Radial prewhirl nozzle stepless regulation system based on bevel gear

Abstract

The invention relates to a radial prewhirl nozzle stepless adjusting system based on a bevel gear, belongs to the technical field of aero-engine prewhirl system adjustment, and solves the problems of high failure rate and low reliability caused by the fact that an adjusting mechanism is continuously in a high-temperature environment in the prior art. The adjusting assembly comprises a hydraulic adjuster which is installed on the radial outer side of the outer duct inner casing; a drive shaft driven by an output of the hydraulic regulator and extending radially inward from the outer duct; a drive shaft bevel gear connected to a radially inner end of the drive shaft and rotating about a radially extending axis; the plurality of nozzle shafts are assembled with the pre-rotating nozzles, drive the pre-rotating nozzles to rotate and axially extend backwards; the nozzle shaft bevel gear is connected to the axial rear end of the nozzle shaft and rotates around the axis extending in the axial direction; wherein the driving shaft bevel gear is meshed with the nozzle shaft bevel gear, so that the hydraulic regulator drives the nozzle shaft.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engine pre-swirl system adjustment, and in particular to a radial pre-swirl nozzle stepless adjustment system based on bevel gears. Background Art

[0002] The preswirl system in an engine is the largest branch of the secondary air system, providing cooling air at the appropriate temperature and pressure for the turbine blades. It is one of the most critical subsystems of the air system. Future aircraft engines with variable cycle characteristics will have significantly different bleed air requirements in different states. Excessive preswirl system bleed air will increase power consumption and engine fuel consumption. Furthermore, the increasing number of adjustable components and complex combination adjustment rules in future variable cycle engines will lead to more complex air system boundary combinations and a higher degree of discretization of air path parameters. With variable geometry adjustment of main flow path components, the fixed geometry preswirl system design faces tremendous pressure to ensure proper cooling, rim sealing, and axial force control over a wider envelope. Preswirl system adjustment technology has attracted widespread attention due to its significant potential for improving engine economy and stability. However, the confined space and high temperatures within the aircraft engine disc cavity pose key limitations and challenges to the layout and reliable operation of the adjustment mechanism in the engineering application of adjustable preswirl systems.

[0003] In existing aircraft engines, the adjustment mechanism of the vane-type pre-swirl nozzle is usually set within a high-temperature internal disc cavity. Therefore, the adjustment mechanism is continuously in a high-temperature environment and is affected by the high temperature, resulting in a high failure rate and low reliability of the adjustment mechanism.

[0004] Therefore, in the technical field, there is a need for an aircraft engine pre-swirl system regulating mechanism with an improved layout, so as to improve the working reliability of the pre-swirl system regulating mechanism and extend its service life. Summary of the Invention

[0005] In order to solve the problem of reliable operation of the adjustment mechanism of the pre-swirl system of future aircraft engines, the present invention proposes a radial pre-swirl nozzle stepless adjustment system based on bevel gears, which can be applied to aircraft engines or gas turbines. The hydraulic regulator installed on the inner casing of the outer duct provides the adjustment driving force, and the reliable adjustment of the pre-swirl nozzle is achieved through the meshing transmission of the bevel gear device.

[0006] According to an embodiment of the present invention, there is provided a bevel gear-based radial pre-swirl nozzle stepless adjustment system, which is mounted to an engine assembly for adjusting the angle of a pre-swirl nozzle in the engine assembly, comprising an adjustment assembly;

[0007] The engine assembly includes: a combustion chamber defined by a combustion chamber casing; an outer duct radially outside the combustion chamber and defined by an outer duct inner casing; and a plurality of pre-swirl nozzles arranged in the pre-swirl channel and circumferentially around the engine axis;

[0008] The adjustment components include:

[0009] Hydraulic regulator, installed in the duct;

[0010] a drive shaft driven by the output of the hydraulic regulator and extending radially inward from the outer duct;

[0011] a drive shaft bevel gear connected to the radially inner end of the drive shaft and rotating about a radially extending axis;

[0012] A plurality of nozzle shafts are assembled with the pre-swirl nozzles and drive the pre-swirl nozzles to rotate, and extend axially backward;

[0013] a nozzle shaft bevel gear connected to the axial rear end of the corresponding nozzle shaft and rotating around an axially extending axis;

[0014] The driving shaft bevel gear is meshed with the nozzle shaft bevel gear, so that the hydraulic regulator drives the nozzle shaft (116) to rotate, thereby adjusting the angle of the pre-rotation nozzle through the nozzle shaft.

[0015] Optionally, the adjustment assembly further includes: a mounting seat fixed on the inner casing of the outer duct, and the hydraulic regulator is mounted on the mounting seat.

