Rotor system for an engine and engine having the same

Abstract

The application relates to the technical field of aero-engines, and discloses a rotor system for an engine and an engine with the same. The rotating shaft comprises a cold end section and a hot end section, the rotating shaft is provided with an inner layer and an outer layer along the radial direction of the rotating shaft, the outer layer of the cold end section is a continuous fiber toughened resin matrix composite layer or a continuous fiber toughened ceramic matrix composite layer, and the outer layer of the hot end section is a continuous fiber toughened ceramic matrix composite layer. The rotating blade is installed on the rotating shaft. The rotating shaft is in a cylindrical structure, the root of the rotating blade is connected to the inner side of the rotating shaft, and the tip of the rotating blade extends in the direction of approaching the axis of the rotating shaft along the radial direction of the rotating shaft. The application combines the external rotating shaft structure and the composite material setting, can more effectively exert the advantages of the continuous fiber toughened composite material, and the external rotating shaft structure makes the outer layer of the rotating shaft easy to prepare, and solves the problem that the traditional aero-engine structure is difficult to exert the advantages of the composite material when the aero-engine using the composite material is replaced in situ.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more specifically to a rotor system for an engine and an engine having the same. Background Technology

[0002] Existing aero-engines using high-temperature alloys and other metallic materials suffer from problems such as high-temperature creep, thermal fatigue, and oxidation corrosion. Composite materials, on the other hand, possess advantages such as low density, high temperature resistance, high specific strength, and high specific stiffness. Applying them to aero-engine structures can effectively achieve high-performance and lightweight engine design. However, simply replacing traditional aero-engine structures with composite materials in situ is insufficient to fully leverage their advantages; a combination of engine structure and composite material characteristics is necessary. Summary of the Invention

[0003] This invention provides a rotor system for an engine and an engine having the same, to solve the problem that it is difficult to take full advantage of composite materials when using composite materials to replace the structure of a traditional aero-engine in situ.

[0004] In a first aspect, the present invention provides a rotor system for an engine, comprising: A rotating shaft includes a cold end section and a hot end section. The rotating shaft is radially provided with an inner rotating shaft layer and an outer rotating shaft layer. The outer rotating shaft layer includes a cold end section outer layer disposed on the cold end section and a hot end section outer layer disposed on the hot end section. The cold end section outer layer is a continuous fiber toughened resin matrix composite material layer or a continuous fiber toughened ceramic matrix composite material layer, and the hot end section outer layer is a continuous fiber toughened ceramic matrix composite material layer. Rotating blades, the rotating blades being mounted on the rotating shaft; The rotating shaft has a cylindrical structure, the root of the rotating blade is connected to the inner side of the rotating shaft, and the tip of the rotating blade extends radially toward the axis of the rotating shaft.

[0005] Beneficial effects: By setting the outer layer of the cold end section as a continuous fiber-toughened resin matrix composite material layer or a continuous fiber-toughened ceramic matrix composite material layer, and the outer layer of the hot end section as a continuous fiber-toughened ceramic matrix composite material, the composite material has advantages such as low density, high temperature resistance, high specific strength, and high specific stiffness, which can effectively reduce the weight of the rotor system, improve engine performance, and realize the high-performance and lightweight design of the engine. The shaft is designed as a cylindrical structure, with the root of the rotating blades connected to the inner side of the shaft. The tips of the rotating blades extend radially towards the shaft axis. The rotor system is designed as an external shaft with internal rotating blades. The outer layer of the cold end section is made of a continuous fiber-reinforced resin matrix composite material or a continuous fiber-reinforced ceramic matrix composite material, and the outer layer of the hot end section is made of a continuous fiber-reinforced ceramic matrix composite material. Both use continuous fiber-reinforced composite materials, which can withstand high tensile loads. The external shaft structure requires the shaft to withstand greater tensile stress. Combining the external shaft structure with the composite material setting can more effectively leverage the advantages of continuous fiber-reinforced composite materials. Furthermore, the external shaft structure makes the outer layers of the cold and hot ends easier to prepare, reducing manufacturing difficulty.

[0006] In one optional embodiment, the rotor system further includes a rotating blade mounting ring, which is mounted on the side of the rotating shaft near the shaft axis. The rotating blade is mounted on the rotating shaft via the rotating blade mounting ring. The rotating blade mounting ring has mounting holes, and the rotating blade is adapted to be fixed within the mounting holes. The mounting holes are wedge-shaped holes, and the cross-sectional area of ​​the mounting holes gradually increases from the opening side near the shaft axis to the opening side away from the shaft axis. And / or, the cross-sectional area of ​​the rotating blade gradually increases from the tip of the rotating blade to the root of the rotating blade.

