CN209878307U - High-low cycle composite fatigue test device for rotor joggle joint structure of turbine engine - Google Patents
High-low cycle composite fatigue test device for rotor joggle joint structure of turbine engine Download PDFInfo
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Abstract
The utility model discloses a compound fatigue test device of turbine engine rotor joggle structure height week. The device comprises a high-speed rotation test system, a high-cycle excitation system, a microcomputer measurement and control system, a crack detection system and a high-speed slip ring. The high-speed slip ring is arranged on the high-speed rotation test system, transmits a signal of the crack detection system to the microcomputer measurement and control system, and transmits the signal of the microcomputer measurement and control system to the high-cycle excitation system. The scheme of the utility model adopts real blades and real mortises to excite vibration under the high-speed rotation state, thereby realizing the accurate transmission of high-cycle vibration load and low-cycle centrifugal load and solving the problems of accurately simulating the pressure distribution, temperature distribution and stress distribution of the joggle joint structure; the stress condition, the crack initiation position, the crack propagation rule and the like can be analyzed simply. The utility model discloses a compound fatigue test device of turbine engine rotor joggle structure height week has the accurate, the high characteristics of fatigue life prediction precision of simulation joggle structure atress.
Description
Technical Field
The utility model belongs to the technical field of be used for instructing or measuring the work piece characteristic, specifically be compound fatigue test device in turbine engine rotor joggle structure height week.
Background
The tenon joint structure is one of main forms of connection of a turbine disc and a blade of an aeroengine, has complex structure geometry, bears high temperature, centrifugal force and tangential air resistance of the blade during service, and bears complex thermal-mechanical alternating load and high and low cycle fatigue load, and is often a key area in which fatigue failure occurs. Therefore, the development of the fatigue test research of the joggle joint structure has important significance for preventing the structural failure, ensuring the safe and reliable operation of the wheel disc and the blade and ensuring the structural integrity and the reliability of the aero-engine.
In designing the fatigue test, the influence of the structure simplification and the loading factor on the fatigue failure mechanism needs to be considered, and the factors are all realized by various fatigue test devices. The existing joggle joint structure fatigue test device mainly comprises a single-axis or multi-axis fatigue test based on a material standard test piece, and a simulation piece bench test based on a phenanthrene wheel tester and the like. These experimental studies have presented the following problems: simplifying the tenon/mortise structure to a certain extent, neglecting the inclination angle and the curvature of the tenon structure, adopting a simplified linear model, and using a simulation blade and a clamp in order to require the contact of the contact surfaces on the two sides of the tenon/mortise to be uniform and achieve good assembly centering property; clamping is difficult and non-critical parts are easy to damage first; the stress state, the friction force and the relative displacement effect damage parameters of the contact area are difficult to measure; the clamping action of the clamp is difficult to accurately describe the centrifugal force of the blade, and meanwhile, due to the clamping action of the clamp, the high-cycle excitation effect of the blade is difficult to achieve, namely, the high-cycle load and the low-cycle load are interfered with each other, and the influence factors such as displacement amplitude, contact pressure, friction force and the like are uncontrollable. This results in difficulties in fully describing the multi-axial stress conditions to which real components are subjected, in accurately predicting the fatigue life of a dovetail structure, and therefore there are no recognized uniform specifications and standards. Thus, these devices suffer from a more or less poor prediction capability for high and low cycle composite fatigue life predictions for turbine engine rotor dovetail configurations. Therefore, the reliability test verification of the actual component under the action of the approximate multi-field load/environment needs to be carried out by carrying out the high-low cycle composite fatigue test research of the joggle joint structure in the high-speed rotation state, and meanwhile, the rationality of the simplifying device needs to be verified.
Disclosure of Invention
For solving the problem that there is a big error in the present turbine engine rotor joggle structure high low cycle compound fatigue life prediction method that proposes in the above-mentioned technical background, the utility model provides a high-speed rotating state is high low cycle compound fatigue research device of joggle structure down.