[0016] Optionally, the adjustment assembly also includes: an actuating rod and a connecting rod arranged in the axial direction; wherein, the front end of the actuating rod is connected to the output end of the hydraulic regulator, the rear end of the actuating rod is connected to the input end of the connecting rod, and the output end of the connecting rod is fitted to the radial outer end of the drive shaft; the output of the hydraulic regulator in the axial direction is converted into rotational drive via the actuating rod and the connecting rod, and then transmitted to the drive shaft.

[0017] Optionally, the drive shaft extends radially inward to the front cavity of the turbine disk of the engine assembly, and the drive shaft bevel gear arranged at the radial inner end of the drive shaft is located in the front cavity of the turbine disk; the nozzle shaft extends axially backward to the front cavity of the turbine disk, and the nozzle shaft bevel gear connected to the axial rear end of the nozzle shaft is located in the front cavity of the turbine disk.

[0018] Optionally, the drive shaft is configured to extend radially inward from the outer duct, pass through the turbine guide vane rear cooling cavity in the turbine guide vane of the engine assembly, and enter the turbine disk front cavity.

[0019] Optionally, the drive shaft is configured to extend radially inward from the outer duct, pass through the turbine guide vane rear cooling cavity and the air collecting cavity of the engine assembly in sequence, and enter the turbine disk front cavity.

[0020] Optionally, the adjustment assembly also includes: spur teeth, which are arranged on the outer periphery of the middle section of each nozzle shaft; a gear ring, which is an annular gear surrounding the engine axis and is located in the front cavity of the turbine disk of the engine assembly, and the teeth on the outer periphery of the gear ring are engaged with the spur teeth of each nozzle shaft; the synchronous adjustment of all pre-rotation nozzles is achieved through the engagement of the gear ring with the spur teeth of each nozzle shaft.

[0021] Optionally, the adjustment assembly also includes: two hydraulic regulators, which are respectively installed at circumferentially symmetrical positions on the inner casing of the outer duct through mounting seats; and two corresponding sets of drive shafts, drive shaft bevel gears and nozzle shaft bevel gears connected to the hydraulic regulators, and the nozzle shaft bevel gears are respectively fixed to two circumferentially symmetrical nozzle shafts.

[0022] Optionally, the number of nozzle shafts and pre-swirl nozzles is 24, which are symmetrically arranged at uniform intervals in the circumferential direction around the engine axis.

[0023] Compared with the prior art, the bevel gear-based radial pre-swirl nozzle stepless adjustment system provided by the present invention has at least the following beneficial effects.

[0024] 1. The present invention provides an adjustment driving force for the pre-swirl nozzle through a hydraulic system, which has high feasibility.

[0025] 2. This invention utilizes a hydraulic regulator mounted on the inner casing of the duct. Two hydraulic regulators are symmetrically mounted on the inner casing of the duct, with a gear ring ensuring synchronization of adjustment. This allows for synchronized adjustment of all pre-swirl nozzles. Compared to adjustment methods using multiple drive units, this improves synchronization.

[0026] 3. The present invention utilizes a drive shaft, drive shaft bevel gear, nozzle shaft, and nozzle shaft bevel gear to enable continuous movement driven by an actuator and connecting rod, thereby achieving stepless adjustment of the pre-swirl nozzle. Compared to existing throttle-based pre-swirl systems, which only achieve two-stage adjustment through valve opening and closing, the stepless adjustment of the present invention offers greater flexibility and adaptability.

[0027] 4. By installing the hydraulic regulator in the duct, the present invention allows for a lower operating temperature. The drive shaft passes through the turbine guide vane rear cooling cavity and into the turbine disc front cavity, thus preventing the impact of high-temperature combustion gases on the drive shaft. This provides greater reliability than methods where the regulating mechanism is located in a high-temperature environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. By referring to the drawings, the features and advantages of the present invention can be more clearly understood. The drawings are schematic and should not be understood as limiting the present invention in any way. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0029] Figure 1 Schematic diagram of a bevel gear-based radial pre-swirl nozzle stepless adjustment system according to an embodiment of the present invention.

[0030] Figure 2 This is a schematic diagram of the installation of a drive shaft in a turbine guide vane rear cooling cavity in a bevel gear-based radial pre-swirl nozzle stepless adjustment system according to an embodiment of the present invention.

[0031] Figure 3 It is a partially enlarged view of the nozzle shaft in the bevel gear-based radial pre-swirl nozzle stepless adjustment system provided according to an embodiment of the present invention.

