CN116291942A - Structure of tail nozzle of aviation turbojet engine - Google Patents

Structure of tail nozzle of aviation turbojet engine Download PDF

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Publication number
CN116291942A
CN116291942A CN202310342911.1A CN202310342911A CN116291942A CN 116291942 A CN116291942 A CN 116291942A CN 202310342911 A CN202310342911 A CN 202310342911A CN 116291942 A CN116291942 A CN 116291942A
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CN
China
Prior art keywords
pipe
powder chamber
tail nozzle
gas
turbojet 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
Application number
CN202310342911.1A
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Chinese (zh)
Inventor
张继远
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Harbin Institute Of Technology Robot Group Hangzhou Bay International Innovation Research Institute
Original Assignee
Harbin Institute Of Technology Robot Group Hangzhou Bay International Innovation Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Harbin Institute Of Technology Robot Group Hangzhou Bay International Innovation Research Institute filed Critical Harbin Institute Of Technology Robot Group Hangzhou Bay International Innovation Research Institute
Priority to CN202310342911.1A priority Critical patent/CN116291942A/en
Publication of CN116291942A publication Critical patent/CN116291942A/en
Pending legal-status Critical Current

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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
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • 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
    • F02C7/27—Fluid drives
    • F02C7/272—Fluid drives generated by cartridges
    • 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
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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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 relates to a structure of an aviation turbojet engine tail nozzle, which comprises a tail nozzle, a powder chamber pipe, a powder chamber connecting seat, a guide pipe, an air guide pipe and an air guide pipe connecting seat; the gunpowder chamber tube and the air duct connecting seat are fixed with the tail nozzle, the gunpowder chamber and the gunpowder chamber connecting seat are arranged in the gunpowder chamber tube, a communication cavity is arranged in the gunpowder chamber connecting seat, one end of the air duct is communicated with the communication cavity, the other end of the air duct is communicated with the gunpowder chamber, one end of the air duct is communicated with the communication cavity, the other end of the air duct is led to the outside of the tail nozzle, a jet pipe is arranged in the air duct connecting seat, one end of the air duct is communicated with the communication cavity, and the other end of the air duct is communicated with the jet pipe; the advantages are that: on the premise of not changing the structure of the turbojet engine, the quick starting device and the tail nozzle are combined into a whole, so that the number of parts of the turbojet engine is reduced, the structure is simplified, and the weight of the whole turbojet engine is reduced; and the engine can be reused in a mode of adding the gunpowder body, so that the use cost is reduced.

