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CN-118129182-B - Flame tube with air inlet distortion resistance and combustion chamber

CN118129182BCN 118129182 BCN118129182 BCN 118129182BCN-118129182-B

Abstract

The invention discloses an air intake distortion resistant flame tube and a combustion chamber in the technical field of aeroengines, and the air intake distortion resistant flame tube comprises an annular tube body and a mixing unit arranged on the tube body, wherein the mixing unit comprises a first-stage vortex device fixedly arranged at the head of the tube body and a fuel nozzle which penetrates through the first-stage vortex device and is coaxially arranged with the first-stage vortex device and is used for conveying fuel into the tube body, a fairing used for covering the first-stage vortex device is arranged on the tube body, the air intake uniformity of the first-stage vortex device is controlled through an air inlet formed in the fairing, the size of the fairing is matched with that of the first-stage vortex device and is used for covering a single first-stage vortex device, the fairings are mutually independent, and compared with the mode of increasing the thickness of a blade of the vortex device or increasing an air inlet channel, and the like, the fairing can achieve larger rectifying benefit through smaller weight.

Inventors

  • LANG XUDONG
  • LI WEI
  • JIN HAILIANG
  • ZHANG RONGXING
  • DAI JINXIN
  • HUANG JING
  • LIU LIJUAN
  • ZHANG SHUHAO
  • LI YUANHAO

Assignees

  • 中国航发湖南动力机械研究所

Dates

Publication Date
20260505
Application Date
20240329

Claims (8)

  1. 1. The utility model provides an anti distortion flame tube that admits air, includes annular barrel (1) and installs the mixing unit on barrel (1), the equidistant opening (2) that have offered a plurality of confession gas mixture entering barrel (1) inner chamber of circumference direction along barrel (1) of the head of barrel (1), and the mixing unit that is used for forming the gas mixture is all installed to every opening (2) department of barrel (1), its characterized in that: The mixing unit comprises a primary swirler (31) fixedly arranged at the head of the cylinder body (1) and a fuel nozzle (32) which penetrates through the primary swirler (31) and is coaxially arranged with the primary swirler (31) and is used for conveying fuel into the cylinder body (1), wherein the primary swirler (31) is used for enabling air entering the cylinder body (1) from the outside to pass through the primary swirler (31) to form high-speed rotary jet flow and mix with the fuel sprayed by the fuel nozzle (32) to form mixed gas; A fairing (4) for covering the primary vortex device (31) is arranged on the cylinder body (1), the air inlet formed by the fairing (4) is used for controlling the air inlet uniformity of the primary vortex device (31), and the size of the fairing (4) is matched with that of the primary vortex device (31) so as to cover a single primary vortex device (31); The air inlet comprises a head air inlet (41) formed in the top of the fairing (4), the head air inlet (41) is circular, and an axis extension line of the primary vortex device (31) penetrates through the center of the head air inlet (41); The air inlet further comprises a plurality of side air inlets (42) which are formed in the side edge of the fairing (4) at equal intervals along the circumferential direction, the side air inlets (42) are inclined to the wall surface of the fairing (4) and are oriented towards the same direction as the blades of the primary vortex device (31), and the air entering the fairing (4) from the side air inlets (42) forms a rotational flow in the fairing (4) in the same direction as the rotational jet flow in the primary vortex device (31).
  2. 2. An intake distortion resistant flame tube as set forth in claim 1 wherein said side intake port (42) is not spaced from the bottom surface of said fairing (4) by a distance greater than the distance between the top surface of the intake area of said primary swirler (31) and the bottom surface of said fairing (4).
  3. 3. An intake distortion resistant burner as set forth in claim 1 wherein said side intake ports (42) are angled at no more than 30 ° from the wall of the location of their opening in the surface of the fairing (4).
  4. 4. The flame tube with the resistance to air intake distortion as set forth in claim 1, wherein the fairing (4) comprises a top, a transition portion (44) and a bottom in sequence from top to bottom, the top diameter is smaller than the bottom diameter, and the transition portion (44) is in a circular arc shape for smoothly transitioning the top and the bottom to adapt to airflow.
  5. 5. The flame tube with resistance to air intake distortion as set forth in claim 1, wherein a secondary swirler (33) is fixedly installed between the primary swirler (31) and the cylinder (1), the primary swirler (31) and the fairing (4) are fixedly installed on one surface of the secondary swirler (33) far away from the cylinder (1), and the secondary swirler (33) is used for forming high-speed rotary jet flow and secondary mixing of fuel oil at a position closer to the inner cavity of the cylinder (1) relative to the primary swirler (31).
  6. 6. The flame tube with the resistance to air intake distortion as set forth in claim 5, wherein a venturi (5) is fixedly installed between the outlet of the primary swirler (31) and the outlet of the secondary swirler (33), and the high-speed rotating jet flow interval generated by the primary swirler (31) and the secondary swirler (33) is increased under the condition that the interval between the primary swirler (31) and the secondary swirler (33) is not increased.
  7. 7. An intake distortion resistant cartridge as recited in claim 5, wherein the vanes of the secondary swirler (33) are rotated in a direction opposite to the direction of rotation of the primary swirler (31).
  8. 8. A combustion chamber comprising the flame tube with resistance to air intake distortion as claimed in any one of claims 1 to 7, and further comprising a casing (6) for mounting the cylinder (1) and a diffuser (7) mounted in the inner cavity of the casing (6), wherein the head of the cylinder (1) is mounted in the inner cavity of the casing (6) towards the diffuser (7).

