Multi-working-condition combustion chamber head structure and aero-engine

Abstract

The application discloses a multi-working-condition combustion chamber head structure and an aero-engine, wherein the multi-working-condition combustion chamber head structure comprises a fuel nozzle, a radial swirler and a slanting hole swirler; the fuel nozzle comprises an oil injection cone surface and an oil injection end surface, the oil injection end surface is provided with a first oil injection hole, and the oil injection cone surface is provided with a second oil injection hole; the radial swirler is provided with a limiting groove, and a reset spring is elastically pressed in the limiting groove; the slanting hole swirler is rotatably installed in the limiting groove, the slanting hole swirler comprises an oil injection area and a swirling area, the oil injection area comprises a fuel outlet corresponding to the oil injection end surface and a lateral oil passage hole corresponding to the second oil injection hole, and the swirling area is provided with a plurality of groups of slanting holes; when the engine is in a small state working condition, the slanting hole swirler is rotated to a state that the lateral oil passage hole avoids the second oil injection hole; and when the engine is in a large state working condition, the slanting hole swirler is rotated to a state that the lateral oil passage hole faces the second oil injection hole. The multi-working-condition combustion chamber head structure provided by the application can realize self-adaptive adjustment of fuel distribution.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine combustion chamber, in particular to a multi-working-condition combustion chamber head structure and an aero-engine adopting the same. BACKGROUND

[0002] The combustion chamber head structure is an important component of the combustion chamber of a gas turbine engine, and its working performance directly affects the performance of the combustion chamber in terms of flameout, combustion and pollution emission. At present, the traditional combustion chamber head structure mainly consists of a fuel nozzle and a stabilizer, the stabilizer is fixed to the flame tube by welding, the stabilizer usually adopts a bowl-shaped bluff body structure, and the air passing through the stabilizer has multiple streams, part of the air flow enters the main combustion zone from the narrow gap outside the stabilizer, forming a recirculation zone downstream of the stabilizer; part of the air flows out through the cooling holes on the stabilizer, which is used to cool the inner wall of the stabilizer and blow off the carbon deposit; the nozzle of the fuel nozzle is inserted into the center of the stabilizer, and the end face of the nozzle directly contacts the high-temperature gas in the flame tube.

[0003] However, the fuel atomization quality of the traditional combustion chamber head structure mainly depends on the design performance of the fuel nozzle, and the recirculation zone formed by the stabilizer cannot generate strong swirl, so the air intake amount is limited, otherwise the air flow velocity in the main combustion zone will be high, which will affect the ignition performance and the combustion efficiency in the small state. However, because the air intake amount is small, the oil-gas ratio in the main combustion zone is too rich, the combustion is incomplete, which will also cause serious carbon deposition at the head of the flame tube, and a large amount of smoke particles will be generated in the main combustion zone, causing exhaust pollution; in addition, the fuel atomization quality and the oil-gas mixing cannot realize the fuel distribution control in different working conditions, which cannot meet the requirements of the main combustion zone concentration field of the low-pollution combustion chamber. SUMMARY

[0004] The present application primarily provides a multi-working-condition combustion chamber head structure to solve the technical problem that the existing combustion chamber head structure cannot meet the fuel distribution requirements of the engine in different working conditions.

[0005] The present application also provides an aero-engine adopting the above-mentioned multi-working-condition combustion chamber head structure.

[0006] According to one aspect of the present application, a multi-working-condition combustion chamber head structure is provided, which comprises a fuel nozzle, a radial swirler and an inclined hole swirler.

[0007] The fuel nozzle is used to be installed at the center position of the head of the flame tube, the nozzle head of the fuel nozzle comprises a fuel injection taper surface gradually tapering along the fuel injection direction and a fuel injection end surface connected with the end of the fuel injection taper surface and arranged towards the axial direction of the flame tube, a first fuel injection hole is arranged on the fuel injection end surface, and a plurality of second fuel injection holes are arranged around the fuel injection end surface on the fuel injection taper surface.

[0008] The radial swirler is used to connect with the head of the flame tube, and a limiting groove for rotating the bevel hole swirler by a preset angle is arranged in the radial swirler, and a return spring is elastically pressed in the limiting groove;

[0009] The bevel hole swirler is rotatably installed in the radial swirler, and the bevel hole swirler comprises an oil injection area and a rotational flow area arranged at the outer periphery of the oil injection area, the oil injection area comprises a fuel outlet arranged corresponding to the oil injection end face and a lateral oil passage arranged corresponding to the second oil injection hole, and the rotational flow area is arranged with a plurality of groups of bevel holes for forming rotational airflow at the outer periphery of the oil injection area.