Description

Structure of tail nozzle of aviation turbojet engine
Technical Field
The invention relates to the technical field of aviation turbojet engines, in particular to a structure of an aviation turbojet engine tail nozzle.
Background
The aviation turbojet engine consists of an air inlet channel, an air compressor, a combustion chamber, a turbine and a tail nozzle. The tail nozzle is also called an exhaust nozzle, a nozzle or a thrust nozzle, and is an engine component in which high-temperature and high-pressure gas exhausted by a turbine in the turbojet engine is exhausted at a high speed so as to generate huge thrust.
When the turbojet engine operates normally, exhaust gas blows the rotation of the turbine blade of the exhaust gas of the aeroengine to drive the rotation of the main shaft so as to drive the rotation of the air inlet blade, a large amount of air passes through the rotating air inlet impeller, enters the combustion chamber after being compressed in volume and is mixed with fuel oil sprayed out by the fuel injector to form combustible mixed gas, the mixed gas is ignited, the temperature of the mixed gas is rapidly increased by the intense volume expansion, and the high-temperature high-speed high-energy gas is discharged through the turbine guide device so as to push the turbine to rotate.
Currently, small turbojet engines are evolving towards high thrust-weight ratios, low cost, simple and reliable structures, etc. The tail nozzle is improved, the number of parts of the turbojet engine is reduced, the structure is simplified, the weight of the whole turbojet engine is reduced, and the method has important significance for improving the whole performance of the small turbojet engine.
Based on this, the present application is hereby proposed.
Disclosure of Invention
The invention aims to provide a structure of an aviation turbojet engine tail nozzle so as to simplify the structure of the aviation turbojet engine and reduce the weight of the whole machine.
In order to achieve the above object, the technical scheme of the present invention is as follows:
the structure of the tail nozzle of the aviation turbojet engine comprises the tail nozzle and a quick starting device, wherein the quick starting device comprises a powder chamber pipe, a powder chamber connecting seat, a guide pipe and a guide pipe connecting seat; the gas-guiding device is characterized in that the powder chamber pipe and the gas-guiding pipe seat are both fixed on the tail nozzle, the powder chamber and the powder chamber seat are both installed in the powder chamber pipe, a communication cavity is formed in the powder chamber seat, one end of the gas-guiding pipe is communicated with the communication cavity, the other end of the gas-guiding pipe is communicated with the powder chamber, one end of the gas-guiding pipe is communicated with the communication cavity, the other end of the gas-guiding pipe is led to the outside of the tail nozzle, a jet pipe for jetting gas to a turbine blade of the turbojet engine is arranged in the gas-guiding pipe seat, one end of the gas-guiding pipe is communicated with the communication cavity, and the other end of the gas-guiding pipe seat is led to the gas-guiding pipe seat and is communicated with the jet pipe.
Furthermore, the diameter of the tail nozzle is gradually reduced from one end to the other end, and the air duct connecting seat is fixed at the outer wall of the large-caliber end of the tail nozzle.
Furthermore, an integrally formed flange is arranged at the outer wall of the large-caliber end of the tail spray pipe.
Further, the gunpowder chamber tube is arranged in the tail nozzle, and the outer wall of the gunpowder chamber tube is fixedly connected with the inner wall of the tail nozzle through the reinforcing ribs.
Further, the powder room is located the powder room intraductal and with both clearance fit, bleed pipe and powder room integrated into one piece, the one end that the powder room was exposed to bleed pipe is equipped with the external screw thread, be equipped with on the powder room seat can with bleed pipe threaded connection's internal thread hole, internal thread hole and intercommunication chamber intercommunication.
Further, a screwing nut is arranged at the outer wall of one end of the gunpowder chamber away from the gunpowder chamber connecting seat.
Further, a screwing nut is arranged at the outer wall of one end of the gunpowder chamber connecting seat, which is far away from the gunpowder chamber.
Furthermore, the number of the two guide tubes is two and the two guide tubes are symmetrically distributed.
Furthermore, two air ducts are symmetrically distributed, and two air duct seats are symmetrically distributed.
The invention has the advantages that: on the premise of not changing the core part structure of the turbojet engine, the quick starting device and the tail nozzle are combined into a whole, so that the number of parts of the turbojet engine is reduced, the structure is simplified, and the weight of the whole turbojet engine is reduced; in addition, the starting scheme can reuse the engine in a mode of adding the gunpowder body, so that the use cost is reduced.
Drawings
FIG. 1 is a three-dimensional schematic view of a turbojet engine in an embodiment;
FIG. 2 is a schematic side view of FIG. 1;
FIG. 3 is a schematic view of a three-dimensional structure of a large-caliber side of a tail pipe according to an embodiment;
FIG. 4 is a schematic view of a three-dimensional structure of a small bore side of a tail pipe according to an embodiment;
