CN112937880A - Jet nozzle of auxiliary power device of airplane - Google Patents
Jet nozzle of auxiliary power device of airplane Download PDFInfo
- Publication number
- CN112937880A CN112937880A CN202110339658.5A CN202110339658A CN112937880A CN 112937880 A CN112937880 A CN 112937880A CN 202110339658 A CN202110339658 A CN 202110339658A CN 112937880 A CN112937880 A CN 112937880A
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- CN
- China
- Prior art keywords
- tail gas
- cooling air
- channel
- auxiliary power
- airplane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001816 cooling Methods 0.000 claims abstract description 64
- 238000002485 combustion reaction Methods 0.000 claims abstract description 9
- 239000007921 spray Substances 0.000 claims abstract 4
- 230000002708 enhancing effect Effects 0.000 claims description 5
- 241000251468 Actinopterygii Species 0.000 claims description 2
- 229910003460 diamond Inorganic materials 0.000 claims 1
- 239000010432 diamond Substances 0.000 claims 1
- 230000001965 increasing effect Effects 0.000 abstract description 14
- 238000000034 method Methods 0.000 abstract description 7
- 230000000694 effects Effects 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 2
- QNRATNLHPGXHMA-XZHTYLCXSA-N (r)-(6-ethoxyquinolin-4-yl)-[(2s,4s,5r)-5-ethyl-1-azabicyclo[2.2.2]octan-2-yl]methanol;hydrochloride Chemical compound Cl.C([C@H]([C@H](C1)CC)C2)CN1[C@@H]2[C@H](O)C1=CC=NC2=CC=C(OCC)C=C21 QNRATNLHPGXHMA-XZHTYLCXSA-N 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001743 silencing effect Effects 0.000 description 1
- 238000005507 spraying Methods 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
- B64D33/06—Silencing exhaust or propulsion jets
-
- 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
- B64D33/10—Radiator arrangement
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Exhaust Silencers (AREA)
Abstract
A tail gas jet pipe of an auxiliary power device of an airplane comprises a tail gas channel, a cooling air channel, grooves and fins. Tail gas generated by combustion in the auxiliary power device of the airplane flows into the tail gas channel from the tail gas inlet of the tail gas pipe and flows out of the tail gas pipe from the tail gas outlet to enter the environment; the cooling air flows into the cooling air channel from the cooling air inlet and flows out into the environment through the cooling air outlet. The tail gas and the cooling air exchange heat in the tail spray pipe, a groove is formed in the tail gas channel, small holes are formed in the groove, and part of the tail gas directly contacts with the cooling air through the small holes to exchange heat. In addition, fins are arranged in the cooling air channel. In addition, the section of the tail gas inlet is smaller than that of the tail gas outlet, so that the driving force of an auxiliary power device of the airplane is increased, and the noise generated in the tail gas flowing process is reduced. The invention increases the heat exchange between the tail gas and the cooling air from the two aspects of increasing the heat exchange coefficient and increasing the heat exchange area; it can also increase the propulsion of the auxiliary power unit of the aircraft and reduce the noise of the exhaust flow.
Description
Technical Field
The invention belongs to the field of auxiliary power devices of airplanes, and relates to a tail nozzle of an auxiliary power device of an airplane.
Background
The aircraft auxiliary power unit is a small gas turbine engine which can replace all functions of the engine except the failure of providing thrust for the aircraft. When the ignition of the auxiliary power device of the airplane is started, the oil supply amount in the combustion chamber begins to be converted from a lean state to a rich state, and the temperature of the combustion chamber is also increased continuously. Because the oil supply plan of the auxiliary power device of the airplane is determined by the rotating speed and the temperature, under the condition that the exhaust of the auxiliary power device of the airplane is not over-temperature, the oil supply quantity is gradually increased along with the rotating speed, and finally the oil supply plan is stable after reaching the fixed rotating speed and enters the rotating speed maintaining mode. If the starting stage of the auxiliary power device of the airplane is started, the front-end air compressor has a small air supply total amount due to low rotating speed, the air quantity for combustion cannot meet the requirement along with the increase of the oil supply amount, incomplete combustion is caused, the air quantity for cooling can not meet the requirement correspondingly, heat accumulation is easily caused, and the highest point of the exhaust temperature is generated.
