CN115419526A - Engine air inlet channel anti-icing device for propeller-driven aircraft - Google Patents
Engine air inlet channel anti-icing device for propeller-driven aircraft Download PDFInfo
- Publication number
- CN115419526A CN115419526A CN202211052194.0A CN202211052194A CN115419526A CN 115419526 A CN115419526 A CN 115419526A CN 202211052194 A CN202211052194 A CN 202211052194A CN 115419526 A CN115419526 A CN 115419526A
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- Prior art keywords
- engine
- air inlet
- front edge
- smoke exhaust
- exhaust pipe
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- 239000000779 smoke Substances 0.000 claims abstract description 34
- 238000010438 heat treatment Methods 0.000 claims description 32
- 238000004519 manufacturing process Methods 0.000 claims description 23
- 239000007789 gas Substances 0.000 claims description 21
- 239000000463 material Substances 0.000 claims description 3
- 229910052755 nonmetal Inorganic materials 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 7
- 230000008020 evaporation Effects 0.000 description 3
- 238000001704 evaporation Methods 0.000 description 3
- 239000002912 waste gas Substances 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000004020 conductor Substances 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/02—Air cleaners
- F02M35/08—Air cleaners with means for removing dust, particles or liquids from cleaners; with means for indicating clogging; with by-pass means; Regeneration of cleaners
- F02M35/088—Water, snow or ice proofing; Separation or drainage of water, snow or ice
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M35/00—Combustion-air cleaners, air intakes, intake silencers, or induction systems specially adapted for, or arranged on, internal-combustion engines
- F02M35/10—Air intakes; Induction systems
- F02M35/10242—Devices or means connected to or integrated into air intakes; Air intakes combined with other engine or vehicle parts
- F02M35/10268—Heating, cooling or thermal insulating means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention relates to the technical field of airplane power devices, in particular to an anti-icing device for an engine air inlet channel of a propeller airplane, which comprises an engine and an engine smoke exhaust pipe assembly, wherein the engine smoke exhaust pipe assembly is arranged on the outer wall of the engine and comprises a left smoke exhaust pipe and a right smoke exhaust pipe which are fixed on the outer walls of two ends of the engine; the bleed air pipe assembly is used for transferring heat of the exhaust gas of the engine; the front edge of the air inlet passage of the airplane engine is heated in real time by hot air in the engine smoke exhaust pipe, so that the front edge of the air inlet passage is prevented from being iced, the structure is simple, i.e. no additional operation is required by a pilot, no maintenance is required by ground staff, the safety index of various propeller airplanes in severe weather can be effectively improved, and the flight safety is ensured.
Description
Technical Field
The invention relates to the technical field of airplane power devices, in particular to an anti-icing device for an engine air inlet channel of a propeller airplane.
Background
When the airplane flies in a specific meteorological environment, the part of the airplane facing the wind and with small curvature radius can collide with water drops in the atmosphere to be gathered and frozen. The investigation of a large number of flight accidents shows that the icing of the key parts of the airplane can cause the lift force of the airplane to fall, the resistance to rise and the operation performance of the airplane to be reduced. The icing of the air inlet of the engine destroys the aerodynamic appearance of the air inlet, reduces the air quantity entering the engine, and causes the power of the engine to be reduced. In order to ensure the thrust of the engine, the pilot mostly increases the oil supply quantity of the engine, so that the fuel consumption is increased, the service life of the engine is shortened, and even faults such as air parking and the like can occur.
At present, the common deicing or anti-icing method for the air inlet of the aircraft engine comprises the following steps:
1. electrothermal ice/ice removal
Heating elements are pre-embedded in the front edge of the air inlet of the engine, so that the anti-icing function can be realized by continuous heating, and the deicing function can be realized by periodic heating.