[0010] The return spring is used to drive the bevel hole swirler to rotate to a state that the lateral oil passage avoids the second oil injection hole when the engine is in a small state working, and the plurality of groups of bevel holes are used to generate reverse deflection force to compress the return spring and drive the bevel hole swirler to rotate to a state that the lateral oil passage directly faces the second oil injection hole when the engine is in a large state working.

[0011] Preferably, the oil injection area comprises a heat shield matched with the oil injection cone face and arranged around the oil injection cone face, the lateral oil passage is arranged on the heat shield, and the end of the heat shield has an opening to form the fuel outlet;

[0012] The heat shield has a gap relative to the fuel nozzle and forms a heat insulation cavity through the gap, and the bevel hole swirler further comprises a plurality of heat insulation rotational flow holes arranged around the heat insulation cavity, and the heat insulation rotational flow holes are used to form rotational airflow in the heat insulation cavity.

[0013] Preferably, the air inlet end of the bevel hole swirler is provided with a gas collection cavity which is contracted in the air inlet direction, and the air outlet end of the bevel hole swirler is provided with an air outlet groove which is expanded in the air outlet direction.

[0014] The plurality of groups of bevel holes comprise a plurality of first bevel holes and a plurality of second bevel holes which are arranged around the oil injection area, the air inlet ends of the first bevel holes and the second bevel holes are communicated with the gas collection cavity, the air outlet ends of the first bevel holes and the second bevel holes are communicated with the air outlet groove, and the rotational direction of the rotational airflow formed by the plurality of first bevel holes is opposite to that of the rotational airflow formed by the plurality of second bevel holes.

[0015] Preferably, the bevel hole cyclone is provided with two air outlet grooves in the radial direction, the two air outlet grooves are respectively provided as a first air outlet groove and a second air outlet groove in the direction outward in the radial direction, the air flow of the first bevel hole and the second bevel hole in the first air outlet groove is used to form an inner shear layer rotating jet, the air flow of the first bevel hole and the second bevel hole in the second air outlet groove is used to form an outer shear layer rotating jet, and the rotating directions of the inner shear layer rotating jet and the outer shear layer rotating jet are the same or opposite.

[0016] Preferably, the air outlet directions of the first bevel hole and the second bevel hole in the first air outlet groove are both arranged towards the oil injection area, and the air outlet directions of the first bevel hole and the second bevel hole in the second air outlet groove are both arranged away from the oil injection area.

[0017] Preferably, the radial distance between the inner opening ring and the outer opening ring of the first air outlet groove is greater than the radial distance between the inner opening ring and the outer opening ring of the second air outlet groove.

[0018] Preferably, the depth of the first air outlet groove is greater than the depth of the second air outlet groove.

[0019] Preferably, the multi-working-condition combustion chamber head structure further comprises a cover plate, an axial end surface of the radial swirler away from the flame tube is provided with a positioning groove, an outer periphery of the bevel hole cyclone is provided with a positioning ring rotatably embedded in the positioning groove, and the cover plate is connected with the radial swirler and is used to press the bevel hole cyclone in the positioning groove in the axial direction.

[0020] The limiting groove is opened on the side wall of the positioning groove and penetrates through to the outside of the radial swirler in the radial direction of the radial swirler, the positioning ring is provided with a driving part extending to the limiting groove in the radial direction and abutting against the reset spring, and the cover plate is further provided with a baffle plate protruding to the radial outside of the radial swirler, the baffle plate is used to cover the reset spring and limit the maximum stroke of the reset spring compressed by the driving part.

[0021] Preferably, the bevel hole cyclone has a radial activity amount relative to the radial swirler.

[0022] As a second aspect, the application further provides an aero-engine comprising the multi-working-condition combustion chamber head structure.

[0023] The application has the following beneficial effects:

[0024] The slanting hole swirler in the multi-working condition combustion chamber head structure can be rotatably installed in the radial swirler, the elastic reset force of the reset spring is applied to the slanting hole swirler in the circumferential direction, and the deflection force generated by the rotating airflow of the slanting hole swirler is opposite to the elastic force of the reset spring; when the engine is in a small state, the reverse deflection force of the rotating airflow generated by the slanting hole swirler is smaller than the elastic force of the reset spring, at this time, the slanting hole swirler is rotated to the state of avoiding the second oil injection hole under the action of the elastic force of the reset spring, so that most of the fuel injected by the fuel nozzle is concentrated to the central axis of the flame tube through the fuel outlet, effectively improving the point extinction performance and combustion efficiency of the engine in the small state; when the engine is in a large state, the reverse deflection force of the rotating airflow generated by the slanting hole swirler is greater than the elastic force of the reset spring, at this time, the slanting hole swirler is rotated to the state of facing the second oil injection hole under the action of the reverse deflection force and compresses the reset spring, so that the fuel injected by the second oil injection hole can be injected towards the rotating airflow area through the lateral oil passage, the fuel and the rotating airflow in the rotating airflow area are fully mixed, the fuel is evenly distributed in the flame tube, and the gaseous pollutant emission and the hot spot temperature of the combustion chamber outlet of the flame tube are effectively reduced. Therefore, the multi-working condition combustion chamber head structure can adaptively adjust the position relationship between the lateral oil passage and the second oil injection hole, improve the airflow structure and fuel concentration distribution of the combustion chamber head, realize different fuel distribution of the engine under different working conditions, effectively solve the flame stability problem in the small state and the pollution emission contradiction and the hot spot temperature problem of the combustion chamber outlet in the large state.

