A dynamic stability adjusting device based on an aero-engine core engine

Abstract

The application discloses a dynamic stability adjusting device based on an aero-engine core engine, which comprises a fixed base body, a casing and support adapter toolings fixed on both sides of the casing; a rotor system, which comprises a rotating shaft accommodated in the casing, a high-pressure rotor and a high-vortex rotor fixedly installed on the rotating shaft; a standard support end, one end of the rotating shaft being rotationally connected with the casing through a front bearing and a front support; and a measurement support end; the application belongs to the technical field of aero-engine and gas turbine manufacturing and assembling, and has the technical effect that: by adopting a detection bearing seat tooling which has the same installation interface and internal cavity structure as the formal bearing seat tooling, the mechanical support environment of the rotor during the balance test is ensured to be completely consistent with the real working environment, so that the perfect balance state debugged in the test state can be preserved without damage and in integrity after the formal tooling is replaced, and the error source is reduced.

Description

Technical Field

[0001] This invention relates to the field of aero-engine and gas turbine manufacturing and assembly technology, specifically to a dynamic stability adjustment device based on the aero-engine core. Background Technology

[0002] Traditional methods for dynamic balancing the rotors of aero-engine core components (typically including the high-pressure compressor, combustion chamber, and high-pressure turbine) have inherent flaws. The conventional approach involves balancing the rotors (including the shaft, high-pressure rotor, and high-pressure turbine rotor) individually on an external balancing machine. Once balanced to the required standard, the rotors are disassembled, reassembled into the casing, and finally, the high-pressure turbine rotor is reinstalled. This "balancing-disassembly-reassembly" process inevitably introduces assembly errors, disrupting the previously adjusted balance and causing excessive vibration of the entire engine. This necessitates repeated adjustments, severely impacting production efficiency and product reliability.

[0003] Therefore, it does not meet the existing requirements, so we propose a dynamic stability adjustment device based on the core of an aero-engine. Summary of the Invention

[0004] To address these issues, the present invention provides a dynamic stability adjustment device based on the core of an aero-engine, thereby solving the aforementioned problems in the prior art.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] According to a first aspect of the present invention, a dynamic stability adjustment device based on an aero-engine core includes a fixed base, comprising a casing and support adapters fixed to both sides thereof.

[0007] The rotor system includes a rotating shaft housed inside the casing, on which a high-pressure rotor and a high-vortex rotor are fixedly mounted;

[0008] Standard support end, one end of the rotating shaft is rotatably connected to the casing via a front bearing and a front bracket;

[0009] The measuring support end, wherein the other end of the rotating shaft is connected to the housing via a rear bearing, the measuring support end includes:

[0010] The rear bracket is fixed to the casing;

[0011] A bearing housing inspection fixture, detachably mounted to the rear bracket via fasteners, has an internal cylindrical cavity for accommodating and clamping the rear bearing; and

[0012] The integrated measurement system includes a piezoelectric sensor group disposed between the detection bearing housing fixture and the rear support, and a key phase sensor for detecting the key phase mark on the shaft.

[0013] Furthermore, the bearing housing testing fixture includes two symmetrical housings, and the inner sides of the two housings are symmetrically provided with arc-shaped fixing cavities.

[0014] Furthermore, the two fixed cavities together form the cylindrical cavity; the two housings are provided with connectors on both sides, and the two housings are fastened together by fasteners passing through the fixing holes on the connectors.

[0015] Furthermore, the external mounting dimensions, connection interfaces, and internal fixing cavity structure of the bearing housing testing fixture are completely identical to the corresponding structure of the formal bearing housing fixture.

[0016] Furthermore, a window is provided on the casing facing the rotor alignment plane, and the window is sealed by a removable sealing plate.

[0017] Furthermore, the counterweight structure includes: counterweight discs with evenly distributed threaded holes or T-slots provided at both ends of the rollers of the rotating shaft.

[0018] Furthermore, the counterweight structure includes: evenly distributed mounting holes on the final stage compressor disk of the high-pressure rotor and the turbine disk of the high-vortex rotor.

[0019] The present invention has the following advantages:

[0020] 1. This dynamic stability adjustment device based on the core of an aero-engine, by adopting a test bearing housing fixture with the same installation interface and internal cavity structure as the formal bearing housing fixture, ensures that the mechanical support environment of the rotor during the balance test is completely consistent with the actual working environment. This allows the perfect balance state calibrated under test conditions to be retained intact and completely after the formal fixture is installed, fundamentally eliminating the sources of error such as reference changes and bolt preload differences caused by secondary assembly in traditional processes, and achieving ultimate balance accuracy.