In order to achieve the above object, the utility model provides a following technical scheme is:
the high-low cycle compound fatigue test device of the turbine engine rotor joggle structure comprises a high-speed rotation test system, a high-cycle excitation system, a microcomputer measurement and control system, a crack detection system and a high-speed slip ring;
the high-speed rotation test system comprises a mandrel, a high-speed flexible shaft, a switching section, a turbine disc and blades; the mandrel and the high-speed flexible shaft are coaxially arranged, oil ducts which are mutually communicated are arranged in the mandrel and the high-speed flexible shaft, an oil duct inlet is positioned in the center of the end part of the high-speed flexible shaft, the oil ducts penetrate through the axial lead of the high-speed flexible shaft and enter the mandrel, and the oil ducts are communicated with an oil duct outlet positioned on the side wall of the mandrel after being opened with a certain length on the axial lead of the mandrel; the turbine disc is arranged at the bottom end of the mandrel through the switching section and rotates along with the mandrel; the turbine disc is fixed with the blade in a joggle mode;
the high-cycle excitation system comprises a high-frequency excitation cylinder, a bracket, a high-frequency excitation valve, an oil tank and an oil pump; the bracket is fixedly arranged on the mandrel; one end of the high-frequency excitation cylinder is fixed on the bracket, and the other end of the high-frequency excitation cylinder is in rigid contact with the blade; the high-frequency excitation cylinder is communicated with an oil pipe arranged on the bracket, and the oil pipe is communicated with an outlet of an oil channel arranged on the mandrel; an oil duct inlet on the high-speed flexible shaft is hermetically connected with an external oil pipe, the external oil pipe is connected with an oil tank, and a high-frequency excitation valve and an oil pump are arranged on the external oil pipe;
the crack detection system comprises a strain gauge, a pressure sensor, a displacement sensor and a high-speed camera; the strain gauge is adhered to the end part of a mortise of the engine rotor, the pressure sensor is arranged at the tenon joint of the turbine disc and the blade, the displacement sensor is adhered to the root part of the tenon of the engine rotor, and the high-speed camera focuses on the tenon joint of the turbine disc and the blade; signals of the strain gauge, the pressure sensor and the displacement sensor are connected with a moving ring wiring terminal of the high-speed slip ring through wires arranged in the mandrel and the high-speed flexible shaft, a static ring wiring terminal of the high-speed slip ring is connected with the microcomputer measurement and control system through the wires, the high-speed slip ring transmits detection signals acquired by the high-cycle excitation system and the crack detection system to the microcomputer measurement and control system, and transmits control signals of the microcomputer measurement and control system to the high-cycle excitation system. The high-speed camera is connected with the microcomputer measurement and control system to transmit the acquired images.
Further, the support contains a plurality of support arms that use the dabber axle center as the center, arrange along dabber radial direction, the dabber on set up with support arm quantity the same, and the position just to the oil duct export of support arm, a high frequency excitation jar is all installed to each support arm tip, high frequency excitation jar and the blade rigid contact that corresponds, an oil pipe is put to the equipartition on every support arm, oil pipe one end links to each other with high frequency excitation jar, the other end links to each other with the oil duct export that corresponds the position. The high-frequency excitation cylinders are controlled by the same high-frequency excitation valve, so that dynamic balance is ensured.
Further, the microcomputer measurement and control system comprises an industrial personal computer and a strain gauge (16); the industrial personal computer is respectively connected with the high-frequency excitation valve (14), the load sensor and the strain gauge and is used for controlling the connecting part and analyzing and processing signals processed by the strain gauge; the strain gauge is connected with a strain gauge (3), a pressure sensor (4) and a displacement sensor (5) in the crack detection system and used for carrying out dynamic strain sampling and transmission on the deformation of the end part of the mortise of the engine rotor and converting an analog signal into a digital signal.
