CN112576378B - Gas turbine engine with automatic separation starting turbine - Google Patents
Gas turbine engine with automatic separation starting turbine Download PDFInfo
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- CN112576378B CN112576378B CN202011469568.XA CN202011469568A CN112576378B CN 112576378 B CN112576378 B CN 112576378B CN 202011469568 A CN202011469568 A CN 202011469568A CN 112576378 B CN112576378 B CN 112576378B
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- turbine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/275—Mechanical drives
- F02C7/277—Mechanical drives the starter being a separate turbine
Abstract
A gas turbine engine with an automatic separation starting turbine is disclosed, wherein the engine core machine consists of a high-pressure compressor, a combustion chamber and a turbine, and a turbine disc with blades distributed at intervals along the circumferential direction is positioned below the engine core machine; the final turbine is arranged on a final turbine disc of the turbine disc, the starting turbine is arranged at the tail end of the final turbine disc, the starting turbine blades are arranged at the rear end of the starting turbine, an elastic pawl mechanism which is meshed with the front end of the starting turbine and the final turbine disc and can realize automatic separation is arranged on the front end of the starting turbine and the final turbine disc, and the starting turbine and an engine rotor are automatically separated after the engine is successfully started to reduce the load of the engine rotor and maximize the working efficiency of the engine; the rear end of the starting turbine is provided with an engine tail cone, a gunpowder starter used for igniting gunpowder to impact the starting turbine blade is arranged in the engine tail cone, and the starting turbine rotates at a high speed to drive an engine rotor to rotate so as to prepare conditions for starting the engine.
Description
Technical Field
The invention relates to the technical field of gas turbine engines, in particular to a gas turbine engine with an automatic separation starting turbine.
Background
The aviation gas turbine engine is mainly divided into five types, namely a turbojet engine, a turbofan engine, a turboshaft engine, a turboprop engine and a paddle fan engine, wherein the turbojet engine comprises an air inlet channel, a gas compressor, a combustion chamber, a turbine and a tail nozzle, and the air inlet channel is an air flow channel formed by an air inlet casing of an air inlet part at the front end of the engine; the compressor is a rotating part which applies work to air to compress the air and can be generally divided into an axial flow compressor and a centrifugal compressor; the combustion chamber is a place where aviation fuel oil is combusted, and chemical energy of the fuel is converted into heat energy to be released; the turbine is a component which receives high-speed heat flow released by the combustion chamber, is acted by gas and supplies a part of the obtained work to the compressor to compress air; the tail nozzle has the functions of expanding and accelerating hot air flow led out by the turbine to generate thrust and adjusting the working state of the engine; the five parts work together to realize the circulation of the gas turbine engine, so that the thrust is continuously generated to propel the aircraft to move.
The gas turbine engine has the advantages of high specific impulse, simple structure, small size, adjustable thrust, no need of booster to start at zero speed, long-time cruise operation and the like, and is widely applied to cruise missiles. In order to meet the requirement of rapid missile launching, the engine needs to be started in a short time and climbs to a state of a large rotating speed, the traditional gas turbine engine has no rapid starting capability, and the engine is usually assisted to be started by adopting a starting motor or an external rotating mode, but the starting process is long, and the requirement of rapid response of the modern aeronautical missile is difficult to meet.
For a gas turbine engine for a cartridge requiring quick starting, a powder gas starting mode is generally adopted, and the principle of powder gas impact starting is that high-temperature high-speed gas flow generated when powder in a powder starter is combusted impacts an engine rotor blade so as to drive a gas turbine engine rotor to rotate at high speed. The gunpowder gas starting mode can be divided into two modes according to the structure: one is a high-temperature gas direct impact engine rotor blade, such as a gas turbine engine of which a powder starter directly impacts an engine turbine through a gas guide pipe as shown in fig. 1, wherein 1 is an engine shell, 2 is the gas guide pipe of the powder starter, 3 is an engine turbine blade, and 4 is the powder starter; the other is a special starting turbine blade for high-temperature gas impact, the starting turbine and the working turbine are fixedly connected through bolts or other modes and rotate together, the starting turbine blade is not in an engine working flow channel, the starting turbine drives an engine rotor to rotate in the starting process, the rotor continuously drives the starting turbine to rotate after the engine is started, and as shown in fig. 2, 1 is an engine working turbine, 2 is an engine shell, 3 is a starting turbine impeller, 4 is a starting turbine blade, 5 is a powder starter nozzle, and 6 is a powder starter;
the first starting mode has the defects that high-temperature gas needs to pass through a longer gas guide pipe, the loss of gas efficiency is serious, the heat protection design of a drainage pipeline also has difficulty, and meanwhile, the high-temperature gas has short-time scouring damage to turbine blades of an engine, the service life of the engine is easily shortened, and potential safety hazards exist; although the second starting mode introduces the starting turbine to avoid the washing damage of high-temperature gas to the turbine blades, the starting turbine needs to be continuously driven to rotate after the engine is started, so that the additional load of the engine is increased, and the working efficiency of the engine is reduced.