[0021] 2. This dynamic stability adjustment device based on the core of an aero-engine features a split-shell design. Through the cooperation of two shells and connecting parts, the bearing is safely and reliably clamped outside the casing, forming a stable "bearing-tooling" module before overall installation. This design completely avoids the high-risk operation of pressing or impact disassembling high-precision bearings in the narrow space inside the engine. It not only greatly reduces the difficulty of operation and the skill requirements of personnel, but more importantly, it fundamentally protects the precision and reliability of the bearing and improves the safety and robustness of the entire process.

[0022] 3. This dynamic stability adjustment device based on the core of an aero-engine integrates a piezoelectric sensor group and a key phase sensor to form a high-rigidity measurement system. Combined with the calibration window set on the casing, it establishes an efficient "sensing-computation-execution" closed-loop system, which enables the high-precision dynamic balancing process to be seamlessly embedded into the final assembly process. This eliminates the need for repeated rotor hoisting and disassembly, significantly shortening the engine's final assembly cycle and improving production efficiency while ensuring quality. Attached Figure Description

[0023] Figure 1 This is a front view of a dynamic stability adjustment device based on an aero-engine core engine proposed in this invention;

[0024] Figure 2 for Figure 1 The left view;

[0025] Figure 3 for Figure 1 The right view;

[0026] Figure 4 for Figure 1 A schematic diagram of the decomposition process;

[0027] Figure 5 for Figure 4 A cross-sectional view;

[0028] Figure 6 A schematic diagram of the disassembled bearing tooling for inspection;

[0029] Figure 7 for Figure 6 Rear view;

[0030] Figure 8 This is an internal view of the rear support.

[0031] Figure 9 for Figure 8 Side view.

[0032] In the diagram: 1. Casing; 101. Window; 102. Sealing plate; 2. Support adapter fixture; 3. Shaft; 301. Roller; 302. High-pressure rotor; 303. High-vortex rotor; 401. Front bearing; 402. Front bracket; 403. Rear bearing; 404. Rear bracket; 405. Perforation; 406. Connecting flange; 5. Bearing housing inspection fixture; 501. Housing; 502. Fixing cavity; 503. Connecting piece; 504. Connecting hole; 505. Fixing hole; 601. Piezoelectric sensor assembly; 602. Key phase sensor; Detailed Implementation

[0033] The following specific embodiments illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. 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.

[0034] Example 1;

[0035] Reference Figure 1 - Figure 9 A dynamic stability adjustment device based on an aero-engine core includes:

[0036] The housing 1 serves as the core fixed base, and its two side walls are fixed with support adapters 2 by bolts to stably support the entire core unit on the external bracket.

[0037] The rotor system has a rotating shaft 3 inside the casing 1. The rotating shaft 3 includes a roller 301 and a high-pressure rotor 302 and a high-vortex rotor 303 fixedly mounted thereon.

[0038] The standard support end, the left end of the rotating shaft 3 is rotatably connected to the casing 1 through the front bearing 401 and the front bracket 402;

[0039] The measuring support end, the right end of the rotating shaft 3 is connected to the housing 1 through the rear bearing 403. The core of this end is: a detection bearing seat fixture 5 is bolted to the rear bracket 404, and the rear bearing 403 is housed inside the detection bearing seat fixture 5.

[0040] The bearing housing fixture 5 includes two housings 501; symmetrical arc-shaped fixing cavities 502 are formed on the inner sides of the two housings 501, and the two fixing cavities 502 are combined to form a complete cylindrical cavity for accommodating and clamping the rear bearing 403; connecting parts 503 (such as ear plates) are provided on both sides of the two housings 501, and the two housings 501 are fastened together by bolts passing through fixing holes 505 on the connecting parts 503, thereby reliably fixing the rear bearing 403 inside the fixture; the bearing housing fixture 5 is bolted to the connecting flange 406 on the outside of the rear support 404 through the connecting holes 504 on its housings 501; the external installation dimensions, connection interface (i.e., the position and size of the connecting hole 504), and the structure of the internal fixing cavity 502 of the bearing housing fixture 5 are completely the same as the corresponding structure of the formal bearing housing fixture; this ensures the consistency of support stiffness and boundary conditions from the perspective of rotor dynamics.