[0025] Secondly, the fuel nozzle is arranged on the slanting hole swirler cover, and the rotating airflow generated by the slanting hole swirler is used to cool the slanting hole swirler itself, so that the problem of nozzle coking is avoided, and the service life and oil injection precision of the fuel nozzle are improved.

[0026] In addition to the purposes, features and advantages described above, the present application has other purposes, features and advantages. The present application will be further described below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0027] The drawings constituting a part of this application are used to provide a further understanding of the present application, the schematic embodiments of the present application and the description thereof are used to explain the present application, and do not constitute an improper limitation on the present application. In the drawings:

[0028] Figure 1 The assembly structure schematic view of the multi-working condition combustion chamber head structure provided for the embodiments of the present application;

[0029] Figure 2 For Figure 1Structure diagram of fuel nozzle in multi-working condition combustion chamber head structure shown;

[0030] Figure 3 For Figure 1 Structure diagram of bevel hole swirler in multi-working condition combustion chamber head structure shown;

[0031] Figure 4 For Figure 1 Flow field diagram of multi-working condition combustion chamber head structure shown;

[0032] Figure 5 For Figure 1 Perspective view of multi-working condition combustion chamber head structure shown;

[0033] Figure 6 For Figure 5 Perspective view of multi-working condition combustion chamber head structure along another angle shown;

[0034] Figure 7 For Figure 6 Exploded view of multi-working condition combustion chamber head structure shown.

[0035] Legend:

[0036] 100, multi-working condition combustion chamber head structure; 200, flame tube; 300, combustion chamber casing;

[0037] 1, fuel nozzle; 11, oil injection end face; 111, first oil injection hole; 12, oil injection cone face; 121, second oil injection hole;

[0038] 2, radial swirler; 21, limiting groove; 22, positioning groove; 23, radial swirler hole;

[0039] 3, bevel hole swirler; 31, heat shield; 311, fuel outlet; 312, lateral oil passage hole; 313, heat insulation cavity; 32, bevel hole; 321, first bevel hole; 322, second bevel hole; 33, heat insulation swirler hole; 34, gas collection cavity; 35, gas outlet groove; 351, first gas outlet groove; 352, second gas outlet groove; 36, mounting hole; 361, chamfer; 37, positioning ring; 371, driving part;

[0040] 4, return spring; 5, cover plate; 51, baffle; 6, flow guide plate. DETAILED DESCRIPTION

[0041] The embodiments of the present application will be described in detail with reference to the drawings, of which the embodiments are shown by way of illustration, and thus the present application can be implemented in various ways. The same or similar components are denoted by the same or similar reference numerals throughout the drawings and a repeated description thereof will be omitted. The embodiments described below are merely exemplary, and are used to explain the present application, and should not be construed as limiting the present application.

[0042] It is to be understood that the phraseology or terminology herein includes the word "comprise" or variations such as "comprises" or "comprising", unless expressly specified to the contrary, is intended to cover the presence of successively stated integers, steps, or components "including" an or more additional integer, steps, components, or combinations thereof. It is to be understood that the terminology "connected to" or "connected with" used herein includes both direct connection to, and indirect connection via an intermediary. The term "and / or" used herein includes any and all combinations of one or more of the associated listed items. The terms "first", "second", and the like used in the description and the claims denote differentia, and do not necessarily describe a particular order or sequence.

[0043] Figures 1 to 7 The multi-condition combustion chamber head structure provided by the embodiments of the present application is shown, which is used for installing at the head of a flame tube and providing fuel and combustion gas for the combustion chamber inside the flame tube to form a high-speed rotating gas mixture and improve the combustion effect.