[0007] Beneficial effects: In the rotor system, a rotating blade mounting ring is used to fix the rotating blade to the side of the rotating shaft near its axis. The rotating blade mounting ring has mounting holes, which are used to fix the rotating blade. The structure is simple. The rotating blade is designed so that the cross-sectional area of ​​the rotating blade gradually increases from the tip to the root. The mounting holes are wedge-shaped, so that the cross-sectional area of ​​the mounting holes gradually increases from the side closer to the axis of the rotating shaft to the side farther away from the axis of the rotating shaft. This allows the rotating blade to be snapped into the mounting hole, effectively preventing the rotating blade from falling off. By matching the shape of the mounting hole with the shape of the rotating blade, the fixing effect of the mounting hole on the rotating blade can be improved, and the rotating blade can be prevented from shaking during operation.

[0008] In one optional embodiment, the rotating blade mounting ring is provided with one of a groove or a first rib on the side away from the axis of the rotating shaft, and the inner layer of the rotating shaft is provided with the other of a groove or a first rib on the side close to the axis of the rotating shaft. The first rib and the groove extend along the axial direction of the rotating shaft. When the rotating blade mounting ring is installed on the rotating shaft, the first rib is fixed in the groove. The first rib cooperates with the groove to circumferentially limit the rotating blade mounting ring.

[0009] Beneficial effects: By setting one of a slot or a first rib on the side of the rotating blade mounting ring away from the axis of rotation, and setting the other of a slot or a first rib on the side of the inner layer of rotation close to the axis of rotation, and fixing the first rib to the slot, the rotating blade mounting ring and the inner layer of rotation can be relatively fixed in the circumferential direction of rotation. The structure is simple and can effectively limit the circumferential movement of the rotating blade mounting ring, preventing relative sliding between the rotating blade mounting ring and the inner layer of rotation in the circumferential direction of rotation, so that the rotation shaft can effectively drive the rotating blade to rotate, and the rotor system can operate smoothly.

[0010] In one optional embodiment, a second rib is provided on the inner layer of the rotating shaft near the axis of the rotating shaft. The second rib extends circumferentially along the rotating shaft. When the rotating blade mounting ring is installed on the rotating shaft, the first end of the rotating blade mounting ring abuts against the second rib, and the second rib axially limits the rotating blade mounting ring. And / or, the two ends of the rotating shaft are provided with threaded structures, the rotor system includes locking nuts, the two locking nuts respectively cooperate with the threaded structures at both ends of the rotating shaft, the second end of the rotating blade mounting ring abuts against the locking nuts, and the locking nuts axially limit the rotating blade mounting ring.

[0011] Beneficial effects: By setting a second rib extending circumferentially along the shaft on one side of the inner layer of the shaft near the shaft axis, and having the first end of the rotating blade mounting ring abut against the second rib, the rotating blade mounting ring can be axially limited on one side, preventing relative sliding between the rotating blade mounting ring and the inner layer of the shaft in the axial direction. By setting threaded structures at both ends of the shaft and installing locking nuts, with the locking nuts abutting against the second end of the rotating blade mounting ring, the rotating blade mounting ring can be axially limited on the other side, preventing relative sliding between the rotating blade mounting ring and the inner layer of the shaft in the axial direction. By setting the second rib and locking nuts on both sides of the rotating blade mounting ring, the rotating blade mounting ring can be effectively fixed, thereby fixing the rotating blades and ensuring smooth operation of the rotor system.

[0012] In one optional embodiment, the inner layer of the rotating shaft includes a mounting portion and a connecting portion, the rotating blade mounting ring is mounted on the mounting portion, the mounting portion protrudes from the side surface of the connecting portion near the axis of the rotating shaft, and the thickness of the mounting portion is greater than the thickness of the connecting portion.

[0013] Beneficial effects: The inner layer of the shaft includes a mounting part and a connecting part. The blade mounting ring is installed in the mounting part. Because the rotating blades exert a large pressure on the shaft under the action of centrifugal force during rotation, the thickness of the mounting part is greater than the thickness of the connecting part. This can avoid increasing the overall thickness of the inner layer of the shaft while meeting structural requirements, thereby avoiding increasing the weight of the shaft and the consumption of raw materials.

[0014] In one optional embodiment, the inner layer of the rotating shaft is provided with a convex edge structure, the convex edge structure protruding from the surface of the inner layer of the rotating shaft away from the axis of the rotating shaft, the convex edge structure being disposed at both ends of the inner layer of the rotating shaft and connected to the two end faces of the outer layer of the rotating shaft.

[0015] Beneficial effects: By setting a convex edge structure on the inner layer of the shaft that protrudes from the side surface of the inner layer away from the shaft axis, and the convex edge structure is connected to the two end faces of the outer layer of the shaft, the outer layer of the shaft can be fixed, making the overall structure of the shaft more stable. In addition, during the manufacturing process of the shaft, the convex edge structure can provide the setting boundaries at both ends of the outer layer of the shaft, playing a positioning role.

[0016] In one optional embodiment, the rotating shaft has a split structure, the cold end section includes cold end section teeth, the hot end section includes hot end section teeth, the cold end section teeth mesh with the hot end section teeth, and the cold end section and the hot end section are connected by the cold end section teeth and the hot end section teeth.