2. Hot gas deicing/anti-icing
Hot gas de-icing/anti-icing may be divided into hot air and engine exhaust de-icing/anti-icing according to air supply
a) Hot air anti-icing: the surface temperature of the front edge of the engine air inlet channel reaches the evaporation temperature of the supercooled water drops under icing conditions through the hot air, so that the supercooled water drops are prevented from icing at the surface temperature.
b) Deicing of engine exhaust gas: the engine exhaust pipe is provided with an air collecting hole, a hot air collecting device, an air collecting pipe and the like, engine exhaust gas can be introduced into an engine air inlet channel with a sandwich layer under the control of the hot air collecting device, and the air inlet channel is heated through the engine exhaust gas, so that deicing is realized.
In the method, the electrothermal deicing is suitable for airplanes which cannot provide hot air, but the heating element of the electrothermal deicing system needs to be pre-embedded into an engine air inlet in advance, and the maintenance work is complex when the conducting wire and the heating element are damaged.
For most propeller aircrafts, the air source for hot air anti-icing comes from engine bleed air, the bleed air control is complex, the efficiency is not high, and the performance of the engine is reduced. The engine waste gas deicing device controls waste gas to enter an engine air inlet channel with an interlayer through the hot gas collecting device, deicing operation is achieved, the device needs a pilot to manually operate the hot gas collecting device through a transmission mechanism in a cockpit, the transmission mechanism is complex, meanwhile, no icing detection mechanism exists, the pilot cannot accurately judge the time for switching on the switching-on mechanism, and the deicing effect is poor.
Disclosure of Invention
The invention aims to provide an anti-icing device for an engine air inlet of a propeller plane, which solves the problems in the background technology.
The technical scheme of the invention is as follows: an anti-icing device for an engine inlet passage for a propeller-driven aircraft comprises an engine and a power unit, wherein the engine inlet passage comprises a first engine and a second engine;
the engine smoke exhaust pipe assembly is arranged on the outer wall of the engine and comprises a left smoke exhaust pipe and a right smoke exhaust pipe which are fixed on the outer walls of two ends of the engine;
the bleed air pipe assembly is used for transmitting heat of the waste gas of the engine;
the engine air inlet leading edge assembly is connected with the engine smoke exhaust pipe assembly and the engine air inlet leading edge assembly respectively in a rigid sealing mode.
Preferably, an air inlet channel is arranged on the outer wall of one end of the engine.
Preferably, the engine air inlet leading edge assembly comprises an engine air inlet leading edge fixed on the outer wall on one side of the air inlet.
Preferably, the outer wall of one side of the front edge of the engine air inlet is spliced with two heating pipes of the front edge of the engine air inlet, and a non-metal heat conduction material is filled between the heating pipes of the front edge of the engine air inlet and the front edge of the engine air inlet.
Preferably, engine air inlet front edge heating pipe is installed to engine air inlet front edge heating pipe one end outer wall, and engine air inlet front edge heating pipe other end installs engine air inlet front edge heating pipe joint.
Preferably, the bleed pipe subassembly includes left gas production pipe subassembly and right gas production pipe subassembly, and left gas production pipe subassembly and right gas production pipe subassembly both ends respectively with left exhaust pipe, right exhaust pipe and engine intake duct leading edge heating pipe joint outer wall fixed connection, left gas production pipe subassembly and right gas production pipe subassembly are fixed on the engine through the fixed clamp of gas production pipe.
The invention provides an anti-icing device for an engine air inlet channel of a propeller aircraft through improvement, and compared with the prior art, the anti-icing device has the following improvements and advantages:
the invention utilizes hot gas in the engine smoke exhaust pipe to heat the front edge of the air inlet passage of the aircraft engine in real time, realizes the anti-icing of the front edge of the air inlet passage, has simple structure, does not need additional operation of a pilot, does not need maintenance of ground staff, can effectively improve the safety index of various propeller aircrafts in severe weather, and ensures the flight safety.
Drawings
The invention is further explained below with reference to the figures and examples:
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic view of the left smoke exhaust duct structure of the present invention;
FIG. 3 is a schematic view of the right smoke exhaust pipe of the present invention;
FIG. 4 is a schematic view of an engine air intake leading edge assembly of the present invention.
