CN112455693A - Air interchanger for aerospace - Google Patents
Air interchanger for aerospace Download PDFInfo
- Publication number
- CN112455693A CN112455693A CN202011393019.9A CN202011393019A CN112455693A CN 112455693 A CN112455693 A CN 112455693A CN 202011393019 A CN202011393019 A CN 202011393019A CN 112455693 A CN112455693 A CN 112455693A
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- friction
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- 238000006073 displacement reaction Methods 0.000 claims abstract description 37
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 15
- 230000005540 biological transmission Effects 0.000 claims description 10
- 238000005096 rolling process Methods 0.000 claims description 4
- 238000009423 ventilation Methods 0.000 description 4
- 238000005452 bending Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000008602 contraction Effects 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Images
Classifications
-
- 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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
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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
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- Biodiversity & Conservation Biology (AREA)
- Environmental Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Toxicology (AREA)
- Pulmonology (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Separating Particles In Gases By Inertia (AREA)
Abstract
The invention provides an aerospace breather, which comprises a main body, a friction groove and a rotating ring, wherein the friction groove is arranged at an opening at the periphery of the middle part in the main body, and the rotating ring is embedded in the middle part of the friction groove; the main part is including receiving gas channel and air current channel, the friction groove is including the gomphosis piece, the displacement groove and receipts restraint ring, the gomphosis piece is including the roller bearing, the displacement groove is including receiving restraint groove and injecing the groove, receive restraint the ring including the combination piece, receive restraint displacement piece and extension piece, rotatory ring is including the gomphosis groove, the driving plate, rotatory groove mark and impact block, the device is provided with and receives the restraint ring, through receiving the restraint ring and producing its heat because the high-speed rotatory friction of the high-speed flow of air current impact and go out to distribute and prevent that it from leading to icing because the temperature is low excessively.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an aerospace ventilating device.
Background
Aviation refers to the navigation activity of an aircraft in the earth's atmosphere, and aerospace refers to the navigation activity of an aircraft in the space outside the atmosphere. Aerospace has greatly changed the structure of transportation. Aerospace ventilation is accomplished by air intake openings, air ducts, or similar openings, which collect air by forward movement of the aircraft, and direct the air to an engine or ventilator. The air replacement is carried out in the aircraft, so that the aircraft has an important structure in the flying process, and the inner wall of the air inlet can be frozen due to the high-speed flow of the airflow at the same time if the temperature of the air inlet is low when the air enters the air inlet, so that the air inlet has the influence on devices in the air inlet and the temperature of the air in the flying process.
Disclosure of Invention
The invention aims to solve the technical problem that when air flows into an interior at a high speed, the air inlet of the aerospace ventilation device freezes the inner wall of the aerospace ventilation device due to the fact that the temperature of the aerospace ventilation device is low and the air flow flows at the high speed.
The purpose and the effect of the air interchanger for aerospace are achieved by the following specific technical means:
an aerospace breather comprises a main body, a friction groove and a rotating ring, wherein the friction groove is arranged at an opening at the periphery of the middle part in the main body, and the rotating ring is embedded in the middle part of the friction groove;
the main body comprises an air receiving channel and an air flow channel, the air receiving channel is fixedly connected to the middle part of the inside of the main body, which is close to one end, and the air flow channel is fixedly connected to the middle part of the inside of the main body;
the friction groove comprises an embedded block, a displacement groove, a bundling ring and a discharge groove, the embedded block is fixedly connected to two sides of the middle of the friction groove, an opening of the displacement groove is formed in one side of the bottom end of the middle of the friction groove, the bundling ring is embedded and arranged around the middle of the displacement groove, and an opening of the discharge groove is formed in the bottom end of the middle of the friction groove;
the discharge groove comprises a flow limiting block, and the flow limiting block is fixedly connected to one side of the middle part of the bottom end of the discharge groove;
the embedded block comprises a rolling shaft, and the rolling shaft is embedded into one side of the embedded block;
the displacement groove comprises a bundling groove and a limiting groove, the bundling groove is fixedly connected to one side of the middle part of the displacement groove, and an opening of the limiting groove is formed in the surface of the bundling groove;
the beam-closing ring comprises a combination block, a beam-closing displacement block and extension blocks, the combination block is embedded around the beam-closing ring, the beam-closing displacement block is fixedly connected to the surface of the inner wall of the middle part of the combination block, and the extension blocks are embedded at two sides of the combination block;
the rotating ring comprises an embedded groove, a transmission plate, a rotating groove mark, an impact block and a water collecting hole, wherein the embedded groove is provided with an opening at two sides of the rotating ring, the transmission plate is fixedly connected to the bottom end of one side of the rotating ring, the rotating groove mark is fixedly connected to the surface of the top end of the transmission plate, the impact block is fixedly connected to the periphery of the surface of the top end of the rotating ring, and the water collecting hole is provided at the periphery of the middle part of the.