[0017] Beneficial effects: By designing the shaft as a split structure, the materials and structures of the cold and hot end sections can be adjusted according to the different working conditions of different areas of the shaft, making the cold and hot end sections more adaptable to the working conditions and facilitating the control of the shaft's manufacturing costs. The cold end section is equipped with cold end teeth, and the hot end section is equipped with hot end teeth. The meshing of the cold end teeth and hot end teeth can achieve an effective connection between the cold and hot end sections, ensuring normal torque transmission. Furthermore, the structure is simple and avoids occupying internal space of the shaft.

[0018] In one optional embodiment, the inner layer of the shaft includes a cold end section inner layer disposed on the cold end section, wherein the cold end section inner layer is a titanium alloy layer. And / or, the rotating blade mounting ring includes a compressor rotating blade mounting ring mounted on the cold end section, the compressor rotating blade mounting ring being a titanium alloy structure.

[0019] Beneficial effects: By using titanium alloy structures for the inner layer of the cold end section and the compressor rotating blade mounting ring, the weight of the rotor system can be effectively reduced. Furthermore, since the cold end section operates at a low temperature, the titanium alloy structure can be adapted to the operating temperature of the cold end section and adapt to its operating conditions without causing structural damage or affecting the normal operation of the rotor system.

[0020] In one alternative embodiment, the rotating blade is a whisker-toughened ceramic matrix composite blade.

[0021] Beneficial effects: Using whisker-toughened ceramic matrix composite blades can reduce the weight of the blades due to the low density of the composite material, thereby reducing the weight of the rotor system. Furthermore, the composite material is heat-resistant and has good pressure-bearing properties. When the rotor system is configured with an external shaft and internal blades, the blades primarily bear pressure, while the whisker-toughened composite material can withstand high compressive loads. Using whisker-toughened ceramic matrix composite blades can be integrated with the rotor system structure, thereby improving engine performance.

[0022] In a second aspect, the present invention also provides an engine comprising a rotor system.

[0023] Beneficial effects: Since the engine includes a rotor system, it has the same effects as the rotor system, which will not be elaborated here. Attached Figure Description

[0024] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of a rotor system for an engine according to an embodiment of the present invention; Figure 2 for Figure 1 The cross-sectional view shown is of the rotor system used in the engine. Figure 3 This is a partial structural diagram of the cold end section of a rotor system for an engine according to an embodiment of the present invention. Figure 4 This is a partial structural diagram of the hot end section of a rotor system for an engine according to an embodiment of the present invention. Figure 5 This is a schematic diagram of the structure of a compressor rotating blade mounting ring and compressor rotating blades in a rotor system for an engine according to an embodiment of the present invention. Figure 6 This is a schematic diagram of the structure of a compressor rotating blade mounting ring in a rotor system of an engine according to an embodiment of the present invention; Figure 7 This is a schematic diagram of the structure of compressor rotating blades in a rotor system for an engine according to an embodiment of the present invention; Figure 8 This is a schematic diagram of the structure of a turbine blade mounting ring and turbine blades in a rotor system for an engine according to an embodiment of the present invention. Figure 9 This is a schematic diagram of the structure of a turbine blade mounting ring in a rotor system of an engine according to an embodiment of the present invention; Figure 10 This is a schematic diagram of the structure of a turbine rotating blade in a rotor system for an engine according to an embodiment of the present invention; Figure 11 This is a schematic diagram of the structure of a first locking nut in a rotor system of an engine according to an embodiment of the present invention; Figure 12 This is a schematic diagram of the structure of a second locking nut in a rotor system of an engine according to an embodiment of the present invention.

[0026] Explanation of reference numerals in the attached figures: 1. Shaft; 11. Cold end section; 111. Cold end section end tooth; 12. Hot end section; 121. Hot end section end tooth; 13. Inner layer of shaft; 131. First rib; 132. Second rib; 133. Mounting part; 134. Connecting part; 1341. Protruding edge structure; 135. Inner layer of cold end section; 136. Inner layer of hot end section; 14. Outer layer of shaft; 141. Outer layer of cold end section; 142. Outer layer of hot end section; 15. Threaded structure; 2. Rotating blades; 21. Compressor rotating blades; 211. First-stage compressor rotating blades; 212. Second-stage compressor rotating blades; 22. Turbine rotating blades; 3. Rotary blade mounting ring; 31. Mounting hole; 32. Slot; 33. First end; 34. Second end; 35. Compressor rotating blade mounting ring; 36. Turbine rotating blade mounting ring; 4. Locking nut; 41. First locking nut; 42. Second locking nut. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] The following is combined Figures 1 to 12 The following describes embodiments of the present invention.