[0044] As shown in Figure 1 The multi-condition combustion chamber head structure 100 includes a fuel nozzle 1, a radial swirler 2, and a slant-hole swirler 3. The fuel nozzle 1 is connected with a combustion chamber case 300 at the oil inlet end, and is installed at the center of the head of a flame tube 200 at the oil outlet end to spray fuel into the combustion chamber inside the flame tube 200. The radial swirler 2 is connected with the head of the flame tube 200 and is arranged around the outer periphery of the fuel nozzle 1, and is used to provide a rotating gas flow in the radial direction into the flame tube 200. The slant-hole swirler 3 is installed in the radial swirler 2 and covers the fuel nozzle 1, and is used to provide a rotating gas flow in the axial direction into the flame tube 200.

[0045] As shown in Figure 2As shown, the spray head of the fuel nozzle 1 comprises a spray cone surface 12 gradually tapered in the spray direction and a spray end surface 11 connected with the end of the spray cone surface 12 and arranged axially towards the flame tube 200, i.e. the spray head of the fuel nozzle 1 is provided in the shape of a circular truncated cone, the end of which is provided as the spray end surface 11 arranged axially towards the flame tube 200, and the position close to the end is provided as the spray cone surface 12 arranged obliquely outwards in the radial direction of the flame tube 200, the spray end surface 11 is provided with first spray holes 111, and the spray cone surface 12 is provided with a plurality of second spray holes 121 arranged around the spray end surface 11.

[0046] Please refer to Figure 6 and Figure 7 , the radial swirler 2 is provided with a limiting groove 21 for rotating the bevel hole swirler 3 by a preset angle, the limiting groove 21 is elastically pressed with a reset spring 4, and the reset spring 4 abuts against the bevel hole swirler 3 and is used to apply an elastic reset force in the circumferential direction to the bevel hole swirler 3.

[0047] Please refer to Figure 3 , the bevel hole swirler 3 is rotatably installed in the radial swirler 2, the bevel hole swirler 3 comprises a spray area and a swirl area arranged at the outer periphery of the spray area, the spray area comprises a fuel outlet 311 arranged corresponding to the spray end surface 11 and a lateral oil passage hole 312 arranged corresponding to the second spray hole 121, and the swirl area is provided with a plurality of groups of bevel holes 32 for forming a rotating airflow at the outer periphery of the spray area.

[0048] Specifically, the reset spring 4 is used to drive the bevel hole swirler 3 to rotate to a state that the lateral oil passage hole 312 avoids the second spray hole 121 when the engine is in a small state working, so as to guide most of the fuel sprayed by the fuel nozzle 1 to be sprayed along the fuel outlet 311 to the central axis of the flame tube 200; the plurality of groups of bevel holes 32 are used to generate a reverse deflection force to compress the reset spring 4 and drive the bevel hole swirler 3 to rotate to a state that the lateral oil passage hole 312 directly faces the second spray hole 121 when the engine is in a large state working, so as to guide the fuel sprayed by the second spray hole 121 to be sprayed along the lateral oil passage hole 312 towards the swirl area. It should be understood that the small state working of the engine refers to the operating mode in which only minimum thrust is required, and the large state working refers to the operating mode in which the working load is met. When the engine is an aero-engine, the small state working includes the ignition state, the ground idle state, the flight idle state, the approach landing state and the warm-up state, etc., and the large state working includes the take-off state, the cruising state and the afterburning state, etc.

[0049] The slant-hole swirler 3 in the multi-working condition combustion chamber head structure 100 is rotatably installed in the radial swirler 2, and the elastic reset force of the reset spring 4 is applied to the slant-hole swirler 3 in the circumferential direction, and the deflection force of the rotating airflow generated by the slant-hole swirler 3 is opposite to the elastic force of the reset spring 4. When the engine is in a small state, the reverse deflection force of the rotating airflow generated by the slant-hole swirler 3 is smaller than the elastic force of the reset spring 4, and at this time, the slant-hole swirler 3 is rotated to the state of avoiding the second oil injection hole 121 under the action of the elastic force of the reset spring 4, so that most of the fuel injected by the fuel nozzle 1 is concentrated along the fuel outlet 311 to the central axis of the flame tube 200, effectively improving the point extinction performance and combustion efficiency of the engine in a small state. When the engine is in a large state, the reverse deflection force of the rotating airflow generated by the slant-hole swirler 3 is greater than the elastic force of the reset spring 4, and at this time, the slant-hole swirler 3 compresses the reset spring 4 and rotates to the state of facing the second oil injection hole 121 under the action of the reverse deflection force, so that the fuel injected by the second oil injection hole 121 can be injected along the lateral oil passage hole 312 towards the swirling area, so that the fuel and the rotating airflow in the swirling area are fully mixed, ensuring that the fuel is uniformly distributed in the flame tube 200, thereby effectively reducing the gaseous pollutant emissions and the hot spot temperature at the outlet of the combustion chamber of the flame tube 200. Therefore, the multi-working condition combustion chamber head structure 100 can adaptively adjust the positional relationship between the lateral oil passage hole 312 and the second oil injection hole 121, improve the combustion chamber head airflow structure and fuel concentration distribution, realize different fuel distribution of the engine under different working conditions, and effectively solve the flame stability problem in a small state and the pollution emission contradiction and the hot spot temperature problem at the outlet of the combustion chamber in a large state.