Furthermore, a load sensor is arranged on the high-frequency excitation cylinder, and the load sensor is electrically connected with the microcomputer measurement and control system through a lead arranged in the core shaft and the high-speed flexible shaft and a high-speed slip ring positioned at the end part of the high-speed flexible shaft.
Furthermore, the end part of the oil passage inlet of the high-speed flexible shaft is hermetically connected with the shaft sleeve through a rotary oil seal, and the external oil pipe is hermetically connected with the shaft sleeve.
Furthermore, the high-frequency excitation system adopts an electro-hydraulic excitation mode and is suitable for a high-temperature environment.
Turbine engine rotor joggle structure high low week compound fatigue test device, its application method as follows:
(1) installing an engine rotor and a high-cycle excitation system;
(2) carrying out polishing treatment on the surfaces of a tenon and a mortise of an engine rotor, pasting a strain gauge on the end part of the mortise of the engine rotor, installing a pressure sensor at the tenon joint of a turbine disc and a blade, pasting a displacement sensor at the root part of the tenon of the blade, and focusing a high-speed camera on the tenon joint of the turbine disc and the blade;
(3) carrying out a high-frequency vibration test, wherein pressure oil in an oil tank enters a high-frequency excitation valve through an oil pipe under the action of an oil pump, a high-frequency excitation cylinder is controlled to work, so that the blades generate high-frequency forced vibration, and load oil pressure is measured through a load sensor on the high-frequency excitation cylinder;
(4) transmitting signals of a crack detection system to a microcomputer measurement and control system through a high-speed slip ring, wherein the signals of the crack detection system comprise strain gauge signals, pressure sensor signals and displacement sensor signals; the high-speed camera transmits the acquired image to a microcomputer measurement and control system;
(5) judging whether the stress-strain state and the distribution rule of the joggle structure in the high-cycle vibration test state meet the test requirements or not according to the crack detection system signal; if yes, entering the step (6); if not, adjusting the high-frequency excitation action, and repeating the steps (3) to (5) until the stress-strain state and the distribution rule of the joggle joint structure meet the test requirements;
(6) the oil pump stops supplying oil;
(7) carrying out a low-cycle test, starting a high-speed rotation test system, and rotating a mandrel;
(8) transmitting the crack detection system signal to a microcomputer measurement and control system through a high-speed slip ring; the high-speed camera transmits the acquired image to a microcomputer measurement and control system;
(9) judging whether the stress-strain state and the distribution rule of the joggle joint structure in the low-cycle test state meet the test requirements or not according to the crack detection system signal; if yes, entering the step (10); if not, adjusting the rotating speed of the mandrel, and repeating the steps (8) to (9) until the stress-strain state of the joggle joint structure and the distribution rule thereof meet the test requirements;
(10) carrying out high-low cycle compound fatigue test, and starting a high-speed rotation test system; pressure oil in the oil tank enters the high-frequency excitation valve through the oil pipe under the action of the oil pump to control the high-frequency excitation cylinder to work, and n is generated on the blade in each low-cycle2Performing forced vibration at the second high cycle, and measuring the load oil pressure through a load sensor;
(11) acquiring a crack detection system signal in real time, and transmitting the crack detection system signal to a microcomputer measurement and control system through a high-speed slip ring; the high-speed camera transmits the acquired image to a microcomputer measurement and control system;
(12) judging whether the stress-strain state of the joggle joint structure and the distribution rule thereof meet the test requirements or not in the high-low cycle composite fatigue test state according to the crack detection system signal; if so, n is completed1One cycle of low frequency, n1*n2The test was terminated after one high cycle; if not, adjusting the high-frequency excitation action, and repeating the steps (10) - (12) until the stress-strain state of the tenon joint structure and the distribution rule thereof meet the test requirements.