[0029] like Figures 1 to 12 According to an embodiment of the present invention, in one aspect, a rotor system for an engine is provided, comprising: a rotating shaft 1 and rotating blades 2. The rotating shaft 1 includes a cold end section 11 and a hot end section 12. The rotating shaft 1 is radially provided with an inner rotating shaft layer 13 and an outer rotating shaft layer 14. The outer rotating shaft layer 14 includes a cold end section outer layer 141 disposed on the cold end section 11 and a hot end section outer layer 142 disposed on the hot end section 12. The cold end section outer layer 141 is a continuous fiber-reinforced resin matrix composite material layer or a continuous fiber-reinforced ceramic matrix composite material layer, and the hot end section outer layer 142 is a continuous fiber-reinforced ceramic matrix composite material layer. The rotating blades 2 are mounted on the rotating shaft 1. The rotating shaft 1 has a cylindrical structure. The root of the rotating blades 2 is connected to the inner side of the rotating shaft 1, and the tip of the rotating blades 2 extends radially toward the axis of the rotating shaft 1.

[0030] In this embodiment, the outer layer 141 of the cold end section is set as a continuous fiber toughened resin matrix composite material layer or a continuous fiber toughened ceramic matrix composite material layer, and the outer layer 142 of the hot end section is set as a continuous fiber toughened ceramic matrix composite material layer. Since composite materials have advantages such as low density, high temperature resistance, high specific strength, and high specific stiffness, they can effectively reduce the weight of the rotor system, improve engine performance, and realize the high-performance and lightweight design of the engine. The rotating shaft 1 is configured as a cylindrical structure, with the root of the rotating blade 2 connected to the inner side of the rotating shaft 1. The tip of the rotating blade 2 extends radially toward the axis of the rotating shaft 1. The rotor system is configured as an external rotating shaft and an internal rotating blade structure. The outer layer 141 of the cold end section is configured as a continuous fiber toughened resin matrix composite material layer or a continuous fiber toughened ceramic matrix composite material layer, and the outer layer 142 of the hot end section is configured as a continuous fiber toughened ceramic matrix composite material layer. Both use continuous fiber toughened composite materials, which can withstand high tensile loads. The rotating shaft 1 in the external rotating shaft structure needs to withstand greater tensile stress. Combining the external rotating shaft structure with the composite material configuration can more effectively leverage the advantages of continuous fiber toughened composite materials. Furthermore, the external rotating shaft structure makes the outer layer 141 of the cold end section and the outer layer 142 of the hot end section easier to prepare, reducing manufacturing difficulty.

[0031] In one specific embodiment, the outer layer 141 of the cold end section is a continuous fiber-reinforced resin-based composite material layer.

[0032] In another specific embodiment, the outer layer 141 of the cold end section is a continuous fiber-reinforced ceramic matrix composite layer.

[0033] Specifically, the outer layer 141 of the cold end section is a continuous carbon fiber toughened resin matrix composite layer, which has good tensile strength. The outer layer 142 of the hot end section is a continuous silicon carbide fiber toughened ceramic matrix composite layer, which has good tensile strength and high temperature resistance.

[0034] Specifically, the cold end segment 11 is prepared as follows: after manufacturing the inner layer 135, continuous carbon fibers are tightly wound around its outer circumference, and resin is used to densify the wound fiber cloth, forming the outer layer 141 of the cold end segment. The hot end segment 12 is prepared as follows: after manufacturing the inner layer 136, continuous silicon carbide fibers are tightly wound around its outer circumference, and chemical vapor deposition is used to densify the wound fiber cloth, forming the outer layer 142 of the hot end segment. The surface roughness at the junction of the inner layer 135 and the outer layer 141 of the cold end segment improves the bonding effect between them; similarly, the surface roughness at the junction of the inner layer 136 and the outer layer 142 of the hot end segment improves the bonding effect between them and prevents interface delamination.

[0035] like Figure 1 and Figures 5 to 10 As shown, in one embodiment, the rotor system further includes a rotating blade mounting ring 3, which is mounted on the side of the rotating shaft 1 near the axis of the rotating shaft 1. The rotating blade 2 is mounted on the rotating shaft 1 via the rotating blade mounting ring 3. The rotating blade mounting ring 3 is provided with a mounting hole 31, and the rotating blade 2 is adapted to be fixed in the mounting hole 31. The mounting hole 31 is a wedge-shaped hole, and the cross-sectional area of ​​the mounting hole 31 gradually increases from the opening on the side near the axis of the rotating shaft 1 to the opening on the side away from the axis of the rotating shaft 1, and / or, the cross-sectional area of ​​the rotating blade 2 gradually increases from the tip of the rotating blade 2 to the root of the rotating blade 2.

[0036] In this embodiment, the rotor system uses a rotating blade mounting ring 3 to fix the rotating blade 2 to the side of the rotating shaft 1 near its axis. The rotating blade mounting ring 3 has mounting holes 31, which are used to fix the rotating blade 2. The structure is simple. The rotating blade 2 is designed so that its cross-sectional area gradually increases from the tip to the root. The mounting hole 31 is designed as a wedge-shaped hole, so that the cross-sectional area of ​​the mounting hole 31 gradually increases from the side of the opening near the axis of the rotating shaft 1 to the side of the opening away from the axis of the rotating shaft 1. This allows the rotating blade 2 to be snapped into the mounting hole 31, effectively preventing the rotating blade 2 from falling off. By matching the shape of the mounting hole 31 with the shape of the rotating blade 2, the fixing effect of the mounting hole 31 on the rotating blade 2 can be improved, and the rotating blade 2 can be prevented from shaking during movement.

