CN112357097A - Turboprop engine power device for single-engine double-wing aircraft - Google Patents
Turboprop engine power device for single-engine double-wing aircraft Download PDFInfo
- Publication number
- CN112357097A CN112357097A CN202011336669.XA CN202011336669A CN112357097A CN 112357097 A CN112357097 A CN 112357097A CN 202011336669 A CN202011336669 A CN 202011336669A CN 112357097 A CN112357097 A CN 112357097A
- Authority
- CN
- China
- Prior art keywords
- engine
- turboprop
- fairing
- wing aircraft
- turboprop engine
- 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.)
- Pending
Links
- 238000009423 ventilation Methods 0.000 claims description 19
- 238000001816 cooling Methods 0.000 claims description 13
- 239000000446 fuel Substances 0.000 claims description 7
- 238000012986 modification Methods 0.000 claims description 7
- 230000004048 modification Effects 0.000 claims description 7
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 239000003350 kerosene Substances 0.000 claims description 2
- 239000007789 gas Substances 0.000 claims 1
- 239000002912 waste gas Substances 0.000 claims 1
- 239000003502 gasoline Substances 0.000 abstract description 12
- 238000004519 manufacturing process Methods 0.000 abstract description 6
- 239000003921 oil Substances 0.000 abstract description 4
- 238000003915 air pollution Methods 0.000 abstract description 2
- 239000000295 fuel oil Substances 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000009191 jumping Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
Images
Classifications
-
- B64D27/40—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/06—Attaching of nacelles, fairings or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control; Arrangement thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
Abstract
The invention discloses a turboprop engine power device for a single-engine double-wing aircraft, which comprises an engine fairing, wherein a turboprop engine is fixedly connected to the inner wall at the front port of the engine fairing, an engine firewall is fixedly connected to the inner wall, an engine mounting frame is installed at one end, positioned inside the engine fairing, of the turboprop engine, five propellers are installed at one end, positioned outside the engine fairing, the outside of the engine mounting frame penetrates through the engine firewall, and a mounting base is installed at the tail of the engine mounting frame. The invention solves the problems that the oil consumption is high, the supply guarantee of the aviation gasoline is also a difficult problem of aviation operation of each airline company in the piston engine adopted by the Y5/Y5B series airplane, and the aviation gasoline is increasingly in short supply and difficult to purchase fuel oil due to a plurality of factors such as high production difficulty, high manufacturing cost, serious air pollution and the like of the aviation gasoline, so that great inconvenience is caused to users of the piston type aviation gasoline engine.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a turboprop engine power device for a single-engine double-wing aircraft.
Background
The Y5 transport plane is the first self-made transport plane in China, and although the transport plane has been in service for nearly 50 years, the transport plane has stable flight and low operation cost, and is still the most common general air transport plane in China to date. The Y5/Y5B series airplane also has good low-altitude low-speed performance and short-distance take-off and landing capability. The Y5/Y5B series airplane is also a multipurpose airplane, can be used for transportation, training, agriculture and forestry operation, passenger transport and travel, aerial photography, rescue, parachute jumping and the like, and is irreplaceable to some extent.
However, the piston engine adopted by the Y5/Y5B series airplane has high oil consumption, the supply guarantee of the aviation gasoline is also a difficult problem for aviation operation of each airline company, and due to a plurality of factors such as high production difficulty, high manufacturing cost, serious air pollution and the like of the aviation gasoline, the aviation gasoline is increasingly in short supply, fuel purchasing is difficult, and great inconvenience is caused to users of the piston type aviation gasoline engine. The piston engine is poor in service and maintenance.
In order to solve the problems, the invention provides a turboprop engine power device for Y5/Y5B series airplanes, which can not only solve the problems of high oil consumption, difficult fuel supply and poor maintainability of the original Y5/Y5B series airplanes, but also greatly improve the flight performance of the Y5/Y5B series airplanes, meet the future development trend of the market, and have good market foundation and competitiveness in the future.
Disclosure of Invention
The invention aims to solve the problems that a piston engine adopted by a Y5/Y5B series airplane has high oil consumption, the supply guarantee of aviation gasoline is also a difficult problem of aviation operation of each airline company, and due to the factors of high production difficulty, high manufacturing cost, serious atmospheric pollution and the like of the aviation gasoline, the aviation gasoline is increasingly in short supply, fuel oil is difficult to purchase, and great inconvenience is caused to users of piston type aviation gasoline engines.
