A compressor sleeve rotor

Abstract

The application discloses a compressor set rotor, and relates to the technical field of rotor system equipment. Specifically comprising: a low-temperature material rotor, a high-temperature material rotor and a rotor limiting device, the low-temperature material rotor is a main rotating shaft, the high-temperature material rotor is a hollow shaft, the high-temperature material rotor is sleeved on the low-temperature material rotor, meanwhile, the inner control surfaces of the low-temperature material rotor and the high-temperature material rotor are mutually toothed, the rotor limiting device is installed downstream of the high-temperature material rotor to limit the axial displacement of the high-temperature material rotor, and the low-temperature material rotor and the high-temperature material rotor are respectively provided with low-temperature zone moving blades and high-temperature zone moving blades. The compressor test piece integral forging rotor is divided into two sections, the rotors made of different materials are used according to the working temperatures of different regions of the compressor, the different requirements of different sections are met, and meanwhile, different high-temperature material rotors can be processed to meet the requirements of the change of the number of compressor stages or the number of outlet stage blades.

Description

Technical Field

[0001] This invention relates to the field of rotor system equipment technology, and specifically to a compressor rotor assembly. Background Technology

[0002] As the core component of the compressor section of a gas turbine engine, the compressor rotor bears the crucial responsibility of compressing and increasing the pressure of air, providing the engine with the necessary compressed air. Its intricate structure primarily consists of a series of rotating blades that skillfully guide air through the compressor section. When the compressor rotor rotates at high speed, the blades effectively compress the air and increase its pressure. In a gas turbine engine, the rotational speed and efficiency of the compressor rotor directly affect the compressor's performance. Any malfunction or damage to the compressor rotor will severely impact the operation of the compressor section, consequently affecting the performance of the entire engine.

[0003] When conducting component testing of heavy-duty gas turbine compressors, forged rotors are typically used. This facilitates blank preparation and forging, and is also less costly and faster. However, when the compressor's pressure ratio is high, the operating temperature difference between the inlet and outlet stages is significant, leading to different material requirements. Combined with the requirements of the bearing lubrication system, the inlet and outlet ends of the compressor test rotor are in the low-temperature zone, with only the middle section being in the high-temperature zone. (See [reference needed]). Figure 1 As shown. Rotors in the low-temperature region require materials with sufficient strength and good low-temperature toughness at low temperatures; rotors in the high-temperature region require materials that can still maintain sufficient tensile properties at high temperatures.

[0004] For compressor test rotors with high pressure ratios, when using integrally forged rotors, if only the material requirements for the low-temperature region are considered, the operating temperature of the downstream stage of the compressor may exceed the allowable temperature of the material, causing high-temperature failure of the rotor. If only the material requirements for high-temperature regions are considered, the rotor section operating in the low-temperature region may face the problem of low-temperature brittle transition, leading to brittle failure. If segmented heat treatment is used, the integrally forged rotor is usually divided into an upstream low-temperature region and a downstream high-temperature region, which cannot meet the requirements of the low-temperature region at the outlet bearing mounting location.

[0005] Existing patent CN112253259A discloses a turbine rotor system, which includes a shaft with a first low-temperature zone, a high-temperature zone, and a second low-temperature zone sequentially arranged along the axial direction of the shaft. A balance disc is located in the first low-temperature zone of the shaft, and a first seal is fitted onto the balance disc. A first air inlet is located in the first low-temperature zone of the shaft and is used to connect to a cooling air source for cooling and sealing. A turbine rotor is located in the high-temperature zone of the shaft, and blades are provided on the outer periphery of the turbine rotor. A second air inlet is located in the high-temperature zone of the shaft and is used to provide high-temperature gas to drive the blades and rotate the shaft. The turbine rotor system of this invention can reduce the leakage of the balance disc, shorten the length of the balance disc, and thus shorten the span of the shaft, thereby improving the safety of the unit.