[0050] Secondly, the slant-hole swirler 3 covers the fuel nozzle 1, and the rotating airflow generated by the slant-hole swirler 3 is used to cool the slant-hole swirler 3 itself, effectively avoiding the direct exposure of the fuel nozzle 1 to the high-temperature combustion gas in the flame tube 200, avoiding the problem of nozzle coking, thereby improving the service life and oil injection precision of the fuel nozzle 1.

[0051] Please combine Figure 3 and Figure 5The fuel injection area comprises a heat shield 31 arranged around the fuel injection cone surface 12, the heat shield 31 is matched with the fuel injection cone surface 12, that is, the heat shield 31 is arranged in a tapered or hemispherical structure which is gradually contracted in the direction towards the flame tube 200, the lateral oil passage hole 312 is arranged on the heat shield 31, and the end of the heat shield 31 has an opening to form the fuel outlet 311. Further, the heat shield 31 has a gap relative to the fuel nozzle 1 and forms a heat insulation cavity 313 through the gap, and the bevel hole swirler 3 further comprises a plurality of heat insulation swirler holes 33 arranged around the heat insulation cavity 313, the heat insulation swirler holes 33 are used to form rotating air flow in the heat insulation cavity 313.

[0052] In use, the rotating air flow is formed in the heat insulation cavity 313 through the heat insulation swirler holes 33, the rotating air flow can be accelerated by the contraction structure of the heat shield 31, so that the rotating air flow can rotate at high speed to cover the nozzle head of the fuel nozzle 1, which can avoid the high-temperature combustion gas in the flame tube 200 flowing back to the fuel nozzle 1 to avoid coking of the fuel nozzle 1, and on the other hand, the high-speed rotating air flow can also strengthen the atomization effect of the fuel sprayed by the fuel nozzle 1, so that the fuel and the incoming air can be quickly and uniformly mixed before entering the flame tube 200 for efficient combustion, thereby effectively reducing the emission of gaseous pollutants in the combustion chamber.

[0053] Preferably, the air inlet end of the bevel hole swirler 3 is provided with a gas collecting cavity 34 which is contracted in the air inlet direction, and the air outlet end of the bevel hole swirler 3 is provided with an air outlet groove 35 which is expanded in the air outlet direction; a plurality of bevel holes 32 comprises a plurality of first bevel holes 321 and a plurality of second bevel holes 322 which are arranged around the fuel injection area, the air inlet ends of the first bevel holes 321 and the second bevel holes 322 are communicated with the gas collecting cavity 34, the air outlet ends of the first bevel holes 321 and the second bevel holes 322 are communicated with the air outlet groove 35, and the rotating directions of the rotating air flow formed by the plurality of first bevel holes 321 are opposite to the rotating directions of the rotating air flow formed by the plurality of second bevel holes 322.

[0054] The gas collection cavity 34 is used to slow down and pressurize the gas flow entering the inclined hole cyclone 3, improve the stability of the gas flow, and stabilize the uniform entry into different inclined holes. The gas outlet groove 35 is used to form an expansion channel to guide the gas flow, ensure that the gas flow fully covers the gas outlet end of the inclined hole cyclone 3, and improve the cooling effect and oil-gas mixing effect. Secondly, a plurality of first inclined holes 321 are arranged along a first circle, a plurality of second inclined holes 322 are arranged along a second circle, the diameters of the first circle and the second circle are different, and the rotation direction of the rotating gas flow formed by the plurality of first inclined holes 321 is opposite to that of the rotating gas flow formed by the plurality of second inclined holes 322. The two rotating gas flows form a shear layer rotating jet under the guidance of the expansion channel of the gas outlet groove 35, further improving the cooling effect and oil-gas mixing effect.

[0055] Please refer to Figure 3 and Figure 4 , the inclined hole cyclone 3 is provided with two gas outlet grooves 35 in the radial direction, and the first inclined hole 321 and the second inclined hole 322 are arranged in the two gas outlet grooves 35. The two gas outlet grooves 35 are respectively arranged as a first gas outlet groove 351 and a second gas outlet groove 352 in the radial direction outward. The gas flow of the first inclined hole 321 and the second inclined hole 322 in the first gas outlet groove 351 is used to form an inner shear layer rotating jet, and the gas flow of the first inclined hole 321 and the second inclined hole 322 in the second gas outlet groove 352 is used to form an outer shear layer rotating jet. The rotation directions of the inner shear layer rotating jet and the outer shear layer rotating jet are the same or opposite, and a central recirculation zone is formed in the flame tube 200. The cooperation of the inner shear layer rotating jet and the outer shear layer rotating jet can realize good fuel dispersion, improve the fuel atomization effect, and enable the fuel sprayed by the fuel nozzle 1 to be efficiently atomized and evaporated in a very short distance, realize the full combustion of the fuel in the flame tube 200, and form an expansion type flame stabilization zone, so that the oil-gas mixture is uniformly distributed in the flame tube 200, ensuring the stability and efficiency of combustion, controlling the main combustion zone temperature, and reducing the pollution emission of the combustion chamber.