Therefore, an efficient cooling and heat dissipation structure of an exhaust nozzle of an auxiliary power device of an airplane is urgently needed at present.
Disclosure of Invention
In order to overcome the above defects and shortcomings of the prior art, the invention aims to provide an efficient cooling and heat dissipation structure for an exhaust nozzle of an aircraft auxiliary power unit.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a tail nozzle of an auxiliary power device of an airplane is of a double-layer sleeve structure, wherein the sleeve is of a horn-shaped structure and comprises a tail gas channel 1, a tail gas inlet 2, a tail gas outlet 3, a cooling air channel 4, a cooling air inlet 5, a cooling air outlet 6, a groove 7, a groove small hole 8 and fins 9; tail gas generated by combustion in the auxiliary power device of the airplane flows into the tail gas channel 1 through the tail gas inlet 2 and then flows out of the tail gas outlet 3 to be discharged into the environment, and cooling air flows into the cooling air channel 4 through the cooling air inlet 5 and then flows out of the cooling air outlet 6 to enter the environment.
The inner layer sleeve structure is enclosed to form an area which is a tail gas channel 1, a small-diameter end is a tail gas inlet 2, and a large-diameter end is a tail gas outlet 3. The sectional area of a tail gas inlet 2 of a tail nozzle of the airplane auxiliary power device is smaller than that of a tail gas outlet 3, the speed of tail gas is reduced, the pressure of the tail gas is increased in the flowing process of a tail gas channel 1, and the driving force of the airplane auxiliary power device is improved; in addition, the "sudden expansion" structure makes the exhaust gas expand, thereby reducing the noise generated during the flow of the exhaust gas in the exhaust gas passage 1.
And a cooling air channel 4 is arranged between the inner layer sleeve structure and the outer layer sleeve structure, the small-diameter end of the outer layer sleeve structure is a cooling air inlet 5, and the large-diameter end of the outer layer sleeve structure is a cooling air outlet 6.
The cooling air channel 4 is internally and uniformly provided with a plurality of fins 9, so that the tail nozzle of the auxiliary power device of the airplane is a whole, and the fins 9 can enhance the heat convection between the cooling air and the inner wall surface of the cooling air channel 4, namely the outer wall surface of the tail gas channel 1.
The inner wall surface of the tail gas channel 1 is provided with an inward groove 7 along the circumferential direction, and the groove 7 is used for increasing the heat exchange area between the tail gas and the inner wall surface of the tail gas channel 1 and enhancing the heat convection between the tail gas and the inner wall surface of the tail gas channel 1. Three surfaces of the groove 7 are provided with groove small holes 8, part of tail gas can directly contact with cooling air through the groove small holes 8 for heat exchange, and the heat exchange effect is greatly enhanced; the existence of the small groove holes 8 can lead the tail gas to generate rotational flow and vortex in the flowing process, thereby enhancing the heat exchange; the small groove holes 8 can also produce a silencing effect, so that the noise generated by the flowing of the tail gas is reduced.
Further, the shape of the small groove holes 8 can be various, and can be, but not limited to, circular holes, oblong holes, rhombic holes, fish scale holes, bulging holes and the like.
Further, the fins may be various types of fins, including but not limited to flat fins, louvered fins, corrugated fins, rectangular staggered-tooth fins, and the like.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects that:
1) the tail gas generated by combustion in the auxiliary power device of the airplane exchanges heat with cooling air in the tail gas spraying pipe, the groove formed in the tail gas channel increases the heat exchange area between the tail gas and the inner wall surface of the tail gas channel, and the heat convection between the tail gas and the inner wall surface of the tail gas channel is enhanced.
2) The groove is provided with small groove holes, part of tail gas can directly contact with cooling air through the small holes for heat exchange, and meanwhile, the small holes can enable the flow of the tail gas to generate rotational flow and vortex, so that the heat exchange is enhanced; the fins are arranged in the cooling air channel, so that the heat convection between the cooling air and the inner wall surface of the cooling air channel, namely the outer wall surface of the tail gas channel, is enhanced. In addition, the small holes formed in the grooves can also produce a noise elimination effect to reduce noise generated in the tail gas flowing process.