The utility model has the advantages that: the utility model adopts the real blade and the real tongue-and-groove, and the excitation is carried out under the high-speed rotation state, thereby being applicable to the normal temperature and the high temperature environment, realizing the accurate and independent transmission of the high-frequency vibration load and the low-frequency centrifugal load, and solving the problems of accurately simulating the pressure distribution, the temperature distribution and the stress distribution of the joggle joint structure; by formulating a fatigue test scheme, the stress condition, the crack initiation position, the crack propagation rule and the like can be analyzed simply. The utility model discloses a compound fatigue test device in turbine engine rotor joggle structure height week has the characteristics that simulation joggle structure atress is accurate, fatigue life prediction precision is high, has solved the compound tired technical weak point in current turbine engine rotor joggle structure height week. The high-frequency excitation cylinder rotates, noise is reduced, and excitation force is more stable.
Drawings
FIG. 1 is a block diagram of a high-low cycle composite fatigue testing apparatus for a turbine engine rotor dovetail structure;
FIG. 2 is a mechanical schematic diagram of a high-low cycle composite fatigue testing device for a turbine engine rotor dovetail structure;
FIG. 3 is a high-low cycle composite fatigue flow diagram for a turbine engine rotor dovetail configuration;
FIG. 4 is a high and low cycle composite fatigue loading spectrum;
in the figure, 1 a switching section, 2 a turbine disc, 3 strain gauges, 4 high-sensitivity pressure sensors, 5 displacement sensors, 6 blades, 7 high-frequency excitation cylinders and load sensors, 8 brackets, 9 oil pipes, 10 mandrels, 11 high-speed flexible shafts, 12 moving ring terminals, 13 static ring terminals, 14 high-frequency excitation valves, 15 oil tanks and oil pumps, 16 industrial personal computers, strain gauges and 17 high-speed slip rings.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
As shown in FIGS. 1-2, the high-low cycle compound fatigue test device for the dovetail structure of the turbine engine rotor comprises a high-speed rotation test system, a high-cycle excitation system, a microcomputer measurement and control system, a crack detection system and a high-speed slip ring.
The high-speed rotation test system comprises a mandrel 10, a high-speed flexible shaft 11, a switching section 1, a turbine disc 2 and blades 6; the mandrel and the high-speed flexible shaft are coaxially arranged, oil ducts which are mutually communicated are arranged in the mandrel and the high-speed flexible shaft, an oil duct inlet is positioned in the center of the end part of the high-speed flexible shaft, the oil ducts penetrate through the axial lead of the high-speed flexible shaft and enter the mandrel, and the oil ducts are communicated with an oil duct outlet positioned on the side wall of the mandrel after being opened with a certain length on the axial lead of the mandrel; the turbine disc is arranged at the bottom end of the mandrel through the switching section and rotates along with the mandrel; the turbine disc is fixed with the blade in a joggle mode;
the high-cycle excitation system adopts an electro-hydraulic excitation mode and comprises a high-frequency excitation cylinder 7, a bracket 8, a high-frequency excitation valve 14, an oil tank and an oil pump 15; the bracket 8 is fixedly arranged on the mandrel 10; one end of the high-frequency excitation cylinder 7 is fixed on the bracket, and the other end of the high-frequency excitation cylinder is in rigid contact with the blade; the high-frequency excitation cylinder is communicated with an oil pipe 9 arranged on the bracket 8, and the oil pipe 9 is communicated with an outlet of an oil channel arranged on the mandrel; an oil duct inlet on the high-speed flexible shaft 11 is hermetically connected with an external oil pipe, the external oil pipe is connected with an oil tank, and a high-frequency excitation valve 14 and an oil pump 15 are arranged on the external oil pipe;
the crack detection system comprises a strain gauge 3, a pressure sensor 4, a displacement sensor 5 and a high-speed camera; the strain gauge is adhered to the end part of a mortise of the engine rotor, the pressure sensor is arranged at the tenon joint of the turbine disc and the blade, the displacement sensor is adhered to the root part of the tenon of the engine rotor, and the high-speed camera focuses on the tenon joint of the turbine disc and the blade; the end of the high-speed flexible shaft is connected with a high-speed slip ring, signals of the strain gauge 3, the pressure sensor 4 and the displacement sensor 5 are connected with a moving ring terminal 12 of the high-speed slip ring through conducting wires arranged in the mandrel and the high-speed flexible shaft, a static ring terminal 13 of the high-speed slip ring is connected with a microcomputer measurement and control system through conducting wires, the high-speed slip ring transmits signals of the crack detection system to the microcomputer measurement and control system, and transmits the signals of the microcomputer measurement and control system to a high-cycle excitation system.