In order to achieve the purpose, the invention adopts the following technical scheme: the utility model provides a turboprop engine power device for single-engine double wing aircraft, including the engine cowling, the inner wall fixedly connected with turboprop engine of engine cowling front portion port department to and inner wall fixedly connected with engine firewall, the turboprop engine is located the inside one end of engine cowling and installs the engine mounting bracket, and is located the outside one end of engine cowling and installs five screw, the engine firewall is passed to the outside of engine mounting bracket, and the afterbody installs the mounting base, the turboprop engine is connected with engine control system through the cable.
Preferably, an engine air inlet system is mounted on the turboprop, an air inlet of the engine air inlet system penetrates through an engine fairing and is located outside the engine fairing, and air required by the operation of the turboprop is provided by the engine air inlet system.
Preferably, an exhaust system is installed on the turboprop, an exhaust port of the exhaust system penetrates through an engine fairing and is located outside the engine fairing, and exhaust gas after combustion of the turboprop is exhausted by the engine exhaust system.
Preferably, the engine fairing is installed at the front part of the aircraft body through a mounting base, the downward depression included angle between the axis of the turboprop engine and the horizontal plane of the aircraft structure is 0-3 degrees, and the axis is positioned on the symmetric plane of the aircraft.
Preferably, the engine control system is located in the aircraft cabin and comprises a control handle and a cable, the turboprop engine is provided with an all-weight digital control system, the handle can completely control all parameters of the turboprop engine, the lower part of the handle is provided with a double-backup cable joint for cable connection between the control handle and the all-weight digital control system, the all-weight digital control system can sense the operation of a pilot on the handle, and then all control signals are calculated for controlling the turboprop engine.
Preferably, the engine fairing is provided with an engine ventilation cooling system, cold air enters the engine heating area through a ventilation air inlet of the engine ventilation cooling system, and hot air is brought into natural air through a ventilation air outlet of the engine ventilation cooling system, so that the purpose of ventilation cooling is achieved.
Preferably, the turboprop uses jet fuel as fuel, and is capable of providing the power required by the aircraft in each flight phase.
Preferably, the system is used for unmanned modification of the Y5/Y5B series airplane.
Compared with the prior art, the invention has the following beneficial effects: the power device provided by the invention has a simple and reliable structure, can greatly improve the flight performance, safety, use maintainability and economy of Y5/Y5B series airplanes, and is also suitable for the requirements of Y5 unmanned airplanes after an unmanned control system is added; the power device uses aviation kerosene, can provide power required by each stage of the plane running, taking off, climbing, cruising and landing, and greatly improves the flight performance of each stage of the Y5/Y5B series plane.
Drawings
The invention is described in further detail below with reference to the following figures and detailed description:
FIG. 1 is a schematic overall structure of the present invention;
fig. 2 is a schematic view of the internal structure of the present invention.
In the figure: the engine comprises 1 engine fairing, 2 five-blade propeller, 3 turboprop engine, 4 engine mounting rack, 5 engine firewall, 6 engine ventilation cooling system, 7 engine air inlet system, 8 engine exhaust system, 9 engine control system and 10 mounting base.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure.
Please refer to fig. 1-2. It should be understood that the structures, ratios, sizes, and the like shown in the drawings and described in the specification are only used for matching with the disclosure of the specification, so as to be understood and read by those skilled in the art, and are not used to limit the conditions under which the present invention can be implemented, so that the present invention has no technical significance, and any structural modification, ratio relationship change, or size adjustment should still fall within the scope of the present invention without affecting the efficacy and the achievable purpose of the present invention. In addition, the terms "upper", "lower", "left", "right", "middle" and "one" used in the present specification are for clarity of description, and are not intended to limit the scope of the present invention, and the relative relationship between the terms and the terms is not to be construed as a scope of the present invention.
The invention provides a technical scheme that: the utility model provides a turboprop engine power device for single-engine double wing aircraft, including engine cowling 1, the inner wall fixedly connected with turboprop engine 3 of 1 front portion port departments of engine cowling to and the fire wall 5 is prevented to inner wall fixedly connected with engine, turboprop engine 3 is located the inside one end of engine cowling 1 and installs engine mounting bracket 4 to and be located the outside one end of engine cowling 1 and install five-bladed propeller 2, the outside of engine mounting bracket 4 is passed the engine and is prevented hot wall 5, and the afterbody installs mounting base 10, turboprop engine 3 is connected with engine control system 9 through the cable.
An engine air inlet system 7 is mounted on the turboprop engine 3, an air inlet of the engine air inlet system 7 penetrates through the engine fairing 1 and is located outside the engine fairing 1, and air required by the running of the turboprop engine 3 is provided by the engine air inlet system 7.