3) In addition, the tail gas inlet section of the tail nozzle of the auxiliary power device of the airplane is smaller than the tail gas outlet section, the speed of tail gas is reduced when the tail gas flows in a tail gas channel, the pressure is increased, and the driving force of the auxiliary power device of the airplane can be increased; and meanwhile, the tail gas expansion can reduce the noise generated in the tail gas flowing process.
Therefore, the heat exchange between the tail gas and the cooling air is increased in two aspects of increasing the heat exchange coefficient and increasing the heat exchange area; in addition, the invention can increase the driving force of the auxiliary power device of the airplane and reduce the flowing noise of the tail gas.
Drawings
FIG. 1 is a schematic block diagram of the present invention;
FIG. 2 is a longitudinal cross-sectional view of the structure of the present invention;
figure 3 is a cross-sectional view of the structure of the present invention.
In the figure: 1 is a tail gas channel, 2 is a tail gas inlet, 3 is a tail gas outlet, 4 is a cooling air channel, 5 is a cooling air inlet, 6 is a cooling air outlet, 7 is a groove, 8 is a groove small hole, and 9 is a fin.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects solved by the present invention more clearly apparent, the present invention is further described below with reference to the accompanying drawings and embodiments. It should be understood that the embodiments described herein are merely illustrative and are not intended to limit the present invention.
A tail nozzle of an auxiliary power device of an airplane is of a double-layer sleeve structure, wherein the sleeve is of a horn-shaped structure and comprises a tail gas channel 1, a tail gas inlet 2, a tail gas outlet 3, a cooling air channel 4, a cooling air inlet 5, a cooling air outlet 6, a groove 7, a groove small hole 8 and fins 9; tail gas generated by combustion in the auxiliary power device of the airplane flows into the tail gas channel 1 through the tail gas inlet 2 and then flows out of the tail gas outlet 3 to be discharged into the environment, and cooling air flows into the cooling air channel 4 through the cooling air inlet 5 and then flows out of the cooling air outlet 6 to enter the environment.
The region of the inner layer sleeve structure enclosed city is a tail gas channel 1, the small diameter end is a tail gas inlet 2, and the large diameter end is a tail gas outlet 3. The sectional area of the tail gas inlet 2 is smaller than that of the tail gas outlet 3, the speed of the tail gas can be reduced and the pressure of the tail gas can be increased in the flowing process of the tail gas channel 1, and the driving force of the auxiliary power device of the airplane is improved.
And a cooling air channel 4 is arranged between the inner layer sleeve structure and the outer layer sleeve structure, the small-diameter end of the outer layer sleeve structure is a cooling air inlet 5, and the large-diameter end of the outer layer sleeve structure is a cooling air outlet 6.
A plurality of fins 9 are uniformly arranged in the cooling air channel 4, so that the tail nozzle of the auxiliary power device of the airplane is a whole.
The inner wall surface of the tail gas channel 1 is provided with an inward groove 7, and the groove 7 is used for increasing the heat exchange area between the tail gas and the inner wall surface of the tail gas channel 1 and enhancing the heat convection between the tail gas and the inner wall surface of the tail gas channel 1. Three surfaces of the groove 7 are provided with groove small holes 8, part of tail gas can directly contact with cooling air through the groove small holes 8 for heat exchange, and the heat exchange effect is greatly enhanced; the existence of the small groove holes 8 can lead the tail gas to generate rotational flow and vortex in the flowing process, thereby enhancing the heat exchange; the fluted apertures 8 also reduce the noise generated by the exhaust flow.
The cooling air channel 4 is internally provided with the fins 9, so that the heat convection between the cooling air and the inner wall surface of the cooling air channel 4, namely the outer wall surface of the tail gas channel 1, is enhanced.