[0037] In one specific embodiment, the mounting hole 31 is a wedge-shaped hole. The cross-sectional area of ​​the mounting hole 31 gradually increases from the opening near the axis of the rotating shaft 1 to the opening away from the axis of the rotating shaft 1. The cross-sectional area of ​​the rotating blade 2 gradually increases from the tip of the rotating blade 2 to the root of the rotating blade 2. The shape of the rotating blade 2 is adapted to the shape of the mounting hole 31. When the rotating blade 2 is installed in the mounting hole 31, the outer surface of the rotating blade 2 is in contact with the inner wall surface of the mounting hole 31, and one end face of the root of the rotating blade 2 is flush with the surface of the rotating blade mounting ring 3 away from the axis of the rotating shaft 1.

[0038] like Figures 3 to 6 and Figure 8 , Figure 9 As shown, in one embodiment, the rotating blade mounting ring 3 is provided with one of a groove 32 or a first rib 131 on the side away from the axis of the rotating shaft 1, and the inner layer 13 of the rotating shaft is provided with the other of a groove 32 or a first rib 131 on the side close to the axis of the rotating shaft 1. The first rib 131 and the groove 32 extend along the axial direction of the rotating shaft 1. When the rotating blade mounting ring 3 is installed on the rotating shaft 1, the first rib 131 is fixed in the groove 32. The first rib 131 cooperates with the groove 32 to circumferentially limit the rotating blade mounting ring 3.

[0039] In this embodiment, by providing one of a slot 32 or a first rib 131 on the side of the rotating blade mounting ring 3 away from the axis of the rotating shaft 1, and providing the other of a slot 32 or a first rib 131 on the side of the inner layer 13 of the rotating shaft close to the axis of the rotating shaft 1, and fixing the first rib 131 to the slot 32, the rotating blade mounting ring 3 and the inner layer 13 of the rotating shaft can be relatively fixed in the circumferential direction of the rotating shaft 1. The structure is simple and can effectively limit the circumferential movement of the rotating blade mounting ring 3, preventing the rotating blade mounting ring 3 and the inner layer 13 of the rotating shaft from sliding relative to each other in the circumferential direction of the rotating shaft 1, so that the rotating shaft 1 can effectively drive the rotating blade 2 to rotate, and the rotor system can operate smoothly.

[0040] In one specific embodiment, the rotating blade mounting ring 3 is provided with a plurality of slots 32, which are spaced apart circumferentially along the rotating blade mounting ring 3. The inner layer 13 of the rotating shaft is provided with a plurality of first ribs 131 on the side near the axis of the rotating shaft 1, which are spaced apart circumferentially along the inner layer 13 of the rotating shaft. The number of slots 32 corresponds to the number of first ribs 131, and the position of the slots 32 corresponds to the position of the first ribs 131.

[0041] In another specific embodiment, a plurality of first ribs 131 are provided on the rotating blade mounting ring 3. The plurality of first ribs 131 are spaced apart circumferentially along the rotating blade mounting ring 3. A plurality of slots 32 are provided on the side of the inner layer 13 of the rotating shaft near the axis of the rotating shaft 1. The plurality of slots 32 are spaced apart circumferentially along the inner layer 13 of the rotating shaft. The number of slots 32 corresponds to the number of first ribs 131, and the position of the slots 32 corresponds to the position of the first ribs 131.

[0042] like Figures 1 to 4 As shown, in one embodiment, a second rib 132 is provided on the side of the inner layer 13 of the rotating shaft near the axis of the rotating shaft 1. The second rib 132 extends circumferentially along the rotating shaft 1. When the rotating blade mounting ring 3 is installed on the rotating shaft 1, the first end 33 of the rotating blade mounting ring 3 abuts against the second rib 132, and the second rib 132 axially limits the rotating blade mounting ring 3. And / or, threaded structures 15 are provided at both ends of the rotating shaft 1. The rotor system includes locking nuts 4. Two locking nuts 4 respectively cooperate with the threaded structures 15 at both ends of the rotating shaft 1. The second end 34 of the rotating blade mounting ring 3 abuts against the locking nuts 4, and the locking nuts 4 axially limit the rotating blade mounting ring 3.