Further preferred embodiments: the friction groove is a rectangular groove with the arc-shaped inner wall in the middle of the airflow channel, and the groove is embedded with the rotating ring.
Further preferred embodiments: the tabling block is a long-hair-shaped convex block at the two sides of the middle part of the friction groove, and the convex block is tabled with the tabling grooves at the two sides of the rotating ring.
Further preferred embodiments: the rolling shaft is an embedded round shaft with one side of a lug of the embedding block in a cylindrical shape.
Further preferred embodiments: the beam-collecting groove is an inclined plane formed by obliquely arranging the bottom end of the displacement groove.
Further preferred embodiments: the limiting groove is a rectangular groove which is obliquely arranged on the surface of the bundling groove, rectangular open grooves are further arranged on two sides of the middle of the groove, and meanwhile the open grooves of the limiting groove are mutually embedded with the convex blocks on the surface of the rotating groove mark.
Further preferred embodiments: the combination block is a circular rectangular plate which is connected with each other through a plurality of extension blocks and is provided with a bending and inclining arrangement, and one side of the combination block which is attached to the bundling groove is an inclined plane which has an inclined angle with the bundling groove.
Further preferred embodiments: the impact block is a triangular convex block arranged on one side of the periphery of the surface of the rotating ring in an inclined arc mode.
Further preferred embodiments: the flow limiting block is a triangular lug which is bent and inclined from one side of the bottom end of the middle part of the discharge groove to the other side.
Has the advantages that:
(1) this kind of breather for aerospace is provided with and receives the collar, can rotate under rotatory ring's drive through receiving the collar, can remove to one side simultaneously and receive to make the rotational speed reduce to prevent that it from removing to lead to its high emergence of heat to warp wearing and tearing at the same position high-speed rotation.
(2) The device is provided with rotatory ring, can rotate through the flow of its air current when high-speed air current flows in into the main part through rotatory ring, drive its receipts in rotatory and restraint the ring and carry out spin friction and produce heat and make it prevent to lead to icing because the air current of main part is extremely low because of the temperature, will freeze the hole that fuses the back through its rotatory ring and discharge rivers in discharging the basin simultaneously, prevent that rivers from flowing into the inside of advancing the main part after fusing.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a schematic view of the overall partial cross-sectional structure of the present invention.
Fig. 3 is an enlarged schematic view of the structure at a in fig. 2 according to the present invention.
FIG. 4 is a partial overall structural view of the friction groove of the present invention.
Fig. 5 is an enlarged view of the structure at B in fig. 4 according to the present invention.
FIG. 6 is a schematic view of the overall structure of the confinement ring of the present invention.
In FIGS. 1-6: the device comprises a main body 1, an air collecting channel 101, an air flow channel 102, a friction groove 2, a fitting block 201, a roller 2011, a displacement groove 202, a beam collecting groove 2021, a limiting groove 2022, a beam collecting ring 203, a combination block 2031, a beam collecting displacement block 2032, an extension block 2033, a discharge groove 204, a flow limiting block 2041, a rotating ring 3, a fitting groove 301, a transmission plate 302, a rotating groove mark 303, an impact block 304 and a water collecting hole 305.
