CN112282964A - High-thrust engine for aircraft - Google Patents
High-thrust engine for aircraft Download PDFInfo
- Publication number
- CN112282964A CN112282964A CN202011211606.1A CN202011211606A CN112282964A CN 112282964 A CN112282964 A CN 112282964A CN 202011211606 A CN202011211606 A CN 202011211606A CN 112282964 A CN112282964 A CN 112282964A
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- China
- Prior art keywords
- compression chamber
- type compression
- power machine
- laval nozzle
- blade type
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a high-thrust engine for an aircraft, which comprises a power machine, a blade type compression chamber and a Laval nozzle, wherein the power machine is connected with the blade type compression chamber through the Laval nozzle; the power machine is connected with the blade type compression chamber through a rotating shaft, the power machine drives the blade type compression chamber to rotate, external air is sucked in, and the air is discharged through the Laval nozzle after being compressed to form supersonic speed air flow. The invention has small volume and can generate larger thrust.
Description
Technical Field
The invention relates to the technical field of aircraft power devices, in particular to a high-thrust engine for an aircraft.
Background
At present, the technology of aircrafts such as unmanned planes and the like is rapidly developed and more widely applied, under the general condition, power devices used by aircrafts such as unmanned planes, helicopters, propeller aircrafts and the like are propellers, air flows backwards through the high-speed rotation of the propellers so as to provide power, and the speed of flowing gas cannot exceed the speed of sound, so that the propellers are large in size, large in occupied area and very high in required rotation angular speed, and the phenomena such as air shock waves and the like are easily caused due to the fact that the linear speed of the tips of the propellers is too large. More importantly, such aircraft cannot be driven too fast because the exhaust velocity is too low, resulting in less thrust being provided by the air.
Disclosure of Invention
In view of the above, the present invention provides a high thrust engine for an aircraft, which has a small size and can generate a large thrust.
The technical scheme adopted by the invention is as follows:
a high thrust engine for an aircraft comprises a power machine, a vane type compression chamber and a Laval nozzle;
the power machine is connected with the blade type compression chamber through a rotating shaft, the power machine drives the blade type compression chamber to rotate, external air is sucked in, and the air is discharged through the Laval nozzle after being compressed to form supersonic speed air flow.
Furthermore, the vane type compression chamber comprises a front seal head, a rear seal head and a plurality of vanes;
the blades are circumferentially fixed between the front seal head and the rear seal head, the front seal head is used for being connected with a power machine, and the rear seal head is used for being fixedly connected with the Laval nozzle.
Has the advantages that:
1. the invention adopts compressed gas for injection to form power, has smaller volume, meets the requirement of environmental protection and has very wide application field; and the compressed gas flows through the Laval nozzle, the speed is rapidly increased and discharged to form supersonic airflow, and the provided thrust is large.
2. The vane type compression chamber has simple structure and small volume.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
the device comprises a power machine 1, a vane type compression chamber 2 and a Laval nozzle 3.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The present embodiment provides a high thrust engine for an aircraft, which includes a power machine 1 capable of driving blades to rotate at a high speed, a compression chamber 2 including rotor blades driven by the power machine, and a laval nozzle 3, as shown in fig. 1 and 2.
As shown in fig. 3, the vane type compression chamber 2 comprises a front head, a rear head and a plurality of vanes; the blades are circumferentially fixed between the front seal head and the rear seal head, and the deflection angles of the blades are related to the rotating speed of the power machine 1. The front end enclosure is connected with the power machine 1 through a rotating shaft, and the rear end enclosure is fixedly connected with the Laval nozzle 3. The power machine 1 drives the blade type compression chamber 2 and the Laval nozzle 3 to rotate at a high speed, the rotation energy of the power machine 1 is converted into the rotation energy of the blades, the blades forcibly suck air from the periphery of the blade type compression chamber 2, the pressure intensity of the sucked air is higher than the external atmospheric pressure, therefore, the air flows in the blade type compression chamber 2, the air is contracted through the convergent section of the Laval nozzle 3 and then is sprayed out through the divergent section, the speed of the sprayed air exceeds the local sound velocity, the thrust efficiency of the air is greatly improved, and the high-speed jet power generation device can be suitable for generating larger thrust.