[0043] In this embodiment, by providing a second rib 132 extending circumferentially along the shaft 1 on one side of the inner layer 13 of the rotating shaft near the axis of the rotating shaft 1, the first end 33 of the rotating blade mounting ring 3 abuts against the second rib 132, which can axially limit the rotating blade mounting ring 3 on one side, preventing relative sliding between the rotating blade mounting ring 3 and the inner layer 13 of the rotating shaft 1 in the axial direction; by providing threaded structures 15 at both ends of the rotating shaft 1 and installing locking nuts 4, which abut against the second end 34 of the rotating blade mounting ring 3, the rotating blade mounting ring 3 can be axially limited on the other side, preventing relative sliding between the rotating blade mounting ring 3 and the inner layer 13 of the rotating shaft 1 in the axial direction; by providing the second rib 132 and locking nuts 4 on both sides of the rotating blade mounting ring 3, the rotating blade mounting ring 3 can be effectively fixed, thereby fixing the rotating blade 2 and enabling the rotor system to operate smoothly.

[0044] Specifically, the rotating blade mounting ring 3 includes a compressor rotating blade mounting ring 35 and a turbine rotating blade mounting ring 36. Both the compressor rotating blade mounting ring 35 and the turbine rotating blade mounting ring 36 have a first end 33 and a second end 34. The first end 33 of the compressor rotating blade mounting ring 35 is the end of the compressor rotating blade mounting ring 35 that is close to the turbine rotating blade mounting ring 36, and the first end 33 of the turbine rotating blade mounting ring 36 is the end of the turbine rotating blade mounting ring 36 that is close to the compressor rotating blade mounting ring 35. The second end 34 of the compressor rotating blade mounting ring 35 is the end of the compressor rotating blade mounting ring 35 that is away from the turbine rotating blade mounting ring 36, and the second end 34 of the turbine rotating blade mounting ring 36 is the end of the turbine rotating blade mounting ring 36 that is away from the compressor rotating blade mounting ring 35.

[0045] Specifically, the threaded structure 15 is located on the side of the inner layer 13 of the shaft near the axis of the shaft 1.

[0046] Specifically, the locking nut 4 includes a first locking nut 41 and a second locking nut 42, which are respectively installed at both ends of the rotating shaft 1. The first locking nut 41 is located at the cold end section 11, and the second locking nut 42 is located at the hot end section 12. The first locking nut 41 is made of high-temperature alloy or titanium alloy, and the second locking nut 42 is made of high-temperature alloy.

[0047] like Figure 2 As shown, in one embodiment, the inner layer 13 of the rotating shaft includes a mounting portion 133 and a connecting portion 134. The rotating blade mounting ring 3 is mounted on the mounting portion 133. The mounting portion 133 protrudes from the side surface of the connecting portion 134 near the axis of the rotating shaft 1. The thickness of the mounting portion 133 is greater than the thickness of the connecting portion 134.

[0048] In this embodiment, the inner layer 13 of the rotating shaft includes a mounting part 133 and a connecting part 134. The blade mounting ring is mounted on the mounting part 133. Since the rotating blade 2 exerts a large pressure on the rotating shaft 1 under the action of centrifugal force during the rotation, the thickness of the mounting part 133 is greater than the thickness of the connecting part 134. This can avoid increasing the overall thickness of the inner layer 13 of the rotating shaft while meeting the structural requirements, thereby increasing the weight of the rotating shaft 1 and the consumption of raw materials.

[0049] like Figure 2 As shown, in one embodiment, the inner layer 13 of the rotating shaft is provided with a protruding edge structure 1341. The protruding edge structure 1341 protrudes from the side surface of the inner layer 13 away from the axis of the rotating shaft 1. The protruding edge structure 1341 is provided at both ends of the inner layer 13 of the rotating shaft and is connected to the two end faces of the outer layer 14 of the rotating shaft.

[0050] In this embodiment, by providing a protruding edge structure 1341 on the side surface of the inner layer 13 of the rotating shaft away from the axis of the rotating shaft 1, and connecting the protruding edge structure 1341 to the two end faces of the outer layer 14 of the rotating shaft, the outer layer 14 of the rotating shaft can be fixed, making the overall structure of the rotating shaft 1 more stable. In addition, during the manufacturing process of the rotating shaft 1, the protruding edge structure 1341 can provide the setting boundaries at both ends of the outer layer 14 of the rotating shaft, playing a positioning role.

[0051] Specifically, the surface of the convex edge structure 1341 away from the axis of the rotating shaft 1 is flush with the surface of the outer layer 14 of the rotating shaft away from the axis of the rotating shaft 1.

[0052] like Figures 2 to 4 As shown, in one embodiment, the rotating shaft 1 is a split structure, the cold end section 11 includes a cold end section end tooth 111, the hot end section 12 includes a hot end section end tooth 121, the cold end section end tooth 111 meshes with the hot end section end tooth 121, and the cold end section 11 and the hot end section 12 are connected by the cold end section end tooth 111 and the hot end section end tooth 121.

[0053] In this embodiment, the shaft 1 is configured as a split structure. The material and structure of the cold end section 11 and the hot end section 12 can be adjusted according to the different working conditions of different areas of the shaft 1, so that the cold end section 11 and the hot end section 12 are more adaptable to the working conditions, and it is easier to control the manufacturing cost of the shaft 1. The cold end section 11 is provided with a cold end section end tooth 111, and the hot end section 12 is provided with a hot end section end tooth 121. The meshing of the cold end section end tooth 111 and the hot end section end tooth 121 can realize the effective connection between the cold end section 11 and the hot end section 12, so that the torque can be transmitted normally. Moreover, the structure is simple and avoids occupying the internal space of the shaft 1.