FIG. 5 is a schematic cross-sectional view A-A of FIG. 2;
FIG. 6 is an enlarged schematic view of portion A in FIG. 5;
FIG. 7 is a schematic cross-sectional view of B-B of FIG. 2;
description of the reference numerals
1-shell, 2-main shaft, 3-turbine, 4-air duct, 5-tail nozzle, 6-explosive chamber, 7-air duct, 8-flange, 9-explosive chamber seat, 10-letter guiding pipe, 11-air duct seat, 12-explosive chamber pipe, 13-screw nut, 14-strengthening rib, 15-screw hole.
Detailed Description
The present invention will be described in further detail with reference to the following embodiments, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like herein indicate an orientation or a positional relationship based on the orientation or the positional relationship shown in the drawings, and are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element to be referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
The present embodiment proposes a structure of an aircraft turbojet engine tail nozzle, as shown in fig. 1 to 7, including a tail nozzle 5 and a quick start device. The structure of the tail nozzle 5 is the same as the existing structure, and is of a convergent structure with the pipe diameter gradually reduced from one end to the other end, the tail nozzle 5 is arranged at the rear end of the engine, and the large-caliber end of the tail nozzle 5 is close to a turbine of the engine. In this embodiment, in order to facilitate the fixing of the tail nozzle 5 to the rear end of the engine, an integrally formed flange 8 is provided at the outer wall of the large-caliber end of the tail nozzle 5.
The quick start device of this embodiment includes a powder chamber tube 12, a powder chamber 6, a powder chamber holder 9, a fuse tube 10, a bleed tube 7, a gas guide tube 4, and a gas guide tube holder 11. The powder chamber tube 12 is located at the center of the tail nozzle 5, the outer wall of the powder chamber tube 12 is fixedly connected with the inner wall of the tail nozzle 5 through four reinforcing ribs 14, and the powder chamber 6 and the powder chamber connecting seat 9 are both installed in the powder chamber tube 12. As shown in fig. 6, a communicating cavity is arranged in the powder chamber seat 9, an integrally formed air-entraining pipe 7 is arranged on one side of the powder chamber 6 close to the powder chamber seat 9, one end of the air-entraining pipe 7 enters the powder chamber 6, and the other end enters the communicating cavity. The powder chamber 6 is in clearance fit with the powder chamber tube 12, an external thread is arranged at one end of the air entraining tube 7, which is exposed out of the powder chamber 6, an internal thread hole 15 which can be in threaded connection with the air entraining tube 7 is arranged on the powder chamber seat 9, and the internal thread hole 15 is communicated with the communicating cavity. During installation, the gunpowder chamber 6 is plugged into the gunpowder chamber pipe 12, and the gunpowder chamber 6 and the gunpowder chamber seat 9 are connected and fixed in a screwing mode. In order to facilitate screwing or pinching of the powder chamber 6 and the powder chamber holder 9, a screwing nut 13 is disposed at the outer wall of the end of the powder chamber 6 far away from the powder chamber holder 9 in this embodiment, and a screwing nut 13 is also disposed at the outer wall of the end of the powder chamber holder 9 far away from the powder chamber 6.
In this embodiment, the air duct 4, the fuze duct 10 and the air duct seat 11 are all provided with two and symmetrically distributed. The air duct base 11 is fixed on the large-caliber side of the tail jet pipe 5, and an ejector pipe is arranged in the air duct base 11 and used for ejecting air to turbine blades of the turbojet engine. One end of the air duct 4 is communicated with the communication cavity, and the other end is led to the air duct base 11 and communicated with the jet pipe. One end of the letter guiding pipe 10 is communicated with the communicating cavity, and the other end of the letter guiding pipe is communicated with the outside of the tail nozzle 5.
After the tail nozzle 5 structure of the embodiment is adopted, the starting flow of the turbojet engine is as follows:
after the engine meets the ignition condition, the gunpowder in the gunpowder chamber 6 is detonated through the ignition tube 10, the gunpowder burns rapidly, the volume expands rapidly and generates high-temperature and high-pressure gas, the high-temperature and high-pressure gas enters the gas guide tube seat 11 after passing through the gas guide tube 7, the gunpowder chamber seat 9 and the gas guide tube 4, and flows into the jet tube in the gas guide tube seat to be ejected to the turbine blade at a high speed, so that the turbine blade is pushed to rotate in an accelerating way, and the rotation of the air inlet blade is driven to form stable air flow, so that the engine can quickly establish circulation balance in a short time. After the engine is started stably, the engine reaches the working rotation speed rapidly by rapidly oiling.
The starting scheme can adapt to high-altitude conditions, effectively reduces maintenance cost, improves installation operability, reduces the appearance space of the turbojet engine, and can also reduce engine cost.
The above embodiments are only for illustrating the concept of the present invention and not for limiting the protection of the claims of the present invention, and all the insubstantial modifications of the present invention using the concept shall fall within the protection scope of the present invention.