[0032] Description of reference numerals:

[0033] 101, mounting seat;

[0034] 102. Hydraulic regulator;

[0035] 103, actuator rod;

[0036] 104, connecting rod;

[0037] 105. Drive shaft;

[0038] 106. Turbine guide vane rear cooling cavity;

[0039] 107. Turbine guide vanes;

[0040] 108. Turbine blades;

[0041] 109, gas collecting cavity;

[0042] 110a, left support plate of pre-spin channel;

[0043] 110b, right support plate of pre-spin channel;

[0044] 111, pre-spin channel;

[0045] 112. Drive shaft bevel gear;

[0046] 113. Nozzle shaft bevel gear;

[0047] 114, gear ring;

[0048] 115. Pre-swirl nozzle;

[0049] 116, nozzle shaft;

[0050] 117a, inner sealing grate teeth sealing ring;

[0051] 117b, inner sealed comb teeth;

[0052] 118a, external sealing grate teeth sealing ring;

[0053] 118b, externally sealed comb teeth;

[0054] 119. Pre-spin cavity;

[0055] 120, receiving hole;

[0056] 121, drum shaft;

[0057] 122, cover cavity;

[0058] 123. Turbine disc;

[0059] 124, air supply hole;

[0060] 125, cover plate;

[0061] 126. Turbine disc front cavity;

[0062] 127, outer duct inner casing;

[0063] 128, duct;

[0064] 129. Combustion chamber;

[0065] 130, high temperature gas;

[0066] 131. Combustion chamber casing;

[0067] 132. Straight teeth. DETAILED DESCRIPTION

[0068] In order to more clearly understand the above-mentioned objects, features and advantages of the present invention, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present invention and the features therein can be combined with each other without conflict.

[0069] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Therefore, the scope of protection of the present invention is not limited to the specific embodiments disclosed below.

[0070] The following is a detailed description of a radial pre-swirl nozzle stepless adjustment system based on a bevel gear according to an embodiment of the present invention, which is used to adjust the angle of the pre-swirl nozzle in the pre-swirl system. Figure 1 The left side in the figure is the front side, the right side is the rear side, the upward direction in the figure is the radially outward direction, the downward direction is the radially inward direction, the direction along the drum shaft 121 in the figure (i.e., the axis of the engine) is the axial direction, and the direction along the vertical direction in the figure is the radial direction. It should be understood that the direction setting is only schematic, and the direction needs to be adjusted accordingly at different viewing angles, and other directions can be set as needed.

[0071] like Figure 1 and Figure 2 As shown, according to an embodiment of the present invention, a bevel gear-based radial pre-swirl nozzle stepless adjustment system is provided. The system is mounted on an engine assembly and adjusts the pre-swirl nozzle in the engine assembly, including an adjustment assembly. This embodiment can be applied to aircraft engines and gas turbines. The bevel gear-based radial pre-swirl nozzle stepless adjustment system can also be a bevel gear-based radial pre-swirl nozzle stepless adjustment device.

[0072] The bevel gear-based radial pre-swirl nozzle stepless adjustment system provided in this embodiment is installed on an engine assembly, which includes a turbine disk 123, a drum shaft 121 formed by the turbine disk 123 extending forward from the center along the engine axis, turbine blades 108 arranged on the radial outside of the turbine disk 123, a combustion chamber casing 131 located in front of the turbine disk 123 and surrounding the drum shaft 121, an outer duct inner casing 127 surrounding the drum shaft 121 on the radial outside of the combustion chamber casing 131, a combustion chamber 129 between the radial outside of the combustion chamber casing 131 and the radial inside of the outer duct inner casing 127, an outer duct 128 defined by the outer duct inner casing 127 and located on the outside of the outer duct inner casing 127, a plurality of turbine guide vanes 107 located behind the combustion chamber 129 and circumferentially arranged around the drum shaft 121, and a turbine guide vane rear cooling cavity 106 formed in the turbine guide vanes 107. The turbine guide vanes 107 are fixedly mounted downstream of the combustion chamber 129. They guide the flow of high-temperature combustion gases through the channels formed between adjacent turbine guide vanes 107, deflecting the high-temperature combustion gases and enhancing their ability to perform work on the turbine rotor blades 108. A cover plate cavity 122 is formed on the axial front side of the turbine disk 123. Air supply holes 124 are formed in the turbine disk 123, extending radially and axially. These holes allow airflow from the cover plate cavity 122 on the front side of the turbine disk 123 to enter and cool the turbine rotor blades 108 radially outward of the turbine disk 123. The turbine guide vane rear cooling cavity 106 is a hollow cavity formed in the rear portion of the turbine guide vane 107.

[0073] like Figure 1As shown in the high-temperature gas flow direction 130, the high-temperature gas generated by the high-temperature combustion of the fuel in the engine is deflected from the combustion chamber 129 through the flow channels between adjacent turbine guide vanes 107, and then discharged to the axial rear side through the flow channels between adjacent turbine blades 108.