[0041] Integrated measurement system: A piezoelectric sensor group 601 is integrated between the mounting interface of the base of the bearing housing fixture 5 and the connecting flange 406 of the rear bracket 404; at the same time, a key phase sensor 602 is installed on the outside of the bearing housing fixture 5 to detect the key phase mark on the rotating shaft 3.

[0042] Drive and calibration system: The drive mechanism is connected to the left end of the rotating shaft 3 via a connecting shaft; A window 101 is provided on the casing 1 facing the rotor calibration plane, and the window is normally sealed by a removable sealing plate 102;

[0043] The assembly, testing, and balancing process for the complete machine is as follows:

[0044] 1. Tooling installation: Install the rotor system into the casing 1; clamp and fix the rear bearing 403 inside the test bearing housing tooling 5 according to the aforementioned structure and method; then install the assembled test bearing housing tooling 5 onto the connecting flange 406 of the rear bracket 404 by passing bolts through the connecting hole 504.

[0045] 2. System Fixing and Connection: Fix the housing 1 using the support adapter 2; connect the drive mechanism; connect the signal output terminals of the piezoelectric sensor group 601 and the key phase sensor 602 to the balance analysis system via cables;

[0046] 3. Data Acquisition: Drive the rotor to rotate to the equilibrium speed; sensors collect data;

[0047] 4. Unbalance Calculation and Counterweight Command: The balance analysis system is configured to perform the following specific functions: receive the signal from the key phase sensor 602 as a reference; receive the signal from the piezoelectric sensor group 601 and perform signal conditioning (such as amplification and filtering) and spectrum analysis (such as Fast Fourier Transform FFT); calculate the magnitude and phase of the unbalance on the two correction planes based on the known influence coefficient method or least squares algorithm; and output counterweight addition commands to the operator.

[0048] 5. Counterweight operation: The operator, according to the instructions, removes the sealing plate 102 of the corresponding window 101 and uses tools to operate the counterweight mechanism on the rotor (such as the counterweight bolt in scheme P2);

[0049] 6. Verification: Repeat steps 3-5 (data acquisition and counterweight operation) until the balance is satisfactory;

[0050] 7. Final State Restoration: After balancing, disassemble the drive mechanism and connecting shaft; remove the bearing housing fixture 5 from the rear bracket 404, loosen the housing connecting bolts, open the two housings 501, and separate them from the rear bearing 403; then, connect the formal bearing housing fixture to the rear bearing 403, and install the formal fixture onto the rear bracket 404; finally, reinstall all the sealing plates 102.

[0051] Working principle: The device operates based on the principle of hard support dynamic balance measurement and the principle of consistency of boundary condition simulation; the piezoelectric sensor group 601 integrated between the detection bearing housing tooling 5 and the connecting flange 406 constitutes a high-rigidity measurement system. Its natural frequency is much higher than the rotor operating speed, which can directly and accurately measure the dynamic force vector caused by rotor imbalance, rather than vibration displacement. It has strong anti-interference ability and the measurement results are direct and accurate; the key phase sensor 602 provides an accurate phase reference.

[0052] The core function of the two housings 501 in the split housing design is to achieve non-destructive clamping and rapid transfer of bearings. It allows the rear bearing 403 to be securely and reliably fixed as a rigid module outside the casing, avoiding the high risks of press-fitting or impacting high-precision bearings in confined spaces, greatly improving operational safety and equipment reliability, and reducing the stringent requirements on operator skills. This device seamlessly integrates the high-precision dynamic balancing process into the final assembly process, eliminating the need for repeated rotor hoisting and disassembly, significantly shortening the engine's final assembly cycle and improving production efficiency.

[0053] Example 2:

[0054] Similar to Embodiment 1, but further: a dynamic stability adjustment device based on an aero-engine core provides three preferred counterweight installation position schemes:

[0055] Option P1 (counterweight plate option): Dedicated counterweight plates are machined or installed at the left and right ends of the roller 301 of the rotating shaft 3. The plate is provided with evenly distributed threaded holes or T-slots for installing counterweights or balance screws.

[0056] Option P2 (wheel disk option, preferred): directly utilize the existing largest diameter disk on the rotor assembly as the correction plane; that is, open mounting holes (such as evenly distributed threaded blind holes) on the last stage compressor disk of the high pressure rotor 302 and the turbine disk of the high vortex rotor 303 to screw in counterweight bolts of different specifications or install counterweight blocks.