[0006] Existing patent CN221942569U discloses a rotor system, gas turbine, air compressor, and heat pump, including a rotating shaft, ball bearings, and a power bearing. The two ends of the rotating shaft are a first mounting end and a second mounting end, respectively. The ratio of the shaft diameter of the first mounting end to the second mounting end is in the range of 1:2 to 1:40. The ball bearing is installed at the first mounting end of the rotating shaft, and the power bearing is installed at the second mounting end. In this solution, the first mounting end of the rotating shaft is in a low-temperature environment, and the second mounting end of the rotating shaft is in a high-temperature environment. By placing the ball bearing on the first mounting end and the power bearing on the second mounting end, the power bearing can be an air bearing. This design satisfies operational needs and saves costs in short-term or one-time operation scenarios.

[0007] In summary, neither of the two existing patents addresses the problem that using a forged rotor in a compressor can cause high-temperature or brittle failure during component testing. Summary of the Invention

[0008] Based on the above-mentioned technical problems, the present invention proposes a compressor rotor assembly, which solves the problem that high-temperature failure or brittle failure may occur when the compressor uses a forged rotor in the prior art during component testing.

[0009] To achieve the above objectives, this invention proposes a compressor rotor assembly. The specific technical solution is as follows:

[0010] A compressor rotor assembly includes a cryogenic material rotor, a cryogenic zone rotor, a high-temperature material rotor, and a high-temperature zone rotor. The cryogenic material rotor is the main rotating shaft. The cryogenic material rotor corresponds sequentially to a first cryogenic zone, a high-temperature zone, and a second cryogenic zone along its axial direction. The shaft diameter of the cryogenic material rotor located in the first cryogenic zone is larger than the shaft diameter located in the high-temperature zone and the second cryogenic zone. The high-temperature material rotor is a hollow shaft. The high-temperature material rotor is mounted on the high-temperature zone of the cryogenic material rotor. The cryogenic zone rotor is installed on the cryogenic material rotor located in the first cryogenic zone, and the high-temperature zone rotor is installed on the high-temperature material rotor.

[0011] Furthermore, the low-temperature material rotor uses a low-temperature material, the high-temperature material rotor uses a high-temperature material, and the applicable temperature of the low-temperature material is lower than that of the high-temperature material.

[0012] Furthermore, the applicable temperature range of the low-temperature material is -20 to 400°C, and the applicable temperature range of the high-temperature material is 400 to 800°C.

[0013] Furthermore, it also includes a rotor limiting device, which is used to limit the axial movement of the high-temperature material rotor.

[0014] Furthermore, the rotor limiting device includes a rotor limiting boss on the low-temperature material rotor, the rotor limiting boss being located between the high-temperature zone and the second low-temperature zone.

[0015] Furthermore, the rotor limiting device also includes a balance disc, which is installed between the high-temperature material rotor and the rotor limiting boss.

[0016] Furthermore, the balance disc includes two semi-circular annular discs, the inner sidewall of which is provided with a balance disc keyway, and bolt holes are provided on the end faces of both ends of the semi-circular annular discs.

[0017] Furthermore, a shaft locking keyway is provided on the low-temperature material rotor at the location where it mates with the balance disc, and a locking key is installed in the shaft locking keyway.

[0018] Furthermore, the balance disc has a recessed stop on the side near the high-temperature material rotor, and the high-temperature material rotor has a convex stop on the end near the balance disc.

[0019] Furthermore, it also includes a spring, with a spring groove formed on the axial end face of the convex stop, and the spring is installed in the spring groove.

[0020] Furthermore, it also includes a sealing ring, which is installed between the convex stop and the concave stop.

[0021] Furthermore, the balance disc is an annular disc, the inner ring wall of the annular disc is provided with internal threads, and the low-temperature material rotor is provided with external threads at the mounting point where it mates with the balance disc.