In a preferred embodiment of the present invention, the turbine disk 2 to be tested is installed on the high-speed rotation test system, and is driven by the high-speed rotation test system to perform a low-cycle fatigue cycle between the lowest rotation speed and the highest rotation speed.
The high-speed slip ring 17 is arranged on a high-speed rotation test system, transmits a signal of a crack detection system to the microcomputer measurement and control system, and transmits the signal of the microcomputer measurement and control system to the high-cycle excitation system.
The microcomputer measurement and control system comprises an industrial personal computer and a strain gauge 16; the industrial personal computer is used for controlling and signal analyzing and processing the high-speed rotation test system, the high-frequency excitation system and the measurement and control system; the strain gauge is used for dynamic strain sampling and transmission of deformation at the end of a mortise of an engine rotor and converting an analog signal into a digital signal.
In a preferred embodiment of the present invention, the support comprises a plurality of support arms, the mandrel is provided with oil channel outlets corresponding to the number and positions of the support arms, a high frequency excitation cylinder is installed at each end of the support arm, the high frequency excitation cylinder is in rigid contact with the corresponding blade, the oil pipe 9 is arranged on the support arm, one end of the oil pipe is connected with the high frequency excitation cylinder, and the other end of the oil pipe is connected with the oil channel outlet corresponding to the position.
In a preferred embodiment of the present invention, the high frequency excitation cylinder 7 is provided with a load sensor, the load sensor is electrically connected to the microcomputer measurement and control system through a wire arranged in the core shaft and the high speed flexible shaft and a high speed slip ring arranged at the end of the high speed flexible shaft, the oil passage inlet end of the high speed flexible shaft 11 is connected to the shaft sleeve through a rotary oil seal, and the external oil pipe is connected to the shaft sleeve in a sealing manner.
By adopting the high-speed slip ring, the utility model solves the problem of signal transmission of the turbine engine rotor in a high-speed rotation state; by adopting an electro-hydraulic excitation mode, the problem of high-cycle excitation in a high-temperature environment in a high-speed rotation state is solved; the aim of accurately identifying the stress-strain state of the joggle joint structure in a high-speed rotation state is fulfilled by arranging the strain gauge, the pressure sensor and the displacement sensor; by formulating a correct test scheme, the problems of high-low cycle composite fatigue life evaluation and the like in a high-speed rotation state are solved.
The use method of the high-low cycle composite fatigue test device for the rotor joggle structure of the turbine engine comprises the following steps:
(1) and installing an engine rotor and a high-cycle excitation system.
(2) And (4) performing smooth finish treatment on the surface of the joggle structure, welding a lead of the strain gauge, and wrapping the lead by using a polyethylene film. Pasting a strain gauge and a lead wire, pasting the strain gauge on the end part of a mortise of an engine rotor, checking the pasting quality of the strain gauge, and then arranging and fixing the lead wire of the strain gauge on the surface of a wheel disc by using an adhesive tape; meanwhile, a high-sensitivity pressure sensor and a displacement sensor are installed, the pressure sensor is installed at the tenon joint of the turbine disc and the blade, the displacement sensor is adhered to the root of the tenon of the engine rotor, and the high-speed camera focuses on the tenon joint of the turbine disc and the blade.