[0074] The engine assembly also includes radially arranged from the inside to the outside: an inner sealing grate 117b and an outer sealing grate 118b fixedly assembled to the outer periphery of the drum shaft 121; an inner sealing grate sealing ring 117a and an outer sealing grate sealing ring 118a respectively on the outside of the inner sealing grate 117b and the outer sealing grate 118b and respectively cooperating to provide sealing functions; the inner sealing grate sealing ring 117a and the outer sealing grate sealing ring 118a are respectively formed by the radial inward extension of the left support plate 110a of the pre-rotation channel and the right support plate 110b of the pre-rotation channel. Among them, the left support plate 110a of the pre-swirl channel is located on the radial inner side of the combustion chamber casing 131 and the outer end of the left support plate 110a of the pre-swirl channel is overlapped and assembled with the combustion chamber casing 131; the right support plate 110b of the pre-swirl channel is located on the radial inner side of the turbine guide vane 107 and is connected to the rear side of the turbine guide vane 107.

[0075] In this embodiment, a receiving hole 120 is formed between the inner sealing grate 117b and the outer sealing grate 118b; a pre-swirl chamber 119 is formed between the inner sealing grate 117b, the outer sealing grate 118b, the inner sealing grate sealing ring 117a, and the outer sealing grate sealing ring 118a; a pre-swirl channel 111 is formed radially outside the pre-swirl chamber 119 and between the left support plate 110a and the right support plate 110b of the pre-swirl channel; and a plurality of pre-swirl nozzles 115 are arranged in the pre-swirl channel 111 in a circumferential direction around the drum shaft 121. The radial outer side of the pre-swirl channel 111 is the air collecting chamber 109, and the radial inner side is the pre-swirl chamber 119. The plenum chamber 109 is enclosed by the radially outer turbine guide vanes 107, the front combustion chamber casing 131, and the radially inner and rear pre-swirl channel left and right support plates 110a and 110b. Pre-swirl channel 111 connects the cooling air from plenum chamber 109 to pre-swirl chamber 119, which collects the cooling air passing through pre-swirl channel 111. The plenum chamber 109 reduces the flow rate of the cooling air during its circulation, ensuring a stable supply.

[0076] The engine assembly also includes a cover plate 125 that extends radially outward from the axial rear end of the outer sealing grate 118b and is connected to the turbine disc 123. The outer sealing grate 118b and the cover plate 125 can be formed as one piece. The inner surfaces of the inner sealing grate 117b and the outer sealing grate 118b, the outer surface of the drum shaft 121, the rear surface of the cover plate 125, and the front surface of the turbine disc 123 together surround and form a cover plate cavity 122. After the cooling air flows through the pre-swirl channel 111 and enters the pre-swirl cavity 119, most of the cooling air enters the cover plate cavity 122 through the receiving hole 120, except for a small amount of cooling air that leaks through the inner sealing grate 117b and the outer sealing grate 118b. The cooling air in the cover plate cavity 122 enters the turbine blades 108 through the air supply hole 124 on the turbine disc 123 to cool them.

[0077] The engine assembly may further include a turbine disk front cavity 126 defined by the turbine disk 123 and located axially forward of the turbine disk 123 . The turbine disk front cavity 126 is defined between the cover plate 125 and the right support plate 110 b of the pre-swirl channel and located axially forward of the cover plate 125 .

[0078] The flow path of the cooling air is as follows: after the cooling air provided by the cold air source enters the air collecting chamber 109, the cooling air in the air collecting chamber 109 is provided to the pre-swirl channel 111 through the pre-swirl nozzle 115, and enters the radially inner pre-swirl chamber 119 along the pre-swirl channel 111, and then enters the cover plate chamber 122 through the receiving hole 120 between the inner sealing grate 117b and the outer sealing grate 118b, and then is provided to the turbine blades 108 through the air supply hole 124 in the turbine disc 123, providing cooling function for the turbine blades 108.

[0079] The adjustment assembly is used to adjust the angle of the pre-swirl nozzle 115, and includes a hydraulic regulator 102 installed on the radially outer side of the outer duct inner casing 127; a drive shaft 105 extending radially inward from the outer duct 128 to the turbine disc front cavity 126 and driven by the output of the hydraulic regulator 102; a drive shaft bevel gear 112 connected to the radial inner end of the drive shaft 105; a plurality of nozzle shafts 116 assembled with the pre-swirl nozzle 115 and driving the pre-swirl nozzle 115 to rotate, and extending axially rearward to the turbine disc front cavity 126; and a nozzle shaft bevel gear 113 connected to the axial rear end of the nozzle shaft 116. Among them, the drive shaft bevel gear 112 rotating around the radially extending axis is engaged with the nozzle shaft bevel gear 113 rotating around the axially extending axis, converting the rotational driving force around the radially extending axis (i.e., Figure 1 The rotational driving force in the vertical direction) is converted into a rotational driving force about the axially extending axis (ie, Figure 1The hydraulic regulator 102 drives the nozzle shaft 116 to rotate, thereby driving the nozzle shaft 116 to rotate. The nozzle shaft 116 then adjusts the angle of the pre-swirl nozzle 115. Optionally, each pre-swirl nozzle 115 is equipped with a nozzle shaft 116, which passes through the mounting hole in the head of the pre-swirl nozzle 115 and is fixed thereto. Alternatively, the number of nozzle shafts 116 and pre-swirl nozzles 115 can be 24, symmetrically arranged at even intervals around the drum axis 121.