[0022] Furthermore, the low-temperature material rotor and the high-temperature material rotor are installed together via a transmission key.

[0023] Furthermore, the low-temperature material rotor has multiple axial torsion transmission teeth on its circumferential surface in the high-temperature zone, and the torsion transmission teeth are evenly distributed along the circumferential direction; the high-temperature material rotor has multiple torsion transmission tooth grooves on its inner side along the circumferential direction, and the torsion transmission tooth grooves are evenly distributed along the circumferential direction.

[0024] Furthermore, the axial mating surface of the low-temperature material rotor and the high-temperature material rotor is a conical surface.

[0025] Furthermore, the low-temperature material rotor has multiple annular discs on its circumferential surface in the first low-temperature zone, and the low-temperature zone moving blades are installed on the discs at equal intervals along the circumferential direction; the high-temperature material rotor has multiple annular discs on its outer circumferential surface, and the high-temperature zone moving blades are installed on the discs at equal intervals along the circumferential direction.

[0026] Based on the above technical solution, the present invention has at least the following beneficial effects:

[0027] 1. The present invention proposes a compressor rotor assembly, which uses a low-temperature material rotor as the main rotating shaft and a high-temperature material rotor mounted on the low-temperature material rotor. The two rotors are made of materials suitable for different temperatures, so that the same rotor can meet the different temperature requirements of different sections.

[0028] 2. The present invention proposes a compressor assembly rotor in which different rotors are meshed with each other in a suitable manner, and at the same time have the functions of centering and torque transmission.

[0029] 3. The present invention proposes a compressor assembly rotor, which is designed with a rotor limiting device to press the rotor sections of different segments together, ensuring that the assembly rotor can work stably.

[0030] 4. The compressor rotor proposed in this invention can be adapted to the needs of changing the number of compressor stages or the number of outlet stage blades by processing and installing rotors made of different high-temperature materials. It can be used for scheme comparison tests and saves test costs. Attached Figure Description

[0031] The accompanying drawings, which form part of this specification, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0032] Figure 1 This is a schematic diagram of the compressor using a forged rotor in the background art of this invention;

[0033] Figure 2 This is an overall schematic diagram of a compressor rotor assembly proposed in this invention;

[0034] Figure 3 This is a schematic diagram of the rotor assembly of a compressor according to the present invention.

[0035] Figure 4 A vertical cross-sectional schematic diagram of a compressor rotor assembly provided by the present invention;

[0036] Figure 5 This is a partial vertical cross-sectional schematic diagram of a compressor rotor assembly provided by the present invention.

[0037] Reference numerals: 1-Low-temperature material rotor, 2-Low-temperature zone moving blade, 3-High-temperature zone moving blade, 4-High-temperature material rotor, 5-Sealing ring, 6-Spring, 7-Balance disc, 8-Locking key, 9-Bolt, 10-Nut, 11-Torsion transmission tooth, 12-Torsion transmission tooth groove, 13-Shaft locking keyway, 14-Balance disc locking keyway, 15-Bolt hole, 16-Axial mating surface, 17-Rotor torsion transmission mating surface, 18-Rotor limiting boss. Detailed Implementation

[0038] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0039] The present invention will be further described in detail below with reference to specific embodiments, which should not be construed as limiting the scope of protection claimed by the present invention.

[0040] To address the problem that high-temperature failure or brittle failure may occur during component testing when using integral forged rotors in existing compressor technologies, this invention proposes a compressor rotor assembly.