Detailed Description
As shown in figures 1 to 6:
an aerospace breather comprises a main body 1, a friction groove 2 and a rotating ring 3, wherein the friction groove 2 is arranged at an opening around the middle part of the interior of the main body 1, and the rotating ring 3 is embedded in the middle part of the friction groove 2;
the main body 1 comprises an air receiving channel 101 and an air flow channel 102, the air receiving channel 101 is fixedly connected to the middle part of the inside of the main body 1 near one end, and the air flow channel 102 is fixedly connected to the middle part of the inside of the main body 1;
the friction groove 2 comprises a tabling block 201, a displacement groove 202, a binding ring 203 and a discharge groove 204, the tabling block 201 is fixedly connected with two sides of the middle part of the friction groove 2, the opening of the displacement groove 202 is arranged at one side of the bottom end of the middle part of the friction groove 2, the binding ring 203 is embedded around the middle part of the displacement groove 202, and the opening of the discharge groove 204 is arranged at the bottom end of the middle part of the friction groove 2;
the discharge groove 204 comprises a flow limiting block 2041, and the flow limiting block 2041 is fixedly connected to one side of the middle of the bottom end of the discharge groove 204;
the embedded block 201 comprises a roller 2011, and the roller 2011 is embedded into one side of the embedded block 201;
the displacement groove 202 comprises a binding groove 2021 and a limiting groove 2022, the binding groove 2021 is fixedly connected to one side of the middle part of the displacement groove 202, and the opening of the limiting groove 2022 is arranged on the surface of the binding groove 2021;
the beam-receiving ring 203 comprises a combination block 2031, a beam-receiving displacement block 2032 and an extension block 2033, the combination block 2031 is embedded around the beam-receiving ring 203, the beam-receiving displacement block 2032 is fixedly connected to the surface of the inner wall of the middle part of the combination block 2031, and the extension block 2033 is embedded at two sides of the combination block 2031;
the rotating ring 3 comprises a tabling groove 301, a transmission plate 302, a rotating groove mark 303, an impact block 304 and a water collecting hole 305, wherein the tabling groove 301 is opened at two sides of the rotating ring 3, the transmission plate 302 is fixedly connected at the bottom end of one side of the rotating ring 3, the rotating groove mark 303 is fixedly connected at the top end surface of the transmission plate 302, the impact block 304 is fixedly connected at the periphery of the top end surface of the rotating ring 3, and the water collecting hole 305 is opened at the periphery of the middle part of the rotating.
The friction groove 2 is a rectangular groove with an arc-shaped inner wall in the middle of the air flow channel 102, and the groove is embedded with the rotating ring 3.
The engaging blocks 201 are long projections at both sides of the middle of the friction groove 2, and the projections are engaged with the engaging grooves 301 at both sides of the rotating ring 3, and the engaging grooves 301 at both sides are engaged with the engaging blocks 201 at both sides of the middle of the friction groove 2 to rotate when the rotating ring 3 rotates, so that the rotation is more stable and no deviation occurs.
The roller 2011 is a cylindrical embedded round shaft on one side of the projection of the embedded block 201, and the roller 2011 on one side of the embedded block 201 can roll through the roller 2011 to reduce friction when the rotating ring 3 rotates, so that the rotating ring can rotate more quickly and cannot be blocked.
The converging groove 2021 is an inclined surface formed by the bottom end of the slot of the displacement groove 202 being inclined.
The limiting groove 2022 is a rectangular groove formed by arranging the converging groove 2021 obliquely on the surface, and rectangular slots are formed on both sides of the middle of the groove, and the slot of the limiting groove 2022 is engaged with the protrusion on the surface of the converging displacement block 2032, so that when the converging ring 203 rotates around the converging groove 2021, the converging displacement block 2032 on the inner wall surface of the converging ring rotates along the inclination angle of the limiting groove 2022 due to the engagement between the converging displacement block 2032 and the limiting groove 2022.
The combination block 2031 is a circular rectangular plate with a curved and inclined arrangement and connected to each other by a plurality of extension blocks 2033, and the combination block 2031 is attached to one side of the convergence groove 2021 and is an inclined surface with a straight inclined angle, so that the combination blocks 2031 around the convergence ring 203 contract by the extension blocks 2033 when the convergence ring contracts due to the rotation movement, and simultaneously the extension blocks 2033 contract into grooves at two sides of the combination block 2031 to contract.
The impact block 304 is a triangular projection arranged on one side of the periphery of the surface of the rotating ring 3 in an inclined arc manner, when air enters the air flow channel 102, high-speed air flow can impact the impact block 304 on the surface of the rotating ring 3, and the flow and impact of the air flow can be guided through the radian and the groove of the inclined surface of the impact block 304, so that the rotating ring 3 is forced to rotate along the friction groove 2.