[0057] Example 3:

[0058] Similar to Embodiment 1, but further: the rear bracket 404 has a hollow structure inside, and a telescopic rod 701 is installed on its inner wall. The output end of the telescopic rod 701 is fixedly connected to a connecting frame 702. Rollers 703 are rotatably connected to both sides of one end of the connecting frame 702. The outer wall of the roller 703 is in rolling connection with the outer wall of the roller 301. When it is necessary to remove the test bearing seat fixture 5, the telescopic rod 701 is controlled to drive the connecting frame 702 and the roller 703 to rise, so that they contact the outer wall of the roller 301.

[0059] Working principle: After balancing, disassemble the drive mechanism and connecting shaft; activate the telescopic rod 701 to raise the roller 703 to support the roller 301; remove the bearing housing fixture 5 from the rear bracket 404, loosen the housing connecting bolts, open the two housings 501, and separate them from the rear bearing 403; then, connect the formal bearing housing fixture to the rear bearing 403 and install the formal fixture onto the rear bracket 404; finally, retract the auxiliary support and reinstall all the sealing plates 102.

Claims

1. A dynamic stability adjustment device based on an aero-engine core, characterized in that, include: The fixed base includes a housing (1) and support adapters (2) fixed on both sides thereon. The rotor system includes a rotating shaft (3) housed inside the casing (1), on which a high-pressure rotor (302) and a high-vortex rotor (303) are fixedly mounted. At the standard support end, one end of the rotating shaft (3) is rotatably connected to the casing (1) via a front bearing (401) and a front bracket (402); The measuring support end, the other end of the rotating shaft (3) is connected to the housing (1) via a rear bearing (403), the measuring support end includes: The rear bracket (404) is fixed to the casing (1); The bearing housing fixture (5) is detachably mounted on the rear bracket (404) by fasteners, and has a cylindrical cavity inside for accommodating and clamping the rear bearing (403); and The integrated measurement system includes a piezoelectric sensor group (601) disposed between the detection bearing housing fixture (5) and the rear support (404), and a key phase sensor (602) for detecting the key phase mark on the rotating shaft (3). The external mounting dimensions, connection interface, and internal fixing cavity (502) structure of the bearing housing tooling (5) are exactly the same as the corresponding structure of the formal bearing housing tooling. The rear bracket (404) has a hollow structure inside, and a telescopic rod (701) is installed on its inner wall. A connecting frame (702) is fixedly connected to the output end of the telescopic rod (701). Rollers (703) are rotatably connected to both sides of one end of the connecting frame (702). The outer wall of the roller (703) is in rolling connection with the outer wall of the roller (301).

2. The dynamic stability adjustment device based on the core engine of an aero-engine according to claim 1, characterized in that, The bearing housing fixture (5) includes two symmetrical housings (501), and the inner sides of the two housings (501) are symmetrically provided with arc-shaped fixing cavities (502).

3. The dynamic stability adjustment device based on the core engine of an aero-engine according to claim 2, characterized in that, The two fixed cavities (502) are combined to form the cylindrical cavity; the two housings (501) are provided with connectors (503) on both sides, and the two housings (501) are fastened together by fasteners passing through the fixing holes (505) on the connectors (503).

4. The dynamic stability adjustment device based on the core engine of an aero-engine according to claim 1, characterized in that, A window (101) is provided on the casing (1) directly opposite the rotor correction plane.

5. The dynamic stability adjustment device based on the core engine of an aero-engine according to claim 4, characterized in that, The window (101) is sealed by a removable cover plate (102).

6. The dynamic stability adjustment device based on the core engine of an aero-engine according to claim 1, characterized in that, The rotor system is equipped with a counterweight structure.

7. The dynamic stability adjustment device based on the core engine of an aero-engine according to claim 6, characterized in that, The counterweight structure includes: counterweight discs with evenly distributed threaded holes or T-slots at both ends of the rollers (301) of the rotating shaft (3).

8. The dynamic stability adjustment device based on the core engine of an aero-engine according to claim 7, characterized in that, The counterweight structure includes: evenly distributed mounting holes on the final stage compressor disk of the high-pressure rotor (302) and the turbine disk of the high-vortex rotor (303).

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