at the nth order natural frequency, the detection device 500 detects the corresponding nth order natural frequency vibration state, and the control device obtains the information that the filter housing is not frozen;
when the filter housing 200 is frozen, the weight of the filter housing 200 is increased, the vibration frequency of the filter housing 200 is reduced, the detection device 500 detects the corresponding vibration state and waveform change, and the control device can obtain the freezing information of the filter housing 200 according to the detection device 500;
when the ice is frozen to a certain degree, the vibration frequency of the filter cover 200 is reduced to be equal to the vibration frequency of the engine, the filter cover 200 and the engine generate resonance, the detection device 500 detects the corresponding vibration state, waveform change and amplitude change, and the control device can obtain the ice removing information of the filter cover 200 according to the detection device 500;
after the ice layer of the filter cover 200 is removed, the vibration frequency of the filter cover 200 is restored to the natural frequency, the filter cover 200 and the engine do not resonate any more, the detection device 500 detects the corresponding vibration state, waveform change and amplitude change, and the control device can obtain the deicing completion information of the filter cover 200 according to the detection device 500.
Further, when the control device obtains the information about the icing of the filter cover 200 or the information about the deicing of the filter cover 200 according to the detection device 500, the control device can control the heating device to start up, so as to heat the ice layer at the joint with the filter cover 200 through the heating device, thereby assisting the resonance effect of the filter cover 200 to improve the deicing effect of the deicing system. Accordingly, when the control device obtains the information of the completion of the deicing of the filter cap 200 through the detection device 500, the control device controls the heating device to be turned off, thereby saving energy when the deicing is not needed.
Further, the engine intake port deicing system of the present invention may be further provided with an elastic connector 400, and specifically, the elastic connector 400 may be a spring, and the elastic connector 400 may be one or more. One end of the elastic connector 400 is connected to the heating ring 300 or the filter housing 200, and the other end of the elastic connector 400 is connected to the supportable member 110, so that the frequency of the filter housing 200 can be better adjusted and the filter housing 200 can be prevented from being separated from the air inlet through the elastic connector 400.
Still further, the detection device 500 is elastically connected with the filter housing 200 through an elastic connection member 400, optionally, the detection device 500 is disposed on the supportable member 110 beside the engine air inlet 100, for example, two ends of the elastic connection member 400 are respectively connected with the detection device 500 and the filter housing 200; for another example, the two ends of the elastic connector 400 are respectively connected to the detection device 500 and the heating ring 300, and further connected to the filter housing 200 through the heating ring 300. The detection device 500 is connected with the filter cover 200 in an elastic connection mode, so that on one hand, the detection device 500 can better respond to the vibration of the filter cover 200 and detect the vibration state; on the other hand, the damage of the detection device 500 caused by the overlarge amplitude of the vibration or resonance of the filter cover 200 can be avoided.
Fig. 4 is a schematic structural diagram according to another embodiment of the present invention. The engine air inlet 100 is composed of symmetrical air inlet walls, and correspondingly, the filter housing 200 includes symmetrically arranged arc-shaped housing bodies, the arc-shaped housing bodies are respectively fixed on the air inlet walls, and the arc-shaped housing bodies are fixedly connected with each other to form the integral filter housing 200. Further, along the arc edge of the arc cover body, a heating device is arranged, the heating device is provided with an arc heating ring 300, and the heating ring 300 is composed of an arc resistance wire and a heat conduction insulating layer wrapped outside the resistance wire. The installation, maintenance and replacement of the filter mantle 200 and the heating device can be facilitated by the arc-shaped mantle body of the filter mantle 200 and the arc-shaped heating ring 300 of the heating device. The structure and thickness of the filter housing 200 are determined by calculation and experiment according to the natural frequency to be set.
As another broad aspect of the present invention, the present invention also provides an internal combustion engine provided at an intake port with an engine intake port deicing system as described above. In particular, the internal combustion engine may be a reciprocating internal combustion engine, a rotary piston engine, a free piston engine, a rotary vane gas turbine, a jet engine or the like, in particular a turbine engine, in particular an aeronautical gas turbine engine.
As another broad aspect of the present invention, there is also provided an aircraft comprising an internal combustion engine as described above.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. In contrast, when an element is referred to as being "directly on" another element, there are no intervening elements present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (10)
1. An engine intake de-icing system, characterized in that the de-icing system comprises a filter hood (200) of the engine intake (100), the natural frequency of the filter hood (200) being equal to or greater than the vibration frequency of the engine at idle speed of the engine and equal to or less than 150% of the vibration frequency of the engine at 100% of the engine speed.
2. Deicing system as claimed in claim 1, characterized in that the natural frequencies comprise a lower mth order natural frequency and a higher nth order natural frequency,
wherein m and n are positive integers, and m is less than n,
the mth order natural frequency is greater than or equal to the vibration frequency of the engine when the engine is idling and is less than or equal to the vibration frequency of the engine when the engine rotates at 100 percent;
the nth order natural frequency is equal to or higher than the vibration frequency of the engine when the engine is cruising and equal to or lower than 150% of the vibration frequency of the engine when the engine is rotating at 100%.
3. Deicing system as claimed in claim 2, characterized in that said mth order natural frequency is 75% of the vibration frequency of said engine at 100% of the speed of rotation of said engine;
the nth order natural frequency is 105% of the vibration frequency of the engine at 100% of the engine speed.
4. Deicing system according to claim 1, characterized in that it further comprises heating means for heating said filter hood (200).
5. Deicing system according to claim 4, characterized in that said heating means comprise a heating ring (300), said heating ring (300) being fitted with said filter hood (200) and being fixedly arranged on said filter hood (200).
6. Deicing system according to claim 5, characterized in that said heating ring (300) comprises a resistive wire and a thermally conductive insulating layer wrapped outside said resistive wire.
7. Deicing system according to any one of claims 1 to 6, characterized in that it further comprises a detection device (500) for detecting the vibration state of the filter hood (200), and a control device in signal connection with said detection device and deriving information on the state of the filter hood (200) from the vibration state signal detected by said detection device (500).
8. Deicing system according to claim 7, characterized in that it further comprises an elastic connector (400), said detection device (500) being connected to said filter hood (200) through said elastic connector (400).
9. An internal combustion engine, characterized in that it comprises a deicing system according to any one of claims 1 to 8.
10. An aircraft, characterized in that it comprises an internal combustion engine according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710228766.9A CN108688824B (en) | 2017-04-10 | 2017-04-10 | Engine air inlet deicing system, internal combustion engine and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710228766.9A CN108688824B (en) | 2017-04-10 | 2017-04-10 | Engine air inlet deicing system, internal combustion engine and aircraft |
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| Publication Number | Publication Date |
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| CN108688824A true CN108688824A (en) | 2018-10-23 |
| CN108688824B CN108688824B (en) | 2020-07-14 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111305953A (en) * | 2020-03-18 | 2020-06-19 | 中国商用飞机有限责任公司 | Method and device for automatically deicing fan blades of aviation turbofan engine |
| CN112324573A (en) * | 2020-10-29 | 2021-02-05 | 中国航发湖南动力机械研究所 | Aeroengine air inlet cover |
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