[0056] Further, the inner ring groove wall of the first gas outlet groove 351 is formed by the heat shield 31, so that the gas sprayed by the first gas outlet groove 351 can fully cover the outer peripheral wall of the heat shield 31, thereby cooperating with the rotating gas flow formed by the heat shield cyclone hole 33 to realize double-layer gas cooling of the heat shield 31, simplify the structure, and further strengthen the heat shielding effect of the fuel nozzle 1.

[0057] Preferably, the first and second bevel holes 321 and 322 in the first air outlet slot 351 are arranged to direct the rotating jet flow towards the fuel injection area, so that the rotating jet flow can be fully mixed with the fuel in the fuel injection area; the first and second bevel holes 321 and 322 in the second air outlet slot 352 are arranged to direct the rotating jet flow away from the fuel injection area, so that the rotating jet flow can be uniformly distributed to the outer periphery of the fuel injection area, guiding the fuel to diffuse outward and improving the combustion effect.

[0058] Preferably, the radial distance between the inner and outer opening circles of the first air outlet slot 351 is greater than the radial distance between the inner and outer opening circles of the second air outlet slot 352, that is, the radial distance between the inner and outer opening circles of the first air outlet slot 351 is greater, so that the rotating jet flow generated by the first air outlet slot 351 can flow more fully along the slot wall, further improving the cooling effect and oil-gas mixing effect, and avoiding the accumulation of carbon and coking on the first air outlet slot 351 due to the concentration of high-temperature gas at the nozzle position of the fuel nozzle 1. Secondly, since the radial distance between the inner and outer opening circles of the second air outlet slot 352 is smaller, the rotating jet flow generated by the second air outlet slot 352 can quickly enter the flame tube 200, increasing the airflow speed and enhancing the fuel diffusion effect.

[0059] Preferably, the depth of the first air outlet slot 351 is greater than the depth of the second air outlet slot 352. Similarly, the depth of the first air outlet slot 351 is greater, which can guide the airflow to flow along the slot wall, achieving a more sufficient cooling effect and oil-gas mixing effect; the depth of the second air outlet slot 352 is shallower, which can avoid excessive deceleration of the airflow and improve the airflow diffusion effect.

[0060] Further, the axial cross-section of the first and second air outlet slots 351 and 352 is approximately triangular, the bottom end is circular arc-shaped, and the opening expands outward at an angle of 60° to 150°, ensuring that the gas can flow along the slot wall of the air outlet slot 35, improving the flow guiding and cooling effect of the bevel hole cyclone 3.

[0061] Further, the first and second bevel holes 321 and 322 and the heat-insulating cyclone hole 33 have a diameter of 0.5mm to 4mm and a number of 6 to 32, and the deflection direction in the axial direction is between -60° and 60°, and the deflection direction in the radial direction is between -45° and 45°, avoiding excessive or insufficient deflection angles and ensuring that the rotating airflow meets the requirements.

[0062] Further, the fuel nozzle 1 has a contraction angle of 5°-85°, the second fuel injection holes 121 are arranged in one or more rows on the fuel injection cone surface 12, and the first fuel injection holes 111 are arranged in one or more rows on the fuel injection end surface 11, the diameters of the first fuel injection holes 111 and the second fuel injection holes 121 are 0.3mm-4mm, and the number of the first fuel injection holes 111 and the second fuel injection holes 121 is 3-30.

[0063] Further, the heat shield 31 has a contraction angle of 30°-90° and an axial length of 8mm-25mm, the fuel outlet 311 has a diameter of 8mm-30mm, the side oil passage 312 is arranged corresponding to the second fuel injection hole 121, and the diameter of the side oil passage 312 is 1mm-5mm. In other embodiments, the number of the side oil passage 312 can also be 1 / 2, 1 / 3, or 1 / 4 of the number of the second fuel injection hole 121.

[0064] Further, the oblique-hole swirler 3 is provided with a mounting hole 36 along the central axis for mounting the fuel nozzle 1, and the insertion end of the mounting hole 36 is provided with a chamfer 361 to guide the fuel nozzle 1 to be accurately inserted into the mounting hole 36.