The small groove holes 8 are circular holes.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. 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 (2)
1. The tail spray pipe of the auxiliary power device of the airplane is characterized in that the tail spray pipe of the auxiliary power device of the airplane is of a double-layer sleeve structure, and a sleeve is of a horn-shaped structure and comprises a tail gas channel (1), a tail gas inlet (2), a tail gas outlet (3), a cooling air channel (4), a cooling air inlet (5), a cooling air outlet (6), a groove (7), small groove holes (8) and fins (9); tail gas generated by combustion in the auxiliary power device of the airplane flows into the tail gas channel (1) from the tail gas inlet (2) and then is discharged into the environment from the tail gas outlet (3), and cooling air flows into the cooling air channel (4) from the cooling air inlet (5) and then enters the environment through the cooling air outlet (6);
the area surrounded by the inner-layer sleeve structure is a tail gas channel (1), the small-diameter end is a tail gas inlet (2), and the large-diameter end is a tail gas outlet (3); the sectional area of the tail gas inlet (2) is smaller than that of the tail gas outlet (3);
a cooling air channel (4) is arranged between the inner layer of sleeve structure and the outer layer of sleeve structure, the small-diameter end is a cooling air inlet (5), and the large-diameter end is a cooling air outlet (6);
a plurality of fins (9) are uniformly arranged in the cooling air channel (4), so that the tail spray pipe of the auxiliary power device of the airplane is a whole, and the fins (9) can enhance the convection heat exchange between the cooling air and the inner wall surface of the cooling air channel (4);
an inward groove (7) is formed in the inner wall surface of the tail gas channel (1) along the circumferential direction and used for enhancing the convection heat exchange between the tail gas and the inner wall surface of the tail gas channel (1); three surfaces of the groove (7) are provided with small groove holes (8), and part of tail gas is in direct contact with cooling air through the small groove holes (8) for heat exchange.
2. An aircraft auxiliary power unit nozzle according to claim 1, characterized in that said recessed aperture (8) is in the shape of, but not limited to, a circular hole, an oblong hole, a diamond hole, a fish scale hole, a bulge hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110339658.5A CN112937880B (en) | 2021-03-30 | 2021-03-30 | Jet nozzle of auxiliary power device of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110339658.5A CN112937880B (en) | 2021-03-30 | 2021-03-30 | Jet nozzle of auxiliary power device of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112937880A true CN112937880A (en) | 2021-06-11 |
| CN112937880B CN112937880B (en) | 2023-03-28 |
Family
ID=76230520
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110339658.5A Active CN112937880B (en) | 2021-03-30 | 2021-03-30 | Jet nozzle of auxiliary power device of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112937880B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110271686A1 (en) * | 2010-05-05 | 2011-11-10 | Francisco Jay M | Exhaust silencer convection cooling |
| CN104875898A (en) * | 2015-06-23 | 2015-09-02 | 中国航空工业集团公司西安飞机设计研究所 | Tail jet nozzle assembly used for airplane and airplane with same |
| CN206968996U (en) * | 2017-07-18 | 2018-02-06 | 广州市司派克航空器材有限公司 | A kind of drainage type bilayer cooling spray pipe |
| CN108082503A (en) * | 2017-11-30 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of ventilating and cooling and exhaust system for aircraft auxiliary power plant |
| CN108138654A (en) * | 2015-08-07 | 2018-06-08 | 普拉特 - 惠特尼加拿大公司 | The turboprop component of engine and cooling exhaust with combination |
| CN112412656A (en) * | 2020-11-13 | 2021-02-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Full-composite-material skin aircraft engine cabin cooling structure |
-
2021
- 2021-03-30 CN CN202110339658.5A patent/CN112937880B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110271686A1 (en) * | 2010-05-05 | 2011-11-10 | Francisco Jay M | Exhaust silencer convection cooling |
| CN104875898A (en) * | 2015-06-23 | 2015-09-02 | 中国航空工业集团公司西安飞机设计研究所 | Tail jet nozzle assembly used for airplane and airplane with same |
| CN108138654A (en) * | 2015-08-07 | 2018-06-08 | 普拉特 - 惠特尼加拿大公司 | The turboprop component of engine and cooling exhaust with combination |
| CN206968996U (en) * | 2017-07-18 | 2018-02-06 | 广州市司派克航空器材有限公司 | A kind of drainage type bilayer cooling spray pipe |
| CN108082503A (en) * | 2017-11-30 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of ventilating and cooling and exhaust system for aircraft auxiliary power plant |
| CN112412656A (en) * | 2020-11-13 | 2021-02-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Full-composite-material skin aircraft engine cabin cooling structure |
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| Publication number | Publication date |
|---|---|
| CN112937880B (en) | 2023-03-28 |
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