CN108045584B - Aviation propulsion system - Google Patents
Aviation propulsion system Download PDFInfo
- Publication number
- CN108045584B CN108045584B CN201711340330.5A CN201711340330A CN108045584B CN 108045584 B CN108045584 B CN 108045584B CN 201711340330 A CN201711340330 A CN 201711340330A CN 108045584 B CN108045584 B CN 108045584B
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- CN
- China
- Prior art keywords
- shaft
- fan
- main engine
- propulsion system
- commutator
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- 230000005540 biological transmission Effects 0.000 claims abstract description 33
- 239000000284 extract Substances 0.000 claims abstract description 6
- 230000008859 change Effects 0.000 claims description 3
- 238000009413 insulation Methods 0.000 claims description 2
- 238000009434 installation Methods 0.000 abstract description 3
- 230000006872 improvement Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
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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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
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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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Retarders (AREA)
Abstract
The invention provides an aviation propulsion system, which comprises a main engine (1), a shaft, a speed changer and a ducted fan, wherein the shaft is vertically connected with the main engine (1) in the radial direction, the other end of the shaft is connected with the ducted fan by arranging the speed changer, the ducted fan is formed by sequentially connecting a transmission shaft, a commutator, a fan shaft and the fan, two ends of the transmission shaft are respectively connected with the speed changer and the commutator, and the commutator is connected with the fan by arranging the fan shaft; the shaft extracts power from the main engine (1) and transmits the power to the transmission shaft through the transmission, the transmission shaft is connected with the fan shaft through the commutator, and the fan shaft is used for driving the fan so as to drive the ducted fan by the main engine (1). The propulsion system provided by the invention improves the propulsion efficiency of the propulsion system, meets the requirement of high-speed flight of an airplane, enables the propulsion system to select the installation position more easily, and can increase the functions which can be realized by the propulsion system.
Description
Technical Field
The invention belongs to the field of aero-engine structural design, and particularly relates to a distributed aero-propulsion system.
Background
In aeroengine design, propulsion efficiency is generally improved by increasing the bypass ratio. Under the condition that the core engines of the existing small bypass ratio engines and the existing large bypass ratio engines are basically consistent, the bypass ratio of the engines is improved through adjustment of low-pressure components, such as measures of increasing the number of stages of low-pressure turbines, enlarging the diameter of a fan and the like, and further the propulsion efficiency is improved. However, the prior art has the following disadvantages: with the increase of the bypass ratio of the engine, the external dimension of the engine is correspondingly increased, on one hand, the flight resistance is increased due to the increase of the windward area, and the requirement of the future passenger plane for high-speed flight cannot be met; on the other hand, the increase of the external dimension puts more strict requirements on the selection of the installation position and the mode of the engine. In addition, the existing scheme can only realize the improvement of the propulsion efficiency and has single and limited function.
Disclosure of Invention
It is an object of the present invention to provide an aviation propulsion system which overcomes or mitigates at least one of the above-mentioned disadvantages of the prior art.
The purpose of the invention is realized by the following technical scheme: an aviation propulsion system comprises a main engine, a shaft, a speed changer and a ducted fan, wherein the shaft is vertically connected in the radial direction of the main engine, the other end of the shaft is connected with the ducted fan through the speed changer, the ducted fan is formed by sequentially connecting a transmission shaft, a commutator, a fan shaft and a fan, two ends of the transmission shaft are respectively connected with the speed changer and the commutator, and the commutator is connected with the fan through the fan shaft; the shaft extracts power from the main engine and transmits the power to the transmission shaft through the transmission, the transmission shaft is connected with the fan shaft through the commutator, and the fan shaft is used for driving the fan so as to drive the ducted fan by the main engine.
Preferably, the transmission shaft and the fan shaft are arranged in parallel to the main engine and arranged in a collinear manner, wherein the fan shaft is vertically connected with the fan.
Preferably, two, four, six or eight shafts connected to the main engine are arranged on the main engine, each shaft is connected with one group of ducted fans through one group of transmissions, and the ducted fans are symmetrically arranged on two sides of the main engine.
Preferably, the number of shift stages of each group of the transmission is 2 to 5.