[0065] Please refer to Figure 6 and Figure 7 , the multi-working-condition combustion chamber head structure 100 further comprises a cover plate 5, the axial end surface of the radial swirler 2 away from the flame tube 200 is provided with a positioning groove 22, the outer periphery of the oblique-hole swirler 3 is provided with a positioning ring 37 rotatably embedded in the positioning groove 22, the cover plate 5 is connected with the radial swirler 2 and is used to press the oblique-hole swirler 3 in the positioning groove 22 in the axial direction, so as to realize the axial and radial positioning of the oblique-hole swirler 3 relative to the radial swirler 2.

[0066] Further, the limiting groove 21 is arranged on the side wall of the positioning groove 22 and penetrates through the radial swirler 2 to the outside of the radial swirler 2 in the radial direction of the radial swirler 2, the positioning ring 37 is provided with a driving part 371 extending outward in the radial direction into the limiting groove 21 and abutting against the reset spring 4, and the cover plate 5 is further provided with a baffle plate 51 protruding outward in the radial direction of the radial swirler 2, the baffle plate 51 is used to cover the reset spring 4 and limit the maximum stroke of the reset spring 4 compressed by the driving part 371.

[0067] The baffle 51 not only prevents the return spring 4 from disengaging from the limiting groove 21, but also limits the maximum stroke of the drive unit 371 in compressing the return spring 4. This allows the oblique-cut cyclone separator 3 to precisely rotate to the state where the lateral oil passage 312 is directly opposite the second oil injection hole 121 when compressing the return spring 4 under the reverse deflection force generated by the rotating airflow, ensuring that the fuel injected from the second oil injection hole 121 can be quickly injected out along the lateral oil passage 312.

[0068] Preferably, the oblique-cut orifice cyclone separator 3 has a radial movement relative to the radial cyclone separator 2. This radial movement compensates for the difference in radial expansion between the combustion chamber casing 300 and the flame tube 200 due to temperature differences, ensuring that the fuel nozzle 1 can be accurately inserted into the mounting hole 36 of the oblique-cut orifice cyclone separator 3 in both cold and hot states. This gives it good displacement coordination and can prevent air leakage at the connection position of the fuel nozzle 1 on the combustion chamber casing 300.

[0069] Furthermore, the radial vortex generator 2 is also provided with a radial vortex hole 23, which is used to provide a rotating airflow radially into the flame tube 200.

[0070] like Figure 1 As shown, the multi-condition combustion chamber head structure 100 also includes a guide plate 6 installed in the radial vortex 2. The guide plate 6 is used to guide the rotating airflow generated by the radial vortex 2 to the side wall of the flame tube 200 to achieve cooling of the flame tube 200.

[0071] As a second aspect, the present invention also provides an aero-engine (not shown in the figure, the same below), including the above-mentioned multi-condition combustor head structure 100. Because the aero-engine adopts the multi-condition combustor head structure 100, it can adaptively adjust the airflow structure and fuel concentration distribution at the combustor head, realizing different fuel distributions under different operating conditions, effectively solving the flame stability problem during low-temperature operation and the pollution emission contradiction and combustor outlet hot spot temperature problem during high-temperature operation.

[0072] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A multi-condition combustion chamber head structure, characterized by, The fuel nozzle (1), the radial swirler (2) and the oblique hole swirler (3); The fuel nozzle (1) is arranged at the center of the head of the flame tube (200), the nozzle head of the fuel nozzle (1) comprises a fuel injection taper (12) gradually tapering along the fuel injection direction and a fuel injection end face (11) connected with the end of the fuel injection taper (12) and arranged along the axial direction of the flame tube (200), the fuel injection end face (11) is provided with a first fuel injection hole (111), and the fuel injection taper (12) is provided with a plurality of second fuel injection holes (121) arranged around the fuel injection end face (11); The radial swirler (2) is arranged at the head of the flame tube (200), the radial swirler (2) is provided with a limiting groove (21) for rotating the oblique hole swirler (3) by a preset angle, and the limiting groove (21) is elastically pressed by a reset spring (4); The oblique hole swirler (3) is rotatably arranged in the radial swirler (2), the oblique hole swirler (3) comprises a fuel injection area and a rotating flow area arranged at the outer periphery of the fuel injection area, the fuel injection area comprises a fuel outlet (311) arranged corresponding to the fuel injection end face (11) and a lateral oil passage (312) arranged corresponding to the second fuel injection hole (121), and the rotating flow area is provided with a plurality of groups of oblique holes (32) for forming rotating airflow at the outer periphery of the fuel injection area; The reset spring (4) is used for driving the oblique hole swirler (3) to rotate to the state that the lateral oil passage (312) avoids the second fuel injection hole (121) when the engine is in a small state; and the plurality of groups of oblique holes (32) are used for generating reverse deflection force to compress the reset spring (4) and drive the oblique hole swirler (3) to rotate to the state that the lateral oil passage (312) directly faces the second fuel injection hole (121) when the engine is in a large state.