[0054] Specifically, the rotating shaft 1 has a split structure, consisting of a cold end section 11 and a hot end section 12.

[0055] like Figure 2 As shown, in one embodiment, the inner shaft layer 13 includes a cold end section inner layer 135 disposed on the cold end section 11, and the cold end section inner layer 135 is a titanium alloy layer. And / or, the rotating blade mounting ring 3 includes a compressor rotating blade mounting ring 35 mounted on the cold end section 11, and the compressor rotating blade mounting ring 35 is a titanium alloy structure.

[0056] In this embodiment, the inner layer 135 of the cold end section and the compressor rotating blade mounting ring 35 are made of titanium alloy, which can effectively reduce the weight of the rotor system. Furthermore, since the cold end section 11 operates at a low temperature, the titanium alloy structure can be adapted to the operating temperature of the cold end section 11 and adapt to the operating conditions of the cold end section 11 without causing structural damage or affecting the normal operation of the rotor system.

[0057] Specifically, the inner layer 13 of the rotating shaft also includes a hot-end section inner layer 136 disposed on the hot-end section 12, and the hot-end section inner layer 136 is a high-temperature alloy layer. The rotating blade mounting ring 3 also includes a turbine rotating blade mounting ring 36 mounted on the hot-end section 12, and the turbine rotating blade mounting ring 36 is a high-temperature alloy structure.

[0058] Alternatively, the inner layer 135 of the cold end section can be a high-temperature alloy layer. The compressor rotating blade mounting ring 35 can also be a high-temperature alloy structure.

[0059] Specifically, the high-temperature alloy can be a high-temperature aluminum alloy.

[0060] In one embodiment, the rotating blade 2 is a whisker-toughened ceramic matrix composite blade.

[0061] In this embodiment, the rotating blade 2 is set as a whisker-toughened ceramic matrix composite blade. Since the whisker-toughened ceramic matrix composite has a low density, the weight of the rotating blade 2 can be reduced, thereby reducing the weight of the rotor system. It can also withstand high temperatures and has a good pressure-bearing effect. When the rotor system is set as an external shaft and an internal rotating blade structure, the rotating blade 2 mainly bears the pressure, while the whisker-toughened composite can withstand high compressive loads. Setting the rotating blade 2 as a whisker-toughened ceramic matrix composite blade can be combined with the structure of the rotor system, thereby improving engine performance.

[0062] Specifically, the rotating blade 2 includes a compressor rotating blade 21 and a turbine rotating blade 22, and the rotating blade 2 is made of silicon carbide whisker-toughened ceramic matrix composite material.

[0063] Specifically, the compressor rotating blade 21 includes a first-stage compressor rotating blade 211 and a second-stage compressor rotating blade 212. Correspondingly, the mounting hole 31 includes a first-stage mounting hole and a second-stage mounting hole. The first-stage compressor rotating blade 211 is mounted in the first-stage mounting hole, and the second-stage compressor rotating blade 212 is mounted in the second-stage mounting hole.

[0064] According to an embodiment of the present invention, in another aspect, an engine is also provided, the engine including a rotor system.

[0065] Specifically, the assembly steps of the rotor system are as follows: The cold end section 11 and the hot end section 12 are connected and positioned using the cold end section end teeth 111 and the hot end section end teeth 121; the rotating blade 2 is inserted into the mounting hole 31 from the side of the rotating blade mounting ring 3 away from the axis of the rotating shaft 1; the first-stage compressor rotating blade 211 is inserted into the first-stage mounting hole; the second-stage compressor rotating blade 212 is inserted into the second-stage mounting hole; and the turbine rotating blade 22 is inserted into the mounting hole 31 on the turbine rotating blade mounting ring 36; the assembled compressor rotating blade 21 and compressor rotating blade mounting ring 35 are then aligned along the axis of the rotor. The compressor rotor blade mounting ring 35 is locked in place by pushing the engine rotor blade 22 into the cold end section 11 in the direction of engine intake. During the pushing process, the first rib 131 needs to be inserted into the slot 32. The first locking nut 41 is screwed in along the direction of engine intake to lock and fix the compressor rotor blade mounting ring 35. The assembled turbine rotor blade 22 and turbine rotor blade mounting ring 36 assembly is pushed into the hot end section 12 in the opposite direction of engine intake. During the pushing process, the first rib 131 needs to be inserted into the slot 32. The second locking nut 42 is screwed in in the opposite direction of engine intake to lock and fix the turbine rotor blade mounting ring 36.