Preferably, the main engine is a twin-shaft turbojet engine with a power turbine or a small bypass ratio turbofan engine.
Preferably, the shaft extracts power from a low-pressure turbine shaft or a power turbine shaft of the main engine, and a heat insulating device is provided at a portion of the shaft in contact with the main engine.
The aviation propulsion system provided by the invention has the beneficial effects that 1) the contradiction between the improvement of the propulsion efficiency and the increase of the windward area of the propulsion system is effectively solved; 2) the installation mode of the propulsion system is more flexible; 3) besides forward propulsion, deceleration can be realized, and a propulsion system can generate control moment on the airplane through corresponding control to replace a part of control surface to realize regulation and control on the flying attitude of the airplane.
Drawings
Fig. 1 is a schematic structural view of an aviation propulsion system of the present invention.
Reference numerals:
1-main engine, 2.1-first shaft, 3.1-first speed changer, 4.1-first transmission shaft, 5.1-first commutator, 6.1-first fan shaft, 7.1-first fan, 2.2-second shaft, 3.2-second speed changer, 4.2-second transmission shaft, 5.2-second commutator, 6.2-second fan shaft and 7.2-second fan.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. 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 aviation propulsion system of the present invention is described in further detail below with reference to the accompanying drawings.
As shown in fig. 1, an aviation propulsion system comprises a main engine 1, a shaft, a transmission and a ducted fan, wherein the main engine 1 is a double-shaft turbojet engine with a power turbine or a small-bypass-ratio turbofan engine. The main engine 1 is vertically connected with a shaft in the radial direction, the other end of the shaft is connected with a ducted fan through a speed changer, wherein the shaft can be selectively provided with two, four, six or eight, each shaft is connected with a group of ducted fans through a group of speed changers, the ducted fans are selectively and symmetrically arranged on two sides of the main engine, and the speed change stage number of each group of speed changers can be selected from 2 stages to 5 stages. The shafts in this embodiment are provided with two (i.e., the first shaft 2.1 and the second shaft 2.2), and the transmission and the ducted fans are also both provided with two sets (i.e., the first ducted fan and the second ducted fan, and the first transmission 3.1 and the second transmission 3.2). Each group of ducted fans is formed by sequentially connecting a transmission shaft, a commutator, a fan shaft and a fan (namely, the first ducted fan is formed by sequentially connecting a first transmission shaft 4.1, a first commutator 5.1, a first fan shaft 6.1 and a first fan 7.1, the second ducted fan is formed by sequentially connecting a second transmission shaft 4.2, a second commutator 5.2, a second fan shaft 6.2 and a second fan 7.2), specifically, two ends of the transmission shaft are respectively connected with a speed changer and the commutator, and the commutator is connected with the fan by arranging the fan shaft, wherein the transmission shaft and the fan shaft are arranged in parallel with the main engine 1, the two shafts are arranged in a collinear way, and the fan shaft and the fan are also connected in a vertical connection way.
The shaft extracts power from a low-pressure turbine shaft or a power turbine shaft in the main engine 1, wherein a heat insulation device is provided at a portion of the shaft in contact with the main engine 1, the power is transmitted to a transmission shaft through a transmission, the transmission shaft is connected with a fan shaft through a commutator, and the fan shaft is used for driving a fan to realize driving of the ducted fan by the main engine 1.
The aviation propulsion system of the invention can realize the following functions:
1) when the main engine 1 works, the first fan 7.1 and the second fan 7.2 are driven to rotate, and positive thrust is generated.
2) The first speed changer 3.1 and the second speed changer 3.2 can make the rotating speeds of the fans (7.1, 7.2) connected with each other different, thereby generating different propelling forces and realizing the control of the flight attitude of the airplane.