Claims (9)

1. The structure of the tail jet pipe of the aviation turbojet engine comprises the tail jet pipe and a quick starting device, and is characterized in that the quick starting device comprises a powder chamber pipe, a powder chamber connecting seat, a letter guiding pipe, a gas guiding pipe and a gas guiding pipe connecting seat; the gas-guiding device is characterized in that the powder chamber pipe and the gas-guiding pipe seat are both fixed on the tail nozzle, the powder chamber and the powder chamber seat are both installed in the powder chamber pipe, a communication cavity is formed in the powder chamber seat, one end of the gas-guiding pipe is communicated with the communication cavity, the other end of the gas-guiding pipe is communicated with the powder chamber, one end of the gas-guiding pipe is communicated with the communication cavity, the other end of the gas-guiding pipe is led to the outside of the tail nozzle, a jet pipe for jetting gas to a turbine blade of the turbojet engine is arranged in the gas-guiding pipe seat, one end of the gas-guiding pipe is communicated with the communication cavity, and the other end of the gas-guiding pipe seat is led to the gas-guiding pipe seat and is communicated with the jet pipe.
2. The structure of an aviation turbojet engine tail nozzle according to claim 1, wherein the diameter of the tail nozzle is gradually reduced from one end to the other end, and the air duct base is fixed at the outer wall of the large-caliber end of the tail nozzle.
3. The structure of an aviation turbojet engine tail nozzle according to claim 2, wherein an integrally formed flange is arranged at the outer wall of the large-caliber end of the tail nozzle.
4. The structure of the tail nozzle of the aviation turbojet engine according to claim 1, wherein the gunpowder chamber pipe is arranged in the tail nozzle, and the outer wall of the gunpowder chamber pipe is fixedly connected with the inner wall of the tail nozzle through reinforcing ribs.
5. The structure of an aviation turbojet engine tail nozzle according to claim 1, wherein the powder chamber is positioned in a powder chamber pipe and is in clearance fit with the powder chamber pipe, the air bleed pipe and the powder chamber are integrally formed, one end of the air bleed pipe, which is exposed out of the powder chamber, is provided with external threads, the powder chamber seat is provided with an internal threaded hole which can be in threaded connection with the air bleed pipe, and the internal threaded hole is communicated with the communicating cavity.
6. The structure of an aviation turbojet engine tail nozzle of claim 4, wherein a screw cap is provided at the outer wall of the end of the powder chamber away from the powder chamber seat.
7. The structure of an aviation turbojet engine tail nozzle of claim 4, wherein a screw cap is provided at the outer wall of the end of the powder chamber socket away from the powder chamber.
8. The structure of an aviation turbojet engine tail nozzle according to claim 1, wherein two guide tubes are symmetrically distributed.
9. The structure of the tail nozzle of the aviation turbojet engine as claimed in claim 1, wherein two air ducts are symmetrically distributed, and two air duct seats are symmetrically distributed.
CN202310342911.1A 2023-03-28 2023-03-28 Structure of tail nozzle of aviation turbojet engine Pending CN116291942A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310342911.1A CN116291942A (en) 2023-03-28 2023-03-28 Structure of tail nozzle of aviation turbojet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310342911.1A CN116291942A (en) 2023-03-28 2023-03-28 Structure of tail nozzle of aviation turbojet engine

Publications (1)

Publication Number Publication Date
CN116291942A true CN116291942A (en) 2023-06-23

Family

ID=86799593

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310342911.1A Pending CN116291942A (en) 2023-03-28 2023-03-28 Structure of tail nozzle of aviation turbojet engine

Country Status (1)

Country Link
CN (1) CN116291942A (en)

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