[0041] To achieve the above objectives, this invention proposes a compressor rotor assembly. A common forged compressor rotor is divided into a low-temperature material rotor and a high-temperature material rotor, with low-temperature and high-temperature blades respectively installed. The low-temperature material rotor serves as the main rotating shaft, with its shaft diameter decreasing in the high-temperature region. The high-temperature material rotor is a hollow shaft that can be fitted onto the low-temperature material rotor. The low-temperature and high-temperature material rotors are made of materials suitable for different operating temperatures, allowing the same rotor to meet the different temperature requirements of different sections. The low-temperature material rotor uses low-temperature materials suitable for low-temperature operating environments, meaning it maintains good performance even at low temperatures. The high-temperature material rotor uses high-temperature materials suitable for high-temperature operating environments, meaning it maintains good performance even at high temperatures. In this embodiment, the applicable operating temperature range for the low-temperature material is -20 to 400°C, and the applicable operating temperature range for the high-temperature material is 400 to 800°C.

[0042] Optional materials for the low-temperature rotor include 30Cr2Ni4MoV, 30Cr1Mo1V, and 34CrNi3Mo.

[0043] Optional materials for high-temperature rotors include 1Cr12Ni3MoVN, 12Cr10NiMoWVNbN, and 13Cr9Mo2Co1NiVNbNB.

[0044] See Figures 2-5 As shown, a specific example of a compressor rotor assembly is illustrated. (See also...) Figure 2 As shown, the compressor rotor assembly mainly consists of a low-temperature material rotor 1, a high-temperature material rotor 4, and a balance disc 7. (See reference...) Figure 3 As shown, the low-temperature material rotor 1 is the main rotating shaft, and the high-temperature material rotor 4 is a hollow shaft. The high-temperature material rotor 4 is mounted on the low-temperature material rotor 1. The balance disk 7 is located downstream of the high-temperature material rotor 4 and is used to limit the axial displacement of the high-temperature material rotor 4.

[0045] As one specific embodiment of the low-temperature material rotor 1, see [reference]. Figure 2 and Figure 3As shown, the cryogenic material rotor 1 is the main rotating shaft, which corresponds sequentially from left to right along the axial direction to the first cryogenic zone, the high-temperature zone, and the second cryogenic zone. The shaft diameter of the cryogenic material rotor 1 in the first cryogenic zone is larger than that in the high-temperature zone, and the shaft diameter in the high-temperature zone is larger than that in the second cryogenic zone. Multiple annular discs are located circumferentially outside the cryogenic material rotor 1 in the first cryogenic zone; these annular discs are used to mount the cryogenic zone moving blades 2. (See reference...) Figure 4 As shown, the low-temperature material rotor 1 has multiple axial torsion-transmitting teeth 11 arranged on the circumferential outer side of the high-temperature zone. The torsion-transmitting teeth 11 are evenly distributed along the circumference and are used to cooperate with the high-temperature material rotor 4 for installation, thereby playing a role in torsion transmission. An annular rotor limiting boss 18 is provided on the low-temperature material rotor 1 between the high-temperature zone and the second low-temperature zone to limit the axial displacement of the high-temperature material rotor 4.

[0046] As a specific embodiment of the high-temperature material rotor 4, see [reference]. Figure 3 As shown, the high-temperature material rotor 4 is a hollow shaft with multiple annular discs on its outer circumference. These annular discs are used to mount the moving blades 3 in the high-temperature zone. (See reference...) Figure 4 As shown, the inner side of the high-temperature material rotor 4 is provided with multiple axial torsion transmission tooth grooves 12. The multiple torsion transmission tooth grooves 12 are distributed at equal intervals along the circumference. The high-temperature material rotor 4 is mounted on the low-temperature material rotor 1, and the torsion transmission tooth grooves 12 and torsion transmission teeth 11 are installed together.

[0047] Optional, see below Figure 4 As shown, the axial mating surface 16 of the low-temperature material rotor 1 and the high-temperature material rotor 4 is a rotor centering mating cone surface, used to achieve centering of the low-temperature material rotor 1 and the high-temperature material rotor 4. Preferably, the rotor centering mating cone surface can be tilted in opposite directions, which has the advantage that when the high-temperature material rotor 4 thermally expands, it can be locked inside the low-temperature material rotor 1.