3) The first reverser 5.1 and the second reverser 5.2 change the steering direction of the fan shafts (6.1, 6.2) which are respectively connected, thereby changing the steering direction of the fans (7.1, 7.2) which are connected with the fan shafts to ensure that the fans do not generate positive thrust, and simultaneously generating flow blocking effect on fan blades, realizing the reduction of the positive thrust of the whole propulsion system and reducing the speed of the airplane.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (6)
1. An aviation propulsion system is characterized by comprising a main engine (1), a shaft, a speed changer and a ducted fan, wherein the shaft is vertically connected with the main engine (1) in the radial direction, the other end of the shaft is connected with the ducted fan by arranging the speed changer, the ducted fan is formed by sequentially connecting a transmission shaft, a commutator, a fan shaft and a fan, two ends of the transmission shaft are respectively connected with the speed changer and the commutator, and the commutator is connected with the fan by arranging the fan shaft; the shaft extracts power from the main engine (1) and transmits the power to the transmission shaft through the transmission, the transmission shaft is connected with the fan shaft through the commutator, and the fan shaft is used for driving the fan so as to drive the ducted fan by the main engine (1).
2. An aircraft propulsion system according to claim 1, characterised in that the drive shaft and the fan shaft are both arranged parallel to the main engine (1) and in a collinear arrangement with the fan shaft perpendicular to the fan.
3. An aircraft propulsion system according to claim 2, characterised in that the main engine (1) is connected to two, four, six or eight shafts, each shaft being connected to a set of ducted fans via a set of said transmissions, wherein the ducted fans are arranged symmetrically on both sides of the main engine.
4. An aviation propulsion system according to claim 3, wherein the variator speed change stages in each group are from 2 to 5.
5. The aircraft propulsion system according to claim 4, characterized in that the main engine (1) is a two-shaft turbojet engine with a power turbine or a small bypass ratio turbofan engine.
6. An aircraft propulsion system according to claim 5, characterised in that the shaft extracts power from a low-pressure turbine shaft or a power turbine shaft of the main engine (1) and in that heat insulation means are provided at the portion of the shaft in contact with the main engine (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711340330.5A CN108045584B (en) | 2017-12-14 | 2017-12-14 | Aviation propulsion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711340330.5A CN108045584B (en) | 2017-12-14 | 2017-12-14 | Aviation propulsion system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108045584A CN108045584A (en) | 2018-05-18 |
| CN108045584B true CN108045584B (en) | 2021-07-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711340330.5A Active CN108045584B (en) | 2017-12-14 | 2017-12-14 | Aviation propulsion system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108045584B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110056451A (en) * | 2019-04-17 | 2019-07-26 | 中国航发湖南动力机械研究所 | External fan turbogenerator arranged side by side and its application in flying wing type airplane field |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3041932A3 (en) * | 2015-10-05 | 2017-04-07 | Snecma | PROPELLER ASSEMBLY OF AN AIRCRAFT COMPRISING AT LEAST TWO BLOWERS DEPORTEES |
| CN206504406U (en) * | 2017-01-25 | 2017-09-19 | 蒋闰涵 | A kind of fan with air-cleaning function |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6792745B2 (en) * | 2002-08-09 | 2004-09-21 | The Boeing Company | High bypass multi-fan engine |
| US7658346B2 (en) * | 2005-02-25 | 2010-02-09 | Honeywell International Inc. | Double ducted hovering air-vehicle |
| DE102013213518A1 (en) * | 2013-07-10 | 2015-01-15 | Rolls-Royce Deutschland Ltd & Co Kg | Turbofan engine |
| FR3042009B1 (en) * | 2015-10-05 | 2018-07-13 | Safran Aircraft Engines | TURBO MOTOR WITH BLOWERS DEPORTEES WITH A DIFFERENTIAL SYSTEM |
| CN106368851A (en) * | 2016-09-13 | 2017-02-01 | 中国民用航空飞行学院 | Multi-fan propelling device |
| CN107235155A (en) * | 2017-06-21 | 2017-10-10 | 桂艳春 | A kind of transmission device for high speed multirotor helicopter |
-
2017
- 2017-12-14 CN CN201711340330.5A patent/CN108045584B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3041932A3 (en) * | 2015-10-05 | 2017-04-07 | Snecma | PROPELLER ASSEMBLY OF AN AIRCRAFT COMPRISING AT LEAST TWO BLOWERS DEPORTEES |
| CN206504406U (en) * | 2017-01-25 | 2017-09-19 | 蒋闰涵 | A kind of fan with air-cleaning function |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108045584A (en) | 2018-05-18 |
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