[0080] like Figure 2 As shown, to prevent structural damage to the drive shaft 105 caused by the impact of high-temperature combustion gases 130 in the combustion chamber 129, the drive shaft 105 is positioned away from the combustion chamber 129. The drive shaft 105 extends from the outer duct 128 through the relatively cool turbine guide vane cooling rear cavity 106 and the plenum 109 inside the turbine guide vane 107, and into the turbine disk front cavity 126. Both the turbine guide vane cooling rear cavity 106 and the plenum 109 are isolated from the combustion chamber 129. The turbine disk front cavity 126 is also isolated from the combustion chamber 129.

[0081] In this embodiment, the adjustment assembly may further include a mounting seat 101, which is fixed to the outer duct inner casing 127, and the hydraulic regulator 102 is then mounted on the mounting seat 101. Optionally, the adjustment assembly may further include an actuating rod 103 and a connecting rod 104 arranged in the axial direction, the output end of the hydraulic regulator 102 in the axial direction is connected to the front end of the actuating rod 103, the rear end of the actuating rod 103 is connected to the input end of the connecting rod 104, and the output end of the connecting rod 104 is sleeved to the radial outer end of the drive shaft 105, thereby providing the output of the hydraulic regulator 102 to the drive shaft 105, driving the rotation of the drive shaft 105. The rotational driving force output by the hydraulic regulator 102 around the axially extending axis (i.e., Figure 1 The horizontal rotational driving force) is converted into a rotational driving force about a radially extending axis (i.e., Figure 1 The vertical rotation driving force drives the drive shaft 105 to rotate.

[0082] like Figure 3As shown, the adjustment assembly may also include spur teeth 132 disposed on the outer periphery of the midsection of each nozzle shaft 116; and a gear ring 114 surrounding the drum shaft 121 and located in the turbine disc front cavity 126, with teeth on its outer periphery meshing with the spur teeth 132 of each nozzle shaft 116. Spur teeth 132 are disposed on the portion of the nozzle shaft 116 located in the turbine disc front cavity 126, and the gear ring 114 meshes with the spur teeth 132 of all nozzle shafts 116. The output driving force of the hydraulic regulator 102, through the drive shaft 105, drives the rotation of the shaft bevel gear 112 and the nozzle shaft bevel gear 113, driving the nozzle shaft 116 connected to the nozzle shaft bevel gear 113. The gear ring 114, meshing with the spur teeth 132 of all nozzle shafts 116, then drives the rotation of the remaining nozzle shafts 116 not connected to the nozzle shaft bevel gear 113, thereby achieving synchronous adjustment of all pre-swirl nozzles 115 through the gear ring 114. The adjustment assembly of this embodiment includes a hydraulic regulator 102 and a matching transmission mechanism. The transmission mechanism includes an actuator rod 103, a connecting rod 104, a drive shaft 105, a shaft bevel gear 112, a nozzle shaft bevel gear 113, and a nozzle shaft 116 connected to the nozzle shaft bevel gear 113. It should be understood that in other embodiments, more than one set of hydraulic regulators 102 and transmission mechanisms can be provided as needed.

[0083] In this embodiment, connecting rod 104 converts the driving force output by hydraulic regulator 102 into rotational motion, driving drive shaft 105 to rotate. The meshing transmission between drive shaft bevel gear 112 and nozzle shaft bevel gear 113 converts the vertical rotational driving force generated by hydraulic regulator 102, actuator rod 103, and connecting rod 104 into horizontal rotational driving force, driving pre-swirl nozzle 115 mounted on nozzle shaft 116 to rotate, thereby adjusting the angle of pre-swirl nozzle 115 and, accordingly, the flow rate of cooling air provided by pre-swirl nozzle 115. Furthermore, the use of bevel gear transmission, including drive shaft bevel gear 112 and nozzle shaft bevel gear 113, enables continuous rotational motion, providing not only precise, stepless angle control but also high reliability and low failure rate.

[0084] This configuration allows the adjustment assembly's mounting base 101, hydraulic regulator 102, actuator rod 103, and connecting rod 104 to be located within the duct 128, shielded from the high-temperature combustion gases in the combustion chamber 129. This prevents functional and structural failures caused by high temperatures, providing a more reliable adjustment drive. The adjustment assembly's drive shaft bevel gear 112, nozzle shaft bevel gear 113, gear ring 114, and other components are located within the turbine disc front cavity 126, similarly shielded from the high-temperature combustion gases from the combustion chamber 129 and protected from high-temperature environments. The drive shaft 105 is configured to extend radially inward from the duct 128, passing through the turbine guide vane rear cooling cavity 106 and the plenum 109, and into the turbine disc front cavity 126, similarly shielded from the high-temperature combustion gases and protected from high-temperature environments.