Description

Flame tube with air inlet distortion resistance and combustion chamber Technical Field The invention relates to the technical field of aeroengines, in particular to an air inlet distortion resistant flame tube and a combustion chamber. Background With the progress of aeroengine technology, the power ratio/thrust ratio index of the engine is higher and higher, the power ratio of the current foreign advanced turboshaft engine is higher than 12, the future requirement is higher, the structural size of the combustion chamber is required to be smaller, more compact, the weight is lower, the oil-gas ratio is higher, the distance between the outlet of the engine diffuser and the burner flame tube head of the combustion chamber is required to be shortened, more fuel is required to burn in a certain space, the inlet air uniformity of the swirler is objectively reduced, and the requirement of the high-oil-gas-ratio combustion chamber on the inlet air uniformity of the swirler is higher. The prior improving of the air inlet uniformity of the flame tube head vortex device of the high-temperature-rise combustion chamber mainly has 2 technical directions: 1. the method is realized by improving the molded surface, the consistency of the blades and other measures of the guide blades in the air inlet channel of the vortex device; 2. a head fairing is arranged outside the flame tube head swirler to wrap the whole swirler (generally 2-level and 3-level swirlers) almost, and only one air inlet channel is reserved. The invention discloses a flame tube structure of an annular combustion chamber of a push-in aeroengine, which is characterized by comprising an outer fairing, a head assembly, an outer tube body and an inner tube body, wherein the inner tube body is arranged in the outer tube body and is coaxially arranged, the rear ends of the outer fairing are respectively connected to the wall surfaces of the outer tube body and the inner tube body, an outer ring and an inner ring of the rear end of the inner fairing in the head assembly are respectively connected with pressing grooves of the front ends of the outer tube body and the inner tube body, the head assembly comprises two ignition heads and a plurality of non-ignition heads, the two ignition heads are arranged on an upper semi-ring and are asymmetrically distributed, a single-stage axial-flow vortex is arranged in the ignition heads, a double-stage axial-flow vortex is arranged in the non-ignition heads, heat shields are arranged in the ignition heads and the non-ignition heads, and the rear ends of the heat shields are welded with the front ends of the inner fairing. For example, the Chinese patent application with publication number CN 117346182A discloses a combined cooling structure for a flame tube head and a vortex device, which comprises a combined cooling structure for forming a cooling air film by enabling cooling air to cling to the inner wall of a heat shield and then flow to the inner wall of an inner fairing to form the cooling air film, and forming the air film by the inner wall and the outer wall of a sleeve formed by expansion sections. The cooling gas discharged from the head cooling inclined hole is tightly attached to the inner wall of the heat shield to form a cooling gas film and then flows to the inner wall of the inner fairing to form a cooling gas film, the cooling gas can be tightly attached to the inner wall and the outer wall of the expansion section extending into the head of the flame tube to form a cooling gas film, and the expansion section is combined to form a structure from the contraction section to the heat shield to be thick and thin, so that the safety of protecting the space of the inner wall of the combustion chamber at the head of the flame tube by forming the gas film on the inner wall and the outer wall of the sleeve formed by the expansion section is ensured, and the problem that the cooling gas discharged by impact type diffusion cannot be tightly attached to the inner wall of the fairing of the combustion chamber at the head of the flame tube and the inner wall and the outer wall of the vortex device extending into the section to form the gas film protection is solved. In the above patent and patent application, the second mode of arranging the head fairing is adopted to improve the air intake uniformity, the whole fairing is adopted to cover the flame tube, so that the head size of the whole flame tube is increased, the weight of the flame tube is greatly increased, the compact flame tube and the weight reduction design are not facilitated, the improvement of the power-to-weight ratio/thrust-weight ratio of the engine is limited, and the scheme of improving the air intake uniformity of the swirler by improving the profile and the vane consistency of the guide vane in the air intake channel of the swirler is adopted, so that the radial size of the swirler is larger, and the design of the compact flame tube is not facilitated