The flow limiting block 2041 is a triangular projection which is formed by bending and inclining the bottom end side of the middle of the discharge groove 204, and discharges water flow through the discharge groove 204 at the bottom end of the middle inside the friction groove 2, so that damage caused by the water flow flowing into the main body 1 after freezing and fusion is prevented.
The working principle is as follows:
the specific use mode and function of this embodiment are that, firstly, in the process of flying the airplane, the airflow is sucked into the air intake channel 102 from the air intake channel 101 of the main body 1, then the air is injected into the air exchange system through the air intake channel 102 to reduce the pressure of the air so as to replace the air inside, when the air enters the air intake channel 102, the high-speed airflow impacts the impact block 304 on the surface of the rotating ring 3, the flow and impact of the airflow can be guided through the radian and the groove of the inclined surface of the impact block 304, so that the rotating ring 3 is forced to rotate along the friction groove 2, when the rotating ring 3 rotates, the embedding grooves 301 on both sides of the rotating ring are embedded in the embedding blocks 201 on both sides of the middle of the friction groove 2 to rotate, so that the rotation is more stable and does not deviate, and simultaneously, the rollers 2011 on one side of the embedding blocks 201 can roll to reduce the friction so that the rotating ring rotates more quickly through the rollers 2011 when the rotating ring 3 rotates, so that the And will not be blocked, after the rotating ring 3 rotates, the driving plate 302 at one side will be embedded in the displacement slot 202 to rotate, when the driving plate 302 rotates in the displacement slot 202, the rotating slot mark 303 on the surface will be embedded with the slot mark embedded in the displacement slot 202 and connected with the surface of the tightening ring 203, so that it will drive the tightening ring 203 to rotate along the tightening slot 2021, when the tightening ring 203 rotates around the tightening slot 2021, because the tightening displacement block 2032 on the inner wall surface is embedded with the limiting slot 2022, it will rotate and move along the inclination angle of the limiting slot 2022, at the same time, through the inclination angle of the limiting slot 2022, the tightening ring 203 will be tightened when moving, so that it will be separated from the rotating ring 3 temporarily, and its rotation speed will be reduced to prevent its surface abrasion caused by the heat rising too fast due to continuous rotation friction, finally, when the ring 203 is contracted by the rotation movement, the surrounding combination blocks 2031 are contracted by the extension blocks 2033, and the extension blocks 2033 are contracted into the grooves on both sides of the combination block 2031, and when the extension blocks 2033 are contracted, because one ends of the extension blocks 2033 are connected to one end of the extension block 2033 on the other side by the spring, the springs are compressed when the ring is contracted, so that when the ring is contracted to one end of the groove 2021, the springs push the extension blocks 2033 outwards by the elasticity because of the reduction of the rotation speed of the ring, and when the ring is pushed, because the combination blocks 2031 are connected to the groove 2021 by the displacement block 2032, the ring can be extended only by the rotation, so that the ring 203 can be restored to be attached to one side of the ring 3 by the elasticity of the ring, such repeated contraction and movement friction heats the inner wall of the flow channel 102, while preventing its wear deformation due to its friction in the same place all the time, and the water after the ice condensed on the surface is melted by the heat generated by the rotation of the contraction ring 203 thereof flows into the inner center of the friction groove 2 through the water collection holes 305 on the surface of the rotation ring 3 thereof, the water flow is discharged by the discharge groove 204 at the bottom end of the middle part of the inner part of the friction groove 2, the damage caused by the water flow flowing into the inner part of the main body 1 after the ice is fused is prevented, and the flow restricting block 2041 at the bottom end of the discharge groove 204 thereof can guide the water flow to one side without flowing again to the surface of the main body 1 while discharging it by its curvature, while being able to reduce the movement by bending its arc is that the air flow impinges into the discharge slot 204 and obstructs the flow of the incoming water flow.