[0085] When the adjustment assembly is operating, the driving force output by the hydraulic regulator 102 drives the radial drive shaft 105 to rotate via the actuator rod 103 and the connecting rod 104. The drive shaft 105 drives the drive shaft bevel gear 112 at the end and the nozzle shaft bevel gear 113 meshing with it to rotate, thereby rotating the nozzle shaft 116 and driving the pre-swirl nozzle 115 to the desired angle. Furthermore, the gear ring 114 meshing with the spur teeth 132 of all nozzle shafts 116 also drives all nozzle shafts 116 to rotate, thereby achieving synchronous adjustment of all pre-swirl nozzles 115 through the gear ring 114. Driven by the actuator rod 103 and the connecting rod 104, the drive shaft 105, the drive shaft bevel gear 112, the nozzle shaft 116, and the nozzle shaft bevel gear 113 can rotate continuously, thereby achieving stepless adjustment of the pre-swirl nozzle 115.

[0086] In this embodiment, the driving force is provided by the hydraulic regulator 102. In addition, in other embodiments, the driving force may also be provided by another motor as needed.

[0087] Alternatively, in another embodiment, the adjustment assembly may include two hydraulic regulators 102, which are mounted on the outer duct inner casing 127 at circumferentially symmetrical positions via a mounting base 101, and the two hydraulic regulators are actuated synchronously; and correspondingly include two sets of actuating rods, connecting rods, drive shafts, drive shaft bevel gears, and nozzle shaft bevel gears, and the two nozzle shaft bevel gears are respectively fixed to two circumferentially symmetrical nozzle shafts, and the two nozzle shafts are respectively connected to two pre-swirl nozzles. The two hydraulic regulators synchronously provide driving force, respectively driving the two drive shaft bevel gears 112 and the two nozzle shaft bevel gears 113 meshed therewith via the two drive shafts 105, and then acting on the corresponding two nozzle shafts 116 symmetrically arranged about the drum axis, driving the pre-swirl nozzles 115 to rotate to the desired angle; wherein, the gear ring 114 meshing with the straight teeth 132 of all nozzle shafts 116 can also drive all nozzle shafts 116 to rotate, and thus all pre-swirl nozzles 115 are synchronously adjusted through the gear ring 114.

[0088] By symmetrically arranging two groups of hydraulic regulators and transmission components, sufficient driving force can be provided, and the driving of the adjustment components can be provided more balanced, thereby providing a better adjustment effect.

[0089] According to another embodiment of the present invention, a radial pre-swirl nozzle stepless adjustment system based on a bevel gear is provided, which is installed to an engine assembly for adjusting the angle of the pre-swirl nozzle in the engine assembly, including an adjustment assembly; wherein the engine assembly includes: a combustion chamber casing 131, arranged around the engine axis; an outer duct inner casing 127, installed radially outside the combustion chamber casing 131 and arranged around the engine axis; a combustion chamber 129, defined between the combustion chamber casing 131 and the outer duct inner casing 127; an outer duct 128, defined radially outside the outer duct inner casing 127; a pre-swirl channel 111, formed between the radial extension parts of the pre-swirl channel left support plate 110a and the pre-swirl channel right support plate 110b of the engine; a plurality of pre-swirl nozzles 115, arranged in the pre-swirl channel 111 and Circumferential layout around the engine axis; the adjustment component includes: a hydraulic regulator 102, installed in the outer duct 128; a drive shaft 105, driven by the output of the hydraulic regulator 102 and extending radially inward from the outer duct 128; a drive shaft bevel gear 112, connected to the radial inner end of the drive shaft 105, and rotating around the radial extension axis; a plurality of nozzle shafts 116, assembled with each pre-swirl nozzle 115 and driving the pre-swirl nozzle 115 to rotate, and extending axially backward; a nozzle shaft bevel gear 113, connected to the axial rear end of the corresponding nozzle shaft 116, and rotating around the axially extended axis; wherein, the drive shaft bevel gear 112 is engaged with the nozzle shaft bevel gear 113 to realize the driving rotation of the nozzle shaft 116 by the hydraulic regulator 102, and then adjust the angle of the pre-swirl nozzle 115 through the nozzle shaft 116.

[0090] In this embodiment, the adjustment assembly further includes: a mounting seat 101 fixed on the inner casing 127 of the outer duct, and the hydraulic regulator 102 is installed on the mounting seat 101.