[0048] Optionally, all mating surfaces of the low-temperature material rotor 1 and the high-temperature material rotor 4 are provided with a heat-insulating coating or a protective layer with low hardness, so that the low-temperature material rotor 1 and the high-temperature material rotor 4 fit together more tightly.

[0049] As one specific implementation of the balance disc 7, see [link / reference]. Figure 4 As shown, the balance disc 7 is installed between the high-temperature material rotor 4 and the rotor limiting boss 18 to further limit the axial displacement of the high-temperature material rotor 4.

[0050] In some embodiments, the balance disk 7 includes two semi-circular annular disks. A balance disk locking keyway 14 is formed on the inner side of each semi-circular annular disk, and bolt holes 15 are formed on the end faces of both ends of the ring body. A shaft locking keyway 13 is formed at the mounting position corresponding to the balance disk 7 on the low-temperature material rotor 1, and a protruding locking key 8 is installed in the shaft locking keyway 13. The two semi-circular annular disks of the balance disk 7 are correspondingly fitted onto the low-temperature material rotor 1. The balance disk locking keyway 14 engages with the locking key 8 on the low-temperature material rotor 1, restricting the relative circumferential movement of the two semi-circular annular disks. The two ends of the ring body are fixed together by bolts 9 and nuts 10. A concave stop is formed on the side of the balance disk 7 near the high-temperature material rotor 4, and a convex stop is formed on the end of the high-temperature material rotor 4 near the balance disk 7. The convex and concave stops fit tightly together to achieve the positioning and fixation of the high-temperature material rotor 4. A spring 6 is also provided between the convex and concave stops. An annular groove is opened on the axial end face of the convex stop of the high-temperature material rotor 4. The spring is placed in the annular groove, with its left side pressing against the high-temperature material rotor 4 and its right side pressing against the balance disc 7, pressing the high-temperature material rotor 4 and the low-temperature material rotor 1 together, further restricting the axial displacement of the high-temperature material rotor 4, and also compensating for the gap caused by thermal expansion. A sealing ring 5 is also provided between the convex and concave stops. The sealing ring 5 prevents high-temperature airflow from entering the shaft diameter gap and protects the low-temperature material rotor 1 and the spring 6.

[0051] In other embodiments, the balance disc 7 is an annular disc with internal threads machined on its inner wall. The low-temperature material rotor 1 has external threads at the mating shaft diameter corresponding to the balance disc 7. After the high-temperature material rotor 4 is installed, the internally threaded balance disc 7 is screwed onto the low-temperature material rotor 1, and a tightening torque is applied to press the high-temperature material rotor 4 and the low-temperature material rotor 1 together. Then, the interference fit rotor limiting boss 18 is installed. This balance disc 7 does not require mating components such as springs, sealing rings, locking keys, bolts, and nuts. The balance disc 7 can be installed using a heat-mounting method, where heating increases the inner hole of the balance disc, allowing it to be screwed onto the low-temperature material rotor 1. After cooling, further tightening is achieved.

[0052] The compressor rotor kit provided by the present invention uses two rotors made of materials suitable for different temperatures, so that the same rotor can meet the different temperature requirements of different sections. At the same time, by processing and installing rotors made of different high-temperature materials, it can meet the needs of changing the number of compressor stages or the number of outlet stage blades, and can be used for scheme comparison tests to save test costs.

[0053] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

[0054] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0055] It should be noted that, in the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