Claims (9)
1. The utility model provides an aerospace breather, includes main part (1), friction groove (2) and rotatory ring (3), its characterized in that: a friction groove (2) is formed in an opening in the periphery of the middle part of the interior of the main body (1), and a rotating ring (3) is embedded in the middle part of the friction groove (2);
the main body (1) comprises an air collecting channel (101) and an air flow channel (102), the air collecting channel (101) is fixedly connected to the middle part of the inside of the main body (1) close to one end, and the air flow channel (102) is fixedly connected to the middle part of the inside of the main body (1);
the friction groove (2) comprises an embedding block (201), a displacement groove (202), a binding ring (203) and a discharge groove (204), the embedding block (201) is fixedly connected to two sides of the middle of the friction groove (2), an opening of the displacement groove (202) is formed in one side of the bottom end of the middle of the friction groove (2), the binding ring (203) is embedded and arranged around the middle of the displacement groove (202), and an opening of the discharge groove (204) is formed in the bottom end of the middle of the friction groove (2);
the discharge groove (204) comprises a flow limiting block (2041), and the flow limiting block (2041) is fixedly connected to one side of the middle of the bottom end of the discharge groove (204);
the embedded block (201) comprises a roller (2011), and the roller (2011) is embedded into one side of the embedded block (201);
the displacement groove (202) comprises a bunching groove (2021) and a limiting groove (2022), the bunching groove (2021) is fixedly connected to one side of the middle part of the displacement groove (202), and an opening of the limiting groove (2022) is formed in the surface of the bunching groove (2021);
the beam-receiving ring (203) comprises a combination block (2031), a beam-receiving displacement block (2032) and an extension block (2033), the combination block (2031) is embedded around the beam-receiving ring (203), the beam-receiving displacement block (2032) is fixedly connected to the surface of the inner wall of the middle part of the combination block (2031), and the extension block (2033) is embedded at two sides of the combination block (2031);
the rotating ring (3) comprises a tabling groove (301), a transmission plate (302), a rotating groove mark (303), an impact block (304) and a water collecting hole (305), wherein the opening of the tabling groove (301) is formed in two sides of the rotating ring (3), the transmission plate (302) is fixedly connected to the bottom end of one side of the rotating ring (3), the rotating groove mark (303) is fixedly connected to the top end surface of the transmission plate (302), the impact block (304) is fixedly connected to the periphery of the top end surface of the rotating ring (3), and the opening of the water collecting hole (305) is formed in the periphery of the middle of the rotating ring (3).
2. An aerospace air exchange device according to claim 1, wherein: the friction groove (2) is a rectangular groove with the arc-shaped inner wall in the middle of the airflow channel (102), and the groove is embedded with the rotating ring (3).
3. An aerospace air exchange device according to claim 1, wherein: the tabling block (201) is a long-hair-shaped convex block at two sides of the middle part of the friction groove (2), and the convex block is tabled with the tabling groove (301) at two sides of the rotating ring (3).
4. An aerospace air exchange device according to claim 1, wherein: the rolling shaft (2011) is an embedded round shaft with a cylindrical shape at one side of a convex block of the embedded block (201).
5. An aerospace air exchange device according to claim 1, wherein: the beam-collecting groove (2021) is an inclined surface which is formed by obliquely arranging the bottom end of the groove of the displacement groove (202).
6. An aerospace air exchange device according to claim 1, wherein: the limiting groove (2022) is a rectangular groove which is obliquely arranged on the surface of the bundling groove (2021), rectangular open grooves are further arranged on two sides of the middle of the groove, and meanwhile, the open groove of the limiting groove (2022) is mutually embedded with the convex block on the surface of the rotary groove mark (303).
7. An aerospace air exchange device according to claim 1, wherein: the combination block (2031) is a circular rectangular plate with a curved inclined arrangement and connected with each other by a plurality of extension blocks (2033), and one side of the combination block (2031) attached to the beam-collecting groove (2021) is an inclined plane with a straight inclined angle.
8. An aerospace air exchange device according to claim 1, wherein: the impact block (304) is a triangular convex block which is arranged on one side of the periphery of the surface of the rotating ring (3) in an inclined arc mode.