[0091] In this embodiment, the adjustment assembly also includes: an actuating rod 103 and a connecting rod 104 arranged in the axial direction; wherein, the front end of the actuating rod 103 is connected to the output end of the hydraulic regulator 102, and the rear end of the actuating rod 103 is connected to the input end of the connecting rod 104, and the output end of the connecting rod 104 is fitted to the radial outer end of the drive shaft 105; the output of the hydraulic regulator 102 in the axial direction is converted into a rotational drive via the actuating rod 103 and the connecting rod 104, and then transmitted to the drive shaft 105.

[0092] The engine assembly further includes a cover plate 125 and a turbine disc front cavity 126 defined between the cover plate 125 and the right support plate 110b of the pre-swirl channel. In this embodiment, the drive shaft 105 extends radially inward into the turbine disc front cavity 126, and the drive shaft bevel gear 112 disposed at the radially inner end of the drive shaft 105 is located in the turbine disc front cavity 126. The nozzle shaft 116 extends axially rearward into the turbine disc front cavity 126, and the nozzle shaft bevel gear 113 connected to the axial rear end of the nozzle shaft 116 is located in the turbine disc front cavity 126.

[0093] The engine assembly further includes a plurality of turbine guide vanes 107 located downstream of the combustion chamber 129 and arranged circumferentially around the engine axis, and a turbine guide vane rear cooling cavity (106) formed within each turbine guide vane 107. In this embodiment, the drive shaft 105 is configured to extend radially inward from the outer duct 128, pass through the turbine guide vane rear cooling cavity 106, and enter the turbine disk front cavity 126.

[0094] The engine assembly further includes a plenum chamber 109 radially outwardly of the pre-swirl passage 111. In this embodiment, the drive shaft 105 is configured to extend radially inwardly from the outer duct 128, sequentially passing through the turbine guide vane rear cooling cavity 106 and the plenum chamber 109, and into the turbine disk front cavity 126.

[0095] In this embodiment, the adjustment component also includes: straight teeth 132, which are arranged on the outer periphery of the middle section of each nozzle shaft 116; a gear ring 114, which is an annular gear surrounding the engine axis and is located in the front cavity 126 of the turbine disk, and its outer peripheral teeth are engaged with the straight teeth 132 of each nozzle shaft 116; the gear ring 114 is used to achieve synchronous adjustment of all pre-rotation nozzles 115.

[0096] In this embodiment, the adjustment assembly also includes: two hydraulic regulators 102, which are respectively installed at circumferentially symmetrical positions on the inner casing 127 of the outer duct through the mounting base 101; and two corresponding sets of drive shafts 105, drive shaft bevel gears 112 and nozzle shaft bevel gears 113 connected to the hydraulic regulators 102, and the nozzle shaft bevel gears 113 are respectively fixed to two circumferentially symmetrical nozzle shafts 116.

[0097] In this embodiment, the number of nozzle shafts 116 and pre-swirl nozzles 115 is 24, and they are symmetrically arranged at even intervals in the circumferential direction around the axis of the engine.

[0098] According to yet another embodiment of the present invention, an aircraft engine is provided, comprising the bevel gear-based radial pre-swirl nozzle stepless adjustment system according to any one of the above embodiments.

[0099] The adjustment components in the existing radially adjustable pre-swirl systems in the art are usually installed on the radial inner side of the combustion chamber casing 131. This position is subject to heat radiation from the combustion chamber 129, resulting in high temperatures, which can cause the adjustment components to malfunction or fail at high temperatures. Compared with the prior art, the radial pre-swirl nozzle stepless adjustment system based on bevel gears provided in accordance with an embodiment of the present invention installs the adjustment component on the inner casing of the outer duct and adjusts the pre-swirl nozzle through bevel gears. Since the temperature in the outer duct is lower, the adjustment mechanism avoids being in a high-temperature working environment and has higher reliability. In addition, in the radial pre-swirl nozzle stepless adjustment system based on bevel gears provided in this embodiment, the drive shaft, drive shaft bevel gear, nozzle shaft, and nozzle shaft bevel gear can move continuously under the drive of the actuator rod and the connecting rod, thereby achieving stepless adjustment of the pre-swirl nozzle. Compared with the throttle valve-based pre-swirl system adjustment method that can only achieve two-stage adjustment by opening and closing the valve, the adjustment of the present invention has higher flexibility and adaptability.

[0100] All the above optional technical solutions can be arbitrarily combined to form optional embodiments of the present invention, and will not be described in detail here.

[0101] It should be understood that the size of the serial numbers of the steps in the above embodiments does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present invention.

[0102] The above description is only a preferred specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with this technical field within the technical scope disclosed by the present invention should be covered by the scope of protection of the present invention.