Therefore, it is an urgent technical problem for those skilled in the art to develop a gas turbine engine which can be applied to a starting process and operated under a powder starter, and can start a turbine to rotate an engine by starting the turbine, and the turbine can be automatically separated from an engine rotor after the engine is successfully started to reduce the load of the engine rotor, so as to maximize the working efficiency of the engine.
Disclosure of Invention
The present invention is directed to a gas turbine engine with an autosegregation start turbine to solve the above problems of the background art.
The technical problem solved by the invention is realized by adopting the following technical scheme:
a gas turbine engine with an automatic separation starting turbine comprises an engine core machine, a turbine disc, a final stage turbine, a starting turbine and an engine tail cone, wherein the engine core machine consists of a high-pressure compressor, a combustion chamber and a turbine, the turbine disc at least provided with a row of blades distributed at intervals along the circumferential direction is positioned below the engine core machine, and the turbine disc rotates at a high speed along the central shaft of the engine during working; the starting turbine is arranged at the tail end of the last-stage turbine disc, the starting turbine blade is arranged at the rear end of the starting turbine, the front end of the starting turbine and the last-stage turbine disc are provided with elastic pawl mechanisms which are meshed with each other and can realize automatic separation at the same time, the rear end of the starting turbine is provided with an engine tail cone, and a powder starter used for igniting powder is arranged in the engine tail cone.
In the invention, the front end of the high-pressure compressor is provided with an air inlet for introducing air, the rear end of the air inlet is provided with a fan, and the air enters the fan from the air inlet, is pressurized by the high-pressure compressor, flows into a combustion chamber and is mixed with fuel in the combustion chamber; when the turbine disc works, the fan and the high-pressure compressor are driven to rotate at the same time, and work is done for air entering the engine.
In the present invention, the starting turbine blade is circumferentially arranged at a starting turbine rear end.
In the invention, the elastic pawl mechanism comprises a circle of pawls arranged at the front end of the starting turbine, ratchets arranged on the final stage turbine disc and meshed with the pawls, a torsion spring arranged on a pawl rotating shaft and a wedge-shaped stop pin arranged on the torsion spring, wherein the pawls are meshed with the ratchets through the torsional force of the torsion spring so as to transmit torque, and after the torsion spring is tightly pressed, the pawl is prevented from rebounding through the stop pin of the wedge-shaped stop pin.
In the present invention, the gas nozzle is provided in the circumferential direction of the powder starter, and high-temperature and high-speed gas is transmitted to the starting turbine blade through the gas nozzle.
In the invention, the engine tail cone is arranged on an engine support plate, a grid channel is arranged on the engine support plate, and fuel gas generated by the gunpowder starter is discharged through the grid channel of the engine support plate.
When the engine is started, the gunpowder starter burns gunpowder to generate high-temperature and high-speed fuel gas, and the fuel gas impacts a starting turbine blade arranged on a starting turbine to drive the starting turbine to rotate at high speed, so that a final stage turbine disc is driven to rotate at high speed, an engine rotor is driven to rotate, and conditions are prepared for starting the engine;
after the engine is successfully started, the rotating speed of the rotor continuously rises, gunpowder of the gunpowder starter in the tail cone of the engine gradually burns out, the driving force is continuously reduced, the starting turbine blade cannot be continuously blown to rotate, the engine rotor is driven to rotate, when the rotating speed of the last-stage turbine exceeds the maximum rotating speed of the starting turbine, the ratchet on the last-stage turbine disc drives the pawl on the starting turbine to continuously compress until the torsion spring arranged in the pawl rotating shaft is pressed into the wedge-shaped stop pin, the pawl is meshed with the pawl through the torsional force of the torsion spring, further the torque is transmitted, the torsion spring is clamped by the wedge-shaped stop pin after being compressed and cannot rebound again, and the starting turbine is separated from the last-stage turbine, so that the starting turbine and the engine rotor are automatically separated; after the starting turbine is separated from the engine rotor, the engine power is not consumed any more, so that the maximum working efficiency of the engine is realized.
Has the advantages that: the invention utilizes the powder starter to burn the powder to generate high-temperature and high-speed gas, and impacts the starting turbine blade arranged on the starting turbine to drive the starting turbine to rotate at high speed, so as to drive the rotor of the engine to rotate and prepare conditions for starting the engine; and then, the automatic separation function can be realized by utilizing the elastic pawl mechanism arranged on the front end of the starting turbine and the final stage turbine disk, and the gas turbine engine which can automatically separate the turbine from the engine rotor to reduce the load of the engine rotor and maximize the working efficiency of the engine is started after the engine is successfully started.