An exhaust system 8 is installed on the turboprop engine 3, an exhaust port of the exhaust system 8 penetrates through the engine fairing 1 and is located outside the engine fairing 1, and exhaust gas after combustion of the turboprop engine 3 is discharged by the engine exhaust system 8.
The engine fairing 1 is installed on the front portion of an airplane body through an installation base 10, the downward depression included angle between the axis of the turboprop engine 3 and the horizontal plane of the airplane structure is 0-3 degrees, and the axis is located on the symmetrical plane of the airplane.
The engine control system 9 is located in an aircraft cabin and comprises a control handle and a cable, the turboprop engine 3 is provided with an all-weight digital control system, the handle can completely control all parameters of the turboprop engine 3, the lower part of the handle is provided with a double-backup cable joint for cable connection between the control handle and the all-weight digital control system, the all-weight digital control system can sense the operation of a pilot on the handle, and then all control signals are calculated to control the turboprop engine 3.
The engine fairing 1 is provided with an engine ventilation cooling system 6, cold air enters an engine heating area through a ventilation air inlet of the engine ventilation cooling system 6, and then hot air is brought into natural air through a ventilation air outlet of the engine ventilation cooling system 6, so that the purpose of ventilation cooling is achieved.
The turboprop engine 3 uses jet fuel as fuel and is capable of providing the power required by the aircraft in the various flight phases.
The unmanned modification device is used for unmanned modification of Y5/Y5B series airplanes.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (8)
1. A turboprop engine power plant for single-engine two-wing aircraft, comprising an engine fairing (1), characterized in that: inner wall fixedly connected with turboprop engine (3) of engine radome fairing (1) front portion port department to and inner wall fixedly connected with engine firewall (5), turboprop engine (3) are located the inside one end of engine radome fairing (1) and install engine mounting bracket (4), and are located the outside one end of engine radome fairing (1) and install five-blade propeller (2), the outside of engine mounting bracket (4) is passed the engine and is prevented firewall (5), and the afterbody installs mounting base (10), turboprop engine (3) are connected with engine control system (9) through the cable.
2. The turboprop engine power plant for single-engine two-wing aircraft according to claim 1, wherein: the turboprop engine is characterized in that an engine air inlet system (7) is mounted on the turboprop engine (3), an air inlet of the engine air inlet system (7) penetrates through the engine fairing (1) and is located outside the engine fairing (1), and air required by the running of the turboprop engine (3) is provided by the engine air inlet system (7).
3. The turboprop engine power plant for single-engine two-wing aircraft according to claim 1, wherein: install exhaust system (8) on turboprop engine (3), the gas vent of exhaust system (8) passes engine fairing (1), and is located the outside of engine fairing (1), the waste gas after turboprop engine (3) combustion is discharged by engine exhaust system (8).
4. The turboprop engine power plant for single-engine two-wing aircraft according to claim 1, wherein: the engine fairing (1) is installed on the front portion of an airplane body through an installation base (10), the downward depression included angle between the axis of the turboprop engine (3) and the horizontal plane of the airplane structure is 0-3 degrees, and the axis is located on the symmetrical plane of the airplane.
5. The turboprop engine power plant for single-engine two-wing aircraft according to claim 1, wherein: the engine control system (9) is positioned in an aircraft cabin and consists of a control handle and a cable, the turboprop engine (3) is provided with a full-weight digital control system, the handle can completely control all parameters of the turboprop engine (3), the lower part of the handle is provided with a double-backup cable joint for cable connection between the control handle and the full-weight digital control system, the full-weight digital control system can sense the operation of a pilot on the handle, and then, each control signal is calculated to control the turboprop engine (3).
6. The turboprop engine power plant for single-engine two-wing aircraft according to claim 1, wherein: an engine ventilation cooling system (6) is installed on the engine fairing (1), cold air enters an engine heating area from a ventilation air inlet of the engine ventilation cooling system (6), and then hot air is brought into natural air from a ventilation air outlet of the engine ventilation cooling system (6), so that the purpose of ventilation cooling is achieved.
7. The turboprop engine power plant for single-engine two-wing aircraft according to claim 1, wherein: the turboprop engine (3) uses aviation kerosene as fuel and can provide the power required by the airplane in each flight stage.