Description of reference numerals:
1. an engine exhaust pipe assembly; 1-1, a left smoke exhaust pipe; 1-2, a right smoke exhaust pipe; 2. a bleed duct assembly; 3. an engine air intake leading edge assembly; 3-1, leading edge of engine inlet; 3-2, heating pipes at the front edge of an air inlet of the engine; 3-3, heating pipes at the front edge of an air inlet of the engine; 3-4, heating a pipe joint at the front edge of an air inlet of the engine; a. an engine; b. fixing a hoop for a gas production pipe; c. an air inlet channel; d. a non-metallic heat conducting material.
Detailed Description
The present invention is described in detail below, and technical solutions in the embodiments of the present invention are clearly and completely described, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides an anti-icing device for an engine air inlet channel of a propeller aircraft through improvement, and the technical scheme of the invention is as follows:
as shown in fig. 1-4, an anti-icing device for an inlet duct of an engine for a propeller-driven aircraft comprises an engine a and a fan;
the smoke exhaust pipe assembly 1 of the engine is arranged on the outer wall of the engine a, the smoke exhaust pipe assembly 1 of the engine comprises a left smoke exhaust pipe 1-1 and a right smoke exhaust pipe 1-2 which are fixed on the outer walls of two ends of the engine a, a gas production pipe in the smoke exhaust pipe assembly 1 of the engine adopts a reverse gas inlet mode and is arranged in an arc shape, the resistance of the smoke exhaust pipe of the engine is reduced as much as possible, and the normal work of the engine is ensured;
the bleed air pipe assembly 2 is used for transferring the heat of the exhaust gas of the engine a and transferring the heat of the exhaust gas of the engine into the front edge assembly 3 of the air inlet channel of the engine;
the engine air inlet leading edge assembly 3 is characterized in that the air entraining pipe assembly 2 is respectively connected with the engine smoke exhaust pipe assembly 1 and the engine air inlet leading edge assembly 3 in a rigid sealing mode, and the engine air inlet leading edge assembly 3 is of a closed sandwich structure.
Furthermore, an air inlet duct c is arranged on the outer wall of one end of the engine a.
Further, the engine inlet leading edge assembly 3 comprises an engine inlet leading edge 3-1 fixed on the outer wall of one side of the inlet c.
Furthermore, two engine air inlet front edge heating pipes 3-2 are inserted into the outer wall of one side of the engine air inlet front edge 3-1, and a non-metal heat conduction material d is filled between the engine air inlet front edge heating pipe 3-2 and the engine air inlet front edge 3-1, so that the surface temperature of the engine air inlet front edge 3-1 reaches the evaporation temperature of the supercooled water drops under the icing condition, and the supercooled water drops are prevented from being frozen at the position.
Further, the outer wall of one end of the engine air inlet leading edge heating pipe 3-2 is provided with the engine air inlet leading edge heating pipe 3-3, and the other end of the engine air inlet leading edge heating pipe 3-3 is provided with the engine air inlet leading edge heating pipe joint 3-4.
Furthermore, the air guide pipe assembly 2 comprises a left air production pipe assembly and a right air production pipe assembly, two ends of the left air production pipe assembly and two ends of the right air production pipe assembly are fixedly connected with the outer walls of the left smoke exhaust pipe 1-1, the right smoke exhaust pipe 1-2 and the heating pipe joint 3-4 at the front edge of the air inlet of the engine respectively, and the left air production pipe assembly and the right air production pipe assembly are fixed on the engine a through an air production pipe fixing clamp b.
The working principle is as follows: the engine smoke exhaust pipe assembly 1 discharges hot smoke through the left smoke exhaust pipe 1-1 and the right smoke exhaust pipe 1-2, and the surface temperature of the front edge 3-1 of the engine air inlet channel reaches the evaporation temperature of supercooled water drops under the icing condition through the front edge heating pipe joint 3-4 of the engine air inlet channel, the front edge heating pipe 3-3 of the engine air inlet channel and the front edge heating pipe 3-2 of the engine air inlet channel penetrating through the front edge 3-1 of the engine air inlet channel, so that the supercooled water drops are prevented from being iced at the position.