9. An aerospace air exchange device according to claim 1, wherein: the flow limiting block (2041) is a triangular lug which is bent and inclined from one side of the bottom end of the middle part of the discharge groove (204) to the other side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011393019.9A CN112455693A (en) | 2020-12-02 | 2020-12-02 | Air interchanger for aerospace |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011393019.9A CN112455693A (en) | 2020-12-02 | 2020-12-02 | Air interchanger for aerospace |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112455693A true CN112455693A (en) | 2021-03-09 |
Family
ID=74806571
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011393019.9A Withdrawn CN112455693A (en) | 2020-12-02 | 2020-12-02 | Air interchanger for aerospace |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112455693A (en) |
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|---|---|---|---|---|
| CN101952170A (en) * | 2007-12-03 | 2011-01-19 | 空中巴士运行简易股份有限公司 | The air discharge port system that is used for the aircraft leading edge |
| CN103184935A (en) * | 2011-12-28 | 2013-07-03 | 中航商用航空发动机有限责任公司 | Hot-air anti-icer for engine inlet |
| CN104136322A (en) * | 2012-03-02 | 2014-11-05 | 埃尔塞乐公司 | Turbine engine nacelle fitted with a heat exchanger |
| CN104373204A (en) * | 2013-08-15 | 2015-02-25 | 福特环球技术公司 | Air intake duct ice ingestion features |
| CN105508054A (en) * | 2014-09-23 | 2016-04-20 | 中航商用航空发动机有限责任公司 | Engine gas inlet pipe anti-icing system and aircraft engine |
| CN105992867A (en) * | 2013-10-25 | 2016-10-05 | 肖特兄弟公司 | Anti-icing system for an aircraft |
| CN106959034A (en) * | 2016-01-08 | 2017-07-18 | 通用电气公司 | Heat exchanger for embedded engine applications |
| CN107448298A (en) * | 2016-05-02 | 2017-12-08 | 通用电气公司 | For the improved pitted cabin inner surface of tool that conducts heat |
| CN207565850U (en) * | 2017-12-03 | 2018-07-03 | 中国直升机设计研究所 | It is a kind of can draining go straight up to air conditioner inlet duct |
| US20190112065A1 (en) * | 2017-10-18 | 2019-04-18 | Airbus Operations S.A.S. | Air Inlet Lip Of An Aircraft Engine Comprising A De-icing System |
| US20200102067A1 (en) * | 2018-09-27 | 2020-04-02 | Rolls-Royce Plc | Nacelle intake |
-
2020
- 2020-12-02 CN CN202011393019.9A patent/CN112455693A/en not_active Withdrawn
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101952170A (en) * | 2007-12-03 | 2011-01-19 | 空中巴士运行简易股份有限公司 | The air discharge port system that is used for the aircraft leading edge |
| CN103184935A (en) * | 2011-12-28 | 2013-07-03 | 中航商用航空发动机有限责任公司 | Hot-air anti-icer for engine inlet |
| CN104136322A (en) * | 2012-03-02 | 2014-11-05 | 埃尔塞乐公司 | Turbine engine nacelle fitted with a heat exchanger |
| CN104373204A (en) * | 2013-08-15 | 2015-02-25 | 福特环球技术公司 | Air intake duct ice ingestion features |
| CN105992867A (en) * | 2013-10-25 | 2016-10-05 | 肖特兄弟公司 | Anti-icing system for an aircraft |
| CN105508054A (en) * | 2014-09-23 | 2016-04-20 | 中航商用航空发动机有限责任公司 | Engine gas inlet pipe anti-icing system and aircraft engine |
| CN106959034A (en) * | 2016-01-08 | 2017-07-18 | 通用电气公司 | Heat exchanger for embedded engine applications |
| CN107448298A (en) * | 2016-05-02 | 2017-12-08 | 通用电气公司 | For the improved pitted cabin inner surface of tool that conducts heat |
| US20190112065A1 (en) * | 2017-10-18 | 2019-04-18 | Airbus Operations S.A.S. | Air Inlet Lip Of An Aircraft Engine Comprising A De-icing System |
| CN207565850U (en) * | 2017-12-03 | 2018-07-03 | 中国直升机设计研究所 | It is a kind of can draining go straight up to air conditioner inlet duct |
| US20200102067A1 (en) * | 2018-09-27 | 2020-04-02 | Rolls-Royce Plc | Nacelle intake |
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Application publication date: 20210309 |
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| WW01 | Invention patent application withdrawn after publication |