(3) And (3) carrying out a high-cycle fatigue test, supplying oil by an oil pump, allowing pressure oil in an oil tank to enter a high-frequency excitation valve through an oil pipe under the action of the oil pump, controlling a high-frequency excitation cylinder to work, allowing the blades to generate high-cycle forced vibration, and measuring load oil pressure by a load sensor.
(4) The strain gauge is used for measuring the strain of the joggle joint structure, the work of measuring the contact pressure and the displacement of the joggle joint structure is carried out simultaneously, signals of a crack detection system are transmitted to the strain gauge and the microcomputer measurement and control system through the high-speed slip ring, and the signals of the crack detection system comprise signals of the strain gauge, signals of a pressure sensor and signals of a displacement sensor.
(5) Judging whether the stress-strain state and the distribution rule of the joggle structure in the high-cycle vibration test state meet the test requirements or not according to the crack detection system signal; if yes, entering the step (6); if not, adjusting the high-frequency excitation action, and repeating the steps (3) - (5) until the stress-strain state of the joggle joint structure and the distribution rule thereof meet the test requirements.
(6) The oil pump stops supplying oil.
(7) And (4) carrying out a low-cycle test, starting a high-speed rotation test system, and rotating the mandrel.
(8) Measuring the strain of the joggle joint structure by using a strain gauge, and transmitting a signal to a strain gauge through a high-speed slip ring; and simultaneously, carrying out the measurement work of the contact pressure and the displacement of the joggle joint structure.
(9) Judging whether the stress-strain state of the joggle joint structure and the distribution rule thereof meet the test requirements or not in the low-cycle test state according to the crack detection system signal; if yes, entering the step (10); if not, adjusting the rotating speed of the mandrel, and repeating the steps (8) to (9) until the stress-strain state of the joggle joint structure, the distribution rule thereof and the like meet the test requirements.
(10) The high and low cycle composite fatigue test is carried out, and the high and low cycle composite fatigue load spectrum is shown in figure 4(in the figure, the horizontal axis represents time t, and the vertical axis represents stress, σhFor high cyclic stress amplitude, σlLow cyclic stress amplitude). The core shaft rotates, the rotating speed of the rotor of the engine is increased from the lowest rotating speed to the highest rotating speed, and the rotor of the engine stays at the highest rotating speed; during the stay period, oil is supplied by the oil pump, the high-frequency excitation valve is actuated, the high-frequency excitation cylinder acts on the blade, and the blade generates n2Performing forced vibration at the next higher cycle, and measuring the load oil pressure; completing high-cycle excitation, stopping oil supply, reducing the rotating speed from the highest rotating speed to the lowest rotating speed, and completing a low-cycle, n2And (4) circulating at a high cycle.
(11) The strain gauge is used for measuring the strain of the joggle joint structure, and a signal is transmitted to the strain gauge and the microcomputer measurement and control system through the high-speed slip ring; and simultaneously, carrying out the measurement work of the contact pressure and the displacement of the joggle joint structure.
(12) And judging that the strain, the contact pressure, the displacement signal and the test requirement meet the test requirement in the high-low cycle composite fatigue test state. If so, n is completed1One cycle of low frequency, n1*n2The test was terminated after one high cycle; if not, repeating the steps (10) - (12) by adjusting the high-frequency excitation action until the stress-strain state of the tenon joint structure and the distribution rule thereof meet the test requirements.
Claims (5)
1. A high-low cycle composite fatigue test device of a turbine engine rotor joggle joint structure is characterized by comprising a high-speed rotation test system, a high-cycle excitation system, a microcomputer measurement and control system, a crack detection system and a high-speed slip ring (17);
the high-speed rotation test system comprises a mandrel (10), a high-speed flexible shaft (11), a switching section (1), a turbine disc (2) and blades (6); the mandrel and the high-speed flexible shaft are coaxially arranged, oil ducts which are mutually communicated are arranged in the mandrel and the high-speed flexible shaft, an oil duct inlet is positioned in the center of