2. The multi-condition combustion chamber head structure according to claim 1, characterized by, The fuel injection area comprises a heat shield (31) matched with the fuel injection taper (12) and arranged around the fuel injection taper (12), the lateral oil passage (312) is arranged on the heat shield (31), and the end of the heat shield (31) is provided with an opening to form the fuel outlet (311); The heat shield (31) has a gap relative to the fuel nozzle (1) and forms a heat insulation cavity (313) through the gap, and the oblique hole swirler (3) further comprises a plurality of heat insulation rotating flow holes (33) arranged around the heat insulation cavity (313), and the heat insulation rotating flow holes (33) are used for forming rotating airflow in the heat insulation cavity (313).

3. The multi-condition combustion chamber head structure according to claim 1, characterized by, The air inlet end of the oblique hole swirler (3) is provided with a converging air collection cavity (34) along the air inlet direction, and the air outlet end of the oblique hole swirler (3) is provided with a diverging air outlet groove (35) along the air outlet direction. The plurality of groups of oblique holes (32) include a plurality of first oblique holes (321) and a plurality of second oblique holes (322) which are all arranged around the oil injection area, the air inlet ends of the first oblique holes (321) and the second oblique holes (322) are all communicated with the gas collection cavity (34), the air outlet ends of the first oblique holes (321) and the second oblique holes (322) are all communicated with the air outlet groove (35), the rotational airflow formed by the plurality of first oblique holes (321) is opposite to the rotational airflow formed by the plurality of second oblique holes (322) in the rotational direction.

4. The multi-condition combustion chamber head structure according to claim 3, characterized by, The oblique hole rotational flow device (3) is provided with two air outlet grooves (35) in the radial direction, the two air outlet grooves (35) are respectively provided as a first air outlet groove (351) and a second air outlet groove (352) in the direction outward in the radial direction, the airflow of the first oblique holes (321) and the second oblique holes (322) in the first air outlet groove (351) is used to form an inner shear layer rotational jet, the airflow of the first oblique holes (321) and the second oblique holes (322) in the second air outlet groove (352) is used to form an outer shear layer rotational jet, the rotational directions of the inner shear layer rotational jet and the outer shear layer rotational jet are the same or opposite.

5. The multi-condition combustion chamber head structure according to claim 4, characterized by, The air outlet directions of the first oblique holes (321) and the second oblique holes (322) in the first air outlet groove (351) are all arranged towards the oil injection area, the air outlet directions of the first oblique holes (321) and the second oblique holes (322) in the second air outlet groove (352) are all arranged in the direction away from the oil injection area.

6. The multi-condition combustion chamber head structure according to claim 4, characterized by, The radial distance between the inner opening ring and the outer opening ring of the first air outlet groove (351) is greater than the radial distance between the inner opening ring and the outer opening ring of the second air outlet groove (352).

7. The multi-condition combustion chamber head structure according to claim 4, characterized by, The depth of the first air outlet groove (351) is greater than the depth of the second air outlet groove (352).

8. The multi-condition combustion chamber head structure according to claim 1, characterized by, The multi-working-condition combustion chamber head structure further includes a cover plate (5), an axial end surface of the radial rotational flow device (2) away from the flame tube (200) is provided with a positioning groove (22), an outer periphery of the oblique hole rotational flow device (3) is provided with a positioning ring (37) which is rotatably embedded in the positioning groove (22), the cover plate (5) is connected with the radial rotational flow device (2) and is used to press the oblique hole rotational flow device (3) in the positioning groove (22) in the axial direction; The limiting groove (21) is opened on the side wall of the positioning groove (22) and penetrates through to the outside of the radial rotational flow device (2) in the radial direction of the radial rotational flow device (2), the positioning ring (37) is provided with a driving part (371) which extends outward in the radial direction to the limiting groove (21) and abuts against the reset spring (4), the cover plate (5) is further provided with a baffle (51) which protrudes outward in the radial direction of the radial rotational flow device (2), the baffle (51) is used to cover the reset spring (4) and limit the maximum stroke of the reset spring (4) compressed by the driving part (371).

9. The multi-condition combustion chamber head structure according to claim 1 or 8, characterized by, The oblique hole rotational flow device (3) has a radial activity amount relative to the radial rotational flow device (2).

10. An aeroengine characterised in that, A multi-condition combustion chamber head structure as claimed in any one of claims 1 to 9.

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