When the vane type compression chamber 2 rotates at a high speed, the angular velocity is ω, the outer diameter of the vane type compression chamber 2 is R, the inner diameter is R, and the external atmospheric pressure is P0Density is rho0Flow velocity v of the inhaled gas0When the pressure of the vane type compression chamber 2 is set to be P and the density is ρ, the following relation is obtained according to the conservation of mass:
wherein
For unknown mass flow rate, L is the vane length of the vane compression chamber 2.
The velocity of the external gas is considered to be 0, and v is the velocity of the vane relative to the vane of the vane-type compression chamber 20Thus has v0ω · π R, thus
Let the area of the throat of the Laval nozzle 3 be AtDefining the characteristic velocity
Wherein
Is the gas mass flow rate out of the laval nozzle 3.
According to the gas state equation, there are:
where μ is the molar mass of the gas, μ 29g/mol, R8.314J/(mol.k) is the gas constant under normal atmospheric conditions, and V pi R2L is the internal volume of the vane compression chamber 2, T is the temperature of the gas inside the vane compression chamber 2, M is the mass of the gas inside the compression chamber.
Because the path of the gas compression process is short, the heat loss is ignored, and the gas is regarded as an isentropic process and is compressed in an isentropic mode. The following relations are provided:
is obtained by the above formula
Wherein
Is the rate of change of the mass of air in the internal volume of the vane-type compression chamber 2, k being airSpecific heat ratio.
According to the formula, the formula is synthesized as follows:
the above equation is a nonlinear equation, and a computer is used for solving P, wherein P is a variable, and the other is a known quantity.
When the pressure inside the vane type compression chamber 2 reaches a stable level, i.e.
The stable pressure inside the vane type compression chamber 2 is obtained
When the internal pressure of the vane type compression chamber 2 is P, the exhaust speed v is obtained according to the result of one-dimensional isentropic flow analysiseComprises the following steps:
according to the momentum conservation formula, the thrust of the engine when the pressure of the vane type compression chamber 2 is stabilized is as follows:
where F is the thrust generated by the engine.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present 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. A high thrust engine for an aircraft is characterized by comprising a power machine, a blade type compression chamber and a Laval nozzle;
the power machine is connected with the blade type compression chamber through a rotating shaft, the power machine drives the blade type compression chamber to rotate, external air is sucked in, and the air is discharged through the Laval nozzle after being compressed to form supersonic speed air flow.
2. The high thrust engine for an aircraft according to claim 1, wherein said vane-type compression chamber comprises a front head, a rear head and a plurality of vanes;
the blades are circumferentially fixed between the front seal head and the rear seal head, the front seal head is used for being connected with a power machine, and the rear seal head is used for being fixedly connected with the Laval nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011211606.1A CN112282964A (en) | 2020-11-03 | 2020-11-03 | High-thrust engine for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011211606.1A CN112282964A (en) | 2020-11-03 | 2020-11-03 | High-thrust engine for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112282964A true CN112282964A (en) | 2021-01-29 |
Family
ID=74351242
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011211606.1A Pending CN112282964A (en) | 2020-11-03 | 2020-11-03 | High-thrust engine for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112282964A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10126632A1 (en) * | 2000-08-08 | 2002-09-12 | Sandor Nagy | Combination propulsion system pref. for aircraft has thrust vector control, also useable as lifting device, located behind multistage vacuum system or ram jet engines |
| CN1693691A (en) * | 2005-04-30 | 2005-11-09 | 张鸿元 | Air compression aeroengine |
| CN205064122U (en) * | 2015-04-24 | 2016-03-02 | 谭佑军 | Aviation air injection motor |
-
2020
- 2020-11-03 CN CN202011211606.1A patent/CN112282964A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10126632A1 (en) * | 2000-08-08 | 2002-09-12 | Sandor Nagy | Combination propulsion system pref. for aircraft has thrust vector control, also useable as lifting device, located behind multistage vacuum system or ram jet engines |
| CN1693691A (en) * | 2005-04-30 | 2005-11-09 | 张鸿元 | Air compression aeroengine |
| CN205064122U (en) * | 2015-04-24 | 2016-03-02 | 谭佑军 | Aviation air injection motor |
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Application publication date: 20210129 |
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| WD01 | Invention patent application deemed withdrawn after publication |