Claims

1. A compressor rotor assembly, characterized in that: The device includes a low-temperature material rotor (1), a low-temperature zone moving blade (2), a high-temperature material rotor (4), and a high-temperature zone moving blade (3). The low-temperature material rotor (1) is the main rotating shaft. The low-temperature material rotor (1) corresponds to the first low-temperature zone, the high-temperature zone, and the second low-temperature zone in sequence along the axial direction. The shaft diameter of the low-temperature material rotor (1) located in the first low-temperature zone is larger than the shaft diameter located in the high-temperature zone and the second low-temperature zone. The high-temperature material rotor (4) is a hollow shaft. The high-temperature material rotor (4) is mounted on the high-temperature zone of the low-temperature material rotor (1). The low-temperature zone moving blade (2) is installed on the low-temperature material rotor (1) located in the first low-temperature zone. The high-temperature zone moving blade (3) is installed on the high-temperature material rotor (4). It also includes a rotor limiting device for limiting the axial movement of the high-temperature material rotor (4); the rotor limiting device includes a rotor limiting boss (18) on the low-temperature material rotor (1), the rotor limiting boss (18) being located between the high-temperature zone and the second low-temperature zone; the rotor limiting device also includes a balance disc (7), the balance disc (7) being installed between the high-temperature material rotor (4) and the rotor limiting boss (18).

2. The compressor rotor assembly according to claim 1, characterized in that: The low-temperature material rotor (1) is made of low-temperature material, and the high-temperature material rotor (4) is made of high-temperature material. The applicable temperature of the low-temperature material is lower than that of the high-temperature material.

3. The compressor rotor assembly according to claim 2, characterized in that: The applicable temperature T1 of the low-temperature material is -20℃≤T1≤400℃, and the applicable temperature T2 of the high-temperature material is 400℃<T2≤800℃.

4. The compressor rotor assembly according to claim 1, characterized in that: The balance disc (7) includes two semi-circular annular discs. The inner sidewall of the semi-circular annular disc is provided with a balance disc keyway (14), and bolt holes (15) are provided on the end faces of both ends of the semi-circular annular disc.

5. The compressor rotor assembly according to claim 4, characterized in that: A shaft locking keyway (13) is provided on the low-temperature material rotor (1) at the location where it is installed in conjunction with the balance disk (7), and a locking key (8) is installed in the shaft locking keyway (13).

6. The compressor rotor assembly according to claim 5, characterized in that: The balance disc (7) has a recessed stop on one side near the high-temperature material rotor (4), and the high-temperature material rotor (4) has a convex stop on one end near the balance disc (7).

7. The compressor rotor assembly according to claim 6, characterized in that: It also includes a spring (6), with a spring groove provided on the axial end face of the convex stop, and the spring (6) is installed in the spring groove.

8. The compressor rotor assembly according to claim 6, characterized in that: It also includes a sealing ring (5), which is installed between the convex stop and the concave stop.

9. The compressor rotor assembly according to claim 1, characterized in that: The balance disc (7) is an annular disc, and the inner ring wall of the annular disc is provided with internal threads. The low-temperature material rotor (1) is provided with external threads at the joint where it is installed with the balance disc (7).

10. The compressor rotor assembly according to claim 1, characterized in that: The low-temperature material rotor (1) and the high-temperature material rotor (4) are installed by means of a transmission key.

11. The compressor rotor assembly according to claim 10, characterized in that: The low-temperature material rotor (1) has multiple axial torsion transmission teeth (11) on the circumferential surface of the high-temperature zone, and the torsion transmission teeth (11) are distributed at equal intervals along the circumferential direction. The high-temperature material rotor (4) has multiple torsion transmission grooves (12) on its inner side along the circumferential direction, and the torsion transmission grooves (12) are distributed at equal intervals along the circumferential direction.

12. The compressor rotor assembly according to claim 1, characterized in that: The axial mating surfaces of the low-temperature material rotor (1) and the high-temperature material rotor (4) are conical surfaces.

13. The compressor rotor assembly according to claim 1, characterized in that: The low-temperature material rotor (1) has multiple annular disks on its circumferential surface in the first low-temperature zone, and the low-temperature zone moving blades (2) are installed on the disks at equal intervals along the circumferential direction; the high-temperature material rotor (4) has multiple annular disks on its outer circumferential surface, and the high-temperature zone moving blades (3) are installed on the disks at equal intervals along the circumferential direction.

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