Claims

1. A radial pre-swirl nozzle stepless adjustment system based on bevel gears, characterized in that: Mounted to an engine assembly for adjusting the angle of a pre-swirl nozzle in the engine assembly, including an adjustment assembly; The engine assembly includes: a combustion chamber (129) defined by a combustion chamber casing (131); an outer duct (128) radially outside the combustion chamber (129) and defined by an outer duct inner casing (127); and a plurality of pre-swirl nozzles (115) arranged in a pre-swirl channel (111) and circumferentially arranged around an engine axis. The adjustment components include: A hydraulic regulator (102) is installed in the outer duct (128); a drive shaft (105) driven by the output of the hydraulic regulator (102) and extending radially inward from the outer duct (128); a drive shaft bevel gear (112) connected to the radially inner end of the drive shaft (105) and rotating about a radially extending axis; A plurality of nozzle shafts (116) are assembled with each pre-swirl nozzle (115) and drive the pre-swirl nozzle (115) to rotate, and extend axially backward; A nozzle shaft bevel gear (113) connected to the axial rear end of the corresponding nozzle shaft (116) and rotating around an axially extending axis; The driving shaft bevel gear (112) is meshed with the nozzle shaft bevel gear (113), so that the hydraulic regulator (102) drives the nozzle shaft (116) to rotate, thereby adjusting the angle of the pre-swirl nozzle (115) through the nozzle shaft (116).

2. The bevel gear-based radial pre-swirl nozzle stepless adjustment system according to claim 1, characterized in that: The adjustment components also include: A mounting seat (101) is fixed on the inner casing (127) of the outer duct, and a hydraulic regulator (102) is mounted on the mounting seat (101).

3. The bevel gear-based radial pre-swirl nozzle stepless adjustment system according to claim 1, characterized in that: The adjustment components also include: An actuating rod (103) and a connecting rod (104) arranged in an axial direction; The front end of the actuating rod (103) is connected to the output end of the hydraulic regulator (102), the rear end of the actuating rod (103) is connected to the input end of the connecting rod (104), and the output end of the connecting rod (104) is sleeved to the radial outer end of the driving shaft (105); The output of the hydraulic regulator (102) in the axial direction is converted into a rotational drive via the actuator rod (103) and the connecting rod (104), and then transmitted to the drive shaft (105).

4. The bevel gear-based radial pre-swirl nozzle stepless adjustment system according to claim 1, characterized in that: The drive shaft (105) extends radially inwardly into a turbine disk front cavity (126) of the engine assembly, and the drive shaft bevel gear (112) disposed at the radial inner end of the drive shaft (105) is located in the turbine disk front cavity (126); The nozzle shaft (116) extends axially backward into the turbine disc front cavity (126), and the nozzle shaft bevel gear (113) connected to the axial rear end of the nozzle shaft (116) is located in the turbine disc front cavity (126).

5. The bevel gear-based radial pre-swirl nozzle stepless adjustment system according to claim 4, characterized in that: The drive shaft (105) is configured to extend radially inward from the outer duct (128), pass through the turbine guide vane rear cooling cavity (106) in the turbine guide vane (107) of the engine assembly, and enter the turbine disk front cavity (126).

6. The bevel gear-based radial pre-swirl nozzle stepless adjustment system according to claim 5, characterized in that: The drive shaft (105) is configured to extend radially inward from the outer duct (128), sequentially pass through the turbine guide vane rear cooling cavity (106) and the air collecting cavity (109) of the engine assembly, and enter the turbine disc front cavity (126).

7. The bevel gear-based radial pre-swirl nozzle stepless adjustment system according to claim 1, characterized in that: The adjustment components also include: Straight teeth (132) are provided on the periphery of the middle section of each nozzle shaft (116); A gear ring (114) is a ring gear surrounding the engine axis and located in the turbine disc front cavity (126) of the engine assembly, wherein the teeth on the outer periphery of the gear ring (114) mesh with the straight teeth (132) of each nozzle shaft (116); Synchronous adjustment of all pre-swirl nozzles (115) is achieved through the meshing of the gear ring (114) and the straight teeth (132) of each nozzle shaft (116).

8. The bevel gear-based radial pre-swirl nozzle stepless adjustment system according to claim 1, characterized in that: The adjustment components also include: Two hydraulic regulators (102) are respectively mounted on circumferentially symmetrical positions of the inner casing (127) of the outer duct via mounting seats (101); and Two corresponding sets of drive shafts (105), drive shaft bevel gears (112) and nozzle shaft bevel gears (113) are connected to the hydraulic regulator (102), and the nozzle shaft bevel gears (113) are respectively fixed to two circumferentially symmetrical nozzle shafts (116).

9. The bevel gear-based radial pre-swirl nozzle stepless adjustment system according to claim 1, characterized in that: The number of nozzle shafts (116) and pre-swirl nozzles (115) is 24, and they are symmetrically arranged at even intervals in the circumferential direction around the axis of the engine.

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