[0066] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A rotor system for an engine, characterized in that, include: A rotating shaft (1) includes a cold end section (11) and a hot end section (12). The rotating shaft (1) is provided with an inner rotating shaft layer (13) and an outer rotating shaft layer (14) along its radial direction. The outer rotating shaft layer (14) includes a cold end section outer layer (141) disposed on the cold end section (11) and a hot end section outer layer (142) disposed on the hot end section (12). The cold end section outer layer (141) is a continuous fiber toughened resin matrix composite material layer or a continuous fiber toughened ceramic matrix composite material layer. The hot end section outer layer (142) is a continuous fiber toughened ceramic matrix composite material layer. Rotating blade (2), the rotating blade (2) is mounted on the rotating shaft (1); The rotating shaft (1) has a cylindrical structure. The root of the rotating blade (2) is connected to the inner side of the rotating shaft (1). The tip of the rotating blade (2) extends radially toward the axis of the rotating shaft (1).

2. The rotor system for an engine according to claim 1, characterized in that, The rotor system further includes a rotating blade mounting ring (3), which is mounted on the side of the rotating shaft (1) near the axis of the rotating shaft (1). The rotating blade (2) is mounted on the rotating shaft (1) through the rotating blade mounting ring (3). The rotating blade mounting ring (3) is provided with a mounting hole (31), and the rotating blade (2) is adapted to be fixed in the mounting hole (31). The mounting hole (31) is a wedge-shaped hole, and the cross-sectional area of ​​the mounting hole (31) gradually increases from the opening on the side near the axis of the rotating shaft (1) to the opening on the side away from the axis of the rotating shaft (1). And / or, the cross-sectional area of ​​the rotating blade (2) gradually increases from the tip of the rotating blade (2) to the root of the rotating blade (2).

3. The rotor system for an engine according to claim 2, characterized in that, The rotating blade mounting ring (3) is provided with either a groove (32) or a first rib (131) on the side away from the axis of the rotating shaft (1). The inner layer (13) of the rotating shaft is provided with either a groove (32) or a first rib (131) on the side close to the axis of the rotating shaft (1). The first rib (131) and the groove (32) extend along the axial direction of the rotating shaft (1). When the rotating blade mounting ring (3) is installed on the rotating shaft (1), the first rib (131) is fixed in the groove (32). The first rib (131) cooperates with the groove (32) to circumferentially limit the rotating blade mounting ring (3).

4. The rotor system for an engine according to claim 3, characterized in that, The inner layer (13) of the rotating shaft is provided with a second rib (132) on the side near the axis of the rotating shaft (1). The second rib (132) extends along the circumference of the rotating shaft (1). When the rotating blade mounting ring (3) is installed on the rotating shaft (1), the first end (33) of the rotating blade mounting ring (3) abuts against the second rib (132), and the second rib (132) axially limits the rotating blade mounting ring (3). And / or, the two ends of the rotating shaft (1) are provided with threaded structures (15), the rotor system includes locking nuts (4), the two locking nuts (4) respectively cooperate with the threaded structures (15) at both ends of the rotating shaft (1), the second end (34) of the rotating blade mounting ring (3) abuts against the locking nuts (4), and the locking nuts (4) axially limit the rotating blade mounting ring (3).

5. The rotor system for an engine according to claim 2, characterized in that, The inner layer (13) of the rotating shaft includes a mounting part (133) and a connecting part (134). The rotating blade mounting ring (3) is mounted on the mounting part (133). The mounting part (133) protrudes from the connecting part (134) on one side surface near the axis of the rotating shaft (1). The thickness of the mounting part (133) is greater than the thickness of the connecting part (134).

6. The rotor system for an engine according to claim 5, characterized in that, The inner layer (13) of the rotating shaft is provided with a convex edge structure (1341). The convex edge structure (1341) protrudes from the side surface of the inner layer (13) away from the axis of the rotating shaft (1). The convex edge structure (1341) is provided at both ends of the inner layer (13) of the rotating shaft and is connected to the two end faces of the outer layer (14) of the rotating shaft.

7. The rotor system for an engine according to any one of claims 1 to 6, characterized in that, The rotating shaft (1) is a split structure. The cold end section (11) includes a cold end section end tooth (111), and the hot end section (12) includes a hot end section end tooth (121). The cold end section end tooth (111) meshes with the hot end section end tooth (121), and the cold end section (11) and the hot end section (12) are connected by the cold end section end tooth (111) and the hot end section end tooth (121).

8. The rotor system for an engine according to any one of claims 2 to 6, characterized in that, The inner layer (13) of the rotating shaft includes a cold end section inner layer (135) disposed on the cold end section (11), and the cold end section inner layer (135) is a titanium alloy layer. And / or, the rotating blade mounting ring (3) includes a compressor rotating blade mounting ring (35) mounted on the cold end section (11), the compressor rotating blade mounting ring (35) being a titanium alloy structure.

9. The rotor system for an engine according to any one of claims 1 to 6, characterized in that, The rotating blade (2) is a whisker-toughened ceramic matrix composite blade.

10. An engine, characterized in that, The engine includes a rotor system according to any one of claims 1 to 9.

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