8. The turboprop engine power plant for single-engine two-wing aircraft according to claim 1, wherein: the unmanned modification device is used for unmanned modification of Y5/Y5B series airplanes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011336669.XA CN112357097A (en) | 2020-11-25 | 2020-11-25 | Turboprop engine power device for single-engine double-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011336669.XA CN112357097A (en) | 2020-11-25 | 2020-11-25 | Turboprop engine power device for single-engine double-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112357097A true CN112357097A (en) | 2021-02-12 |
Family
ID=74533297
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011336669.XA Pending CN112357097A (en) | 2020-11-25 | 2020-11-25 | Turboprop engine power device for single-engine double-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112357097A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117002732A (en) * | 2023-10-07 | 2023-11-07 | 成都天域航通科技有限公司 | Unmanned aerial vehicle-based throwing device and control system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108128471A (en) * | 2017-12-15 | 2018-06-08 | 石家庄飞机工业有限责任公司 | A kind of aircraft fuel system fuel oil cooling device |
| CN108298095A (en) * | 2017-12-15 | 2018-07-20 | 石家庄飞机工业有限责任公司 | A kind of Small General Aircraft boat coal piston engine power plants |
| CA3033854A1 (en) * | 2018-02-19 | 2019-08-19 | Pratt & Whitney Canada Corp. | Aircraft with wheel well between heat exchangers of engine assembly |
| CN210437376U (en) * | 2019-06-06 | 2020-05-01 | 北京威凯通航空技术有限公司 | Y5 series airplane turboprop engine cabin safety firewall |
| CN210455238U (en) * | 2019-06-06 | 2020-05-05 | 北京威凯通航空技术有限公司 | Y5 series airplane turboprop lower lip |
-
2020
- 2020-11-25 CN CN202011336669.XA patent/CN112357097A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108128471A (en) * | 2017-12-15 | 2018-06-08 | 石家庄飞机工业有限责任公司 | A kind of aircraft fuel system fuel oil cooling device |
| CN108298095A (en) * | 2017-12-15 | 2018-07-20 | 石家庄飞机工业有限责任公司 | A kind of Small General Aircraft boat coal piston engine power plants |
| CA3033854A1 (en) * | 2018-02-19 | 2019-08-19 | Pratt & Whitney Canada Corp. | Aircraft with wheel well between heat exchangers of engine assembly |
| CN210437376U (en) * | 2019-06-06 | 2020-05-01 | 北京威凯通航空技术有限公司 | Y5 series airplane turboprop engine cabin safety firewall |
| CN210455238U (en) * | 2019-06-06 | 2020-05-05 | 北京威凯通航空技术有限公司 | Y5 series airplane turboprop lower lip |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117002732A (en) * | 2023-10-07 | 2023-11-07 | 成都天域航通科技有限公司 | Unmanned aerial vehicle-based throwing device and control system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11878805B2 (en) | Efficient low-noise aircraft propulsion system | |
| US9180974B2 (en) | Aircraft with an integral aerodynamic configuration | |
| EP1243782B1 (en) | Double jet engine inlet | |
| US10967980B2 (en) | Turbine engine propelled airplane having an acoustic baffle | |
| CN102530248A (en) | Design method for multifunctional helicopter | |
| CN208746231U (en) | A kind of distribution shrouded propeller power vertical take-off and landing drone | |
| CN109677608A (en) | Anury all-wing aircraft couples power aerial vehicle | |
| CN112357097A (en) | Turboprop engine power device for single-engine double-wing aircraft | |
| CN108298095A (en) | A kind of Small General Aircraft boat coal piston engine power plants | |
| CN103625634B (en) | A kind of winglet device of detachable adjustable inclination angle | |
| CN207045731U (en) | A kind of Concord | |
| CN210116639U (en) | Variable-configuration multi-mode unmanned aerial vehicle | |
| RU2789425C1 (en) | Aircraft with a hybrid power plant | |
| RU223474U1 (en) | Airplane integrated circuit | |
| CN110294104A (en) | It is a kind of can VTOL the stealthy Fixed Wing AirVehicle of high speed | |
| CN110228581A (en) | A kind of high speed Bi-Tail-Boom Layout unmanned plane | |
| RU204577U1 (en) | PLANE | |
| CN218463882U (en) | Engine nacelle for power influence of turboprop aircraft | |
| Piancastelli et al. | Multi-objective optimization of the cooling system of a diesel helicopter | |
| Xiao-li et al. | A Review of Electric Propulsion for Air Vehicle Research | |
| Chang et al. | The overall design and full-aircraft aerodynamic simulation of the tilting rotor cargo UAV based on variable shaft angle gear drive | |
| Pereira | Drag reduction of airframe and non-lifting rotating systems | |
| Glasgow et al. | Type AV/STOL propulsion system development | |
| RU1804415C (en) | Aircraft for local-service air lines | |
| Cochrane et al. | Applications of advanced upper surface blowing propulsive-lift technology |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210212 |
|
| RJ01 | Rejection of invention patent application after publication |