Claims (6)
1. An anti-icing device of an engine inlet channel for a propeller-driven aircraft comprises an engine (a) and is characterized by also comprising a power unit, a power unit and a power unit, wherein the power unit is connected with the engine;
the engine smoke exhaust pipe assembly (1) is arranged on the outer wall of the engine (a), and the engine smoke exhaust pipe assembly (1) comprises a left smoke exhaust pipe (1-1) and a right smoke exhaust pipe (1-2) which are fixed on the outer walls of two ends of the engine (a);
a bleed air pipe assembly (2) for heat transfer from exhaust gases of the engine (a);
the engine air inlet leading edge assembly (3) and the air guide pipe assembly (2) are respectively connected with the engine smoke exhaust pipe assembly (1) and the engine air inlet leading edge assembly (3) in a rigid sealing mode.
2. The inlet scoop ice protection device of an engine for a propeller aircraft as defined in claim 1, wherein: and an air inlet (c) is arranged on the outer wall of one end of the engine (a).
3. The inlet scoop ice protection device of an engine for a propeller aircraft as defined in claim 1, wherein: the engine air inlet duct leading edge assembly (3) comprises an engine air inlet duct leading edge (3-1) fixed on the outer wall of one side of the air inlet duct (c).
4. The inlet scoop ice protection device of an engine for a propeller aircraft as claimed in claim 3, wherein: two engine air inlet front edge heating pipes (3-2) are spliced on the outer wall of one side of the engine air inlet front edge (3-1), and a non-metal heat conduction material (d) is filled between the engine air inlet front edge heating pipes (3-2) and the engine air inlet front edge (3-1).
5. The inlet scoop ice protection device of an engine for a propeller aircraft as defined in claim 4, wherein: an engine air inlet front edge heating pipe (3-3) is installed on the outer wall of one end of the engine air inlet front edge heating pipe (3-2), and an engine air inlet front edge heating pipe joint (3-4) is installed at the other end of the engine air inlet front edge heating pipe (3-3).
6. The inlet scoop ice protection device of an engine for a propeller aircraft as defined in claim 1, wherein: the air guide pipe assembly (2) comprises a left air production pipe assembly and a right air production pipe assembly, two ends of the left air production pipe assembly and two ends of the right air production pipe assembly are fixedly connected with the outer walls of a left smoke exhaust pipe (1-1), a right smoke exhaust pipe (1-2) and an engine air inlet front edge heating pipe joint (3-4) respectively, and the left air production pipe assembly and the right air production pipe assembly are fixed on an engine (a) through an air production pipe fixing clamp (b).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211052194.0A CN115419526A (en) | 2022-08-30 | 2022-08-30 | Engine air inlet channel anti-icing device for propeller-driven aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211052194.0A CN115419526A (en) | 2022-08-30 | 2022-08-30 | Engine air inlet channel anti-icing device for propeller-driven aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115419526A true CN115419526A (en) | 2022-12-02 |
Family
ID=84199484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211052194.0A Pending CN115419526A (en) | 2022-08-30 | 2022-08-30 | Engine air inlet channel anti-icing device for propeller-driven aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115419526A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101952171A (en) * | 2007-12-28 | 2011-01-19 | 空中巴士运作简易股份有限公司 | Aircraft propulsion assembly comprising hot air bleed systems |
| CN102182559A (en) * | 2011-05-04 | 2011-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Anti-icing passage system with functions of precooling and backheating |
| CN104727945A (en) * | 2015-01-30 | 2015-06-24 | 江苏中陆航星航空工业有限公司 | De-icing system of aircraft engine inlet |
-
2022
- 2022-08-30 CN CN202211052194.0A patent/CN115419526A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101952171A (en) * | 2007-12-28 | 2011-01-19 | 空中巴士运作简易股份有限公司 | Aircraft propulsion assembly comprising hot air bleed systems |
| CN102182559A (en) * | 2011-05-04 | 2011-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Anti-icing passage system with functions of precooling and backheating |
| CN104727945A (en) * | 2015-01-30 | 2015-06-24 | 江苏中陆航星航空工业有限公司 | De-icing system of aircraft engine inlet |
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