Drawings
Fig. 1-2 are schematic structural views of a conventional gunpowder gas starting mode.
FIG. 3 is a schematic structural diagram of a preferred embodiment of the present invention.
FIG. 4 is a schematic view of the start-up turbine and the last stage turbine disk in accordance with the preferred embodiment of the present invention.
FIG. 5 is a schematic view of the spring pawl mechanism and the engine tail cone mounting in the preferred embodiment of the present invention.
FIG. 6 is a schematic view of the starting turbine and the last turbine in engagement in a preferred embodiment of the present invention.
FIG. 7 is a schematic illustration of the starting turbine and the last turbine in a disengaged state in accordance with a preferred embodiment of the present invention.
Fig. 8 is a schematic view of the installation of the resilient detent mechanism in the preferred embodiment of the present invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.
Referring to fig. 3-8, the gas turbine engine with the automatic separation starting turbine comprises an air inlet 1, a fan (low-pressure compressor) 2, a high-pressure compressor 3, a combustion chamber 4, a turbine 5, a last-stage turbine disc 6, a last-stage turbine 7, a starting turbine 8, a starting turbine blade 9, an engine support plate 10, an engine tail cone 11, a tail nozzle 12, a gas nozzle 13, a ratchet 14, a pawl 15, a torsion spring 16 and a wedge-shaped stop pin 17, wherein the high-pressure compressor 3, the combustion chamber 4 and the turbine 5 form an engine core machine, air enters the fan 2 from the air inlet 1, is pressurized by the high-pressure compressor 3, then flows into the combustion chamber 4, and is mixed with fuel in the combustion chamber 4; the turbine disc is provided with at least one row of blades distributed at intervals along the circumferential direction and is positioned below the engine core machine, and when the turbine disc works, the turbine disc rotates at a high speed along the central shaft of the engine and simultaneously drives the fan 2 and the high-pressure compressor 3 to rotate so as to apply work to air entering the engine; the final-stage turbine 7 is mounted on the final-stage turbine disc 6, the starting turbine 8 is arranged at the tail end of the final-stage turbine disc 6, the starting turbine blades 9 are circumferentially arranged at the rear end of the starting turbine 8, elastic pawl mechanisms used for being meshed with each other to achieve automatic separation are arranged on the front end of the starting turbine 8 and the final-stage turbine disc, an engine tail cone 11 is arranged at the rear end of the starting turbine 8, and a powder starter used for igniting powder is mounted in the engine tail cone 11.
In this embodiment, the elastic ratchet mechanism comprises a ring of ratchets 15 installed at the front end of the starting turbine 8, ratchets 14 installed on the last stage turbine disk 6 and meshed with the ratchets 15, a torsion spring 16 installed on the rotation shaft of the ratchets 15, and a wedge-shaped stop pin 17 installed on the torsion spring 16, wherein the ratchets 15 are forced to be meshed with the ratchets 14 by the torsion force of the torsion spring 16 to transmit torque, and after the torsion spring 16 is compressed, the wedge-shaped stop pin 17 stops to prevent the ratchets 15 from rebounding, as shown in fig. 6.
In the gas turbine engine, high-temperature combustion gas mainly passes through one or more flow passages, so a certain number of gas nozzles 13 are arranged in the circumferential direction of the gunpowder starter, the gas nozzles 13 are Laval nozzles with fixed throat diameters, the opening directions of the gas nozzles face to the starting turbine blades 9 so as to fully utilize the kinetic energy of the high-temperature gas, the starting turbine blades 9 which are circumferentially distributed at intervals are impacted on the starting turbine 8 to drive the starting turbine 8 to rotate at high speed, and the pawl 15 on the starting turbine 8 drives the last-stage turbine disc 6 to rotate at high speed so as to drive an engine rotor to rotate, so that conditions are prepared for starting the engine; because high-temperature combustion gas is sprayed out through the gas nozzle 13, hot spots and high thermal stress are formed in the gas nozzle 13, meanwhile, the starting success rate and the starting time of an engine are directly influenced by the belt rotation efficiency of the gunpowder starter, the gas nozzle 13 can be ensured to bear higher and higher temperatures under the condition of no degradation, failure or shortened service life, and therefore, the gas nozzle 13 is coated with a thermal protection coating so as to ensure that the gas nozzle 13 can normally work under the condition of high-temperature gas scouring without structural damage.
In the present embodiment, the engine tail cone 11 is mounted on the engine stay 10, and a grill passage is provided in the engine stay 10, and gas generated by the powder starter flows into the engine airflow passage through the grill passage of the engine stay 10 and is discharged from the tail nozzle 12 out of the engine.
In the embodiment, after the engine is started successfully, the rotation speed of the rotor is continuously increased, gunpowder of the gunpowder starter in the tail cone 11 of the engine is gradually burnt out, the driving force is continuously reduced, the starting turbine blades 9 cannot be blown to rotate continuously to drive the engine rotor to rotate, when the rotation speed of the final turbine 7 exceeds the maximum rotation speed of the starting turbine 8, the final turbine 7 becomes a driving wheel to drive the starting turbine 8 to rotate, the difference between the rotation torque of the engine rotor and the inertia torque of the starting turbine 8 around the central shaft is gradually increased, the ratchet 14 on the final turbine disc 6 drives the pawl 15 on the starting turbine 8 to be pressed continuously until the torsion spring 16 in the rotation shaft of the pawl 15 is pressed into the wedge-shaped stop pin 17, the torsion spring 16 is clamped by the wedge-shaped stop pin 17 and cannot rebound again, the starting turbine 8 is separated from the final turbine 7, so that the automatic separation of the starting turbine 8 and the engine rotor is realized, and the separated state is shown in fig. 7; after the starting turbine 8 is disengaged from the engine rotor, the power of the engine is no longer consumed, so that the work efficiency of the engine is maximized.
Claims (7)
1. A gas turbine engine with an automatic separation starting turbine comprises an engine core machine, a turbine disc, a final stage turbine, a starting turbine and an engine tail cone, and is characterized in that the engine core machine consists of a high-pressure compressor, a combustion chamber and a turbine, and the turbine disc is positioned below the engine core machine; the starting turbine blade is arranged at the rear end of the starting turbine, an elastic pawl mechanism which is meshed with each other and can realize automatic separation is arranged on the front end of the starting turbine and the last stage turbine disc, the rear end of the starting turbine is provided with an engine tail cone, and a gunpowder starter for igniting gunpowder is arranged in the engine tail cone; the elastic pawl mechanism comprises a circle of pawls arranged at the front end of the starting turbine, ratchets arranged on a final-stage turbine disc and meshed with the pawls, a torsion spring arranged on a pawl rotating shaft and a wedge-shaped stop pin arranged on the torsion spring;
when the engine is started, the powder starter burns powder to generate high-temperature and high-speed gas, and the gas impacts a starting turbine blade arranged on a starting turbine to drive the starting turbine to rotate at high speed, so that a final stage turbine disc is driven to rotate at high speed, and an engine rotor is driven to rotate to prepare conditions for starting the engine;
after the engine is successfully started, the rotating speed of the rotor continuously rises, gunpowder of the gunpowder starter in the tail cone of the engine gradually burns out, the driving force is continuously reduced, the starting turbine blade cannot be continuously blown to rotate, the engine rotor is driven to rotate, when the rotating speed of the last-stage turbine exceeds the maximum rotating speed of the starting turbine, the ratchet on the last-stage turbine disc drives the pawl on the starting turbine to continuously press until the torsion spring arranged in the pawl rotating shaft is pressed into the wedge-shaped stop pin, the pawl is meshed with the pawl through the torsion force of the torsion spring, further the torque is transmitted, the torsion spring is clamped by the wedge-shaped stop pin and cannot rebound again after being pressed, the starting turbine is separated from the last-stage turbine, therefore, the automatic separation of the starting turbine and the engine rotor is realized, and after the starting turbine is separated from the engine rotor, the power of the engine is not consumed any more.
2. The gas turbine engine with an automatically disengaging starting turbine of claim 1, wherein said turbine disk has at least one row of circumferentially spaced blades.
3. The gas turbine engine with the auto-separating starting turbine as claimed in claim 1, wherein the high pressure compressor is provided at a front end thereof with an intake duct for introducing air, and a fan is provided at a rear end thereof.
4. The gas turbine engine with an auto-separating starting turbine of claim 1, wherein said starting turbine blades are circumferentially disposed at a starting turbine aft end.
5. The gas turbine engine with an auto-disconnect starting turbine of claim 1, wherein the powder starter is circumferentially provided with a gas nozzle.
6. The gas turbine engine with an auto-disconnect start turbine of claim 1, wherein the engine tail cone is mounted on an engine mount.
7. The gas turbine engine with the autosegregation starting turbine as set forth in claim 6, wherein the engine support plate is provided with a grill passage, and gas generated by the powder starter is discharged through the grill passage of the engine support plate.
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| CN202011469568.XA CN112576378B (en) | 2020-12-14 | 2020-12-14 | Gas turbine engine with automatic separation starting turbine |
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| CN202011469568.XA CN112576378B (en) | 2020-12-14 | 2020-12-14 | Gas turbine engine with automatic separation starting turbine |
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| CN112576378B true CN112576378B (en) | 2023-03-24 |
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| CN113898477B (en) * | 2021-08-30 | 2023-02-03 | 四川航天中天动力装备有限责任公司 | Embedded starting belt rotating device of small turbine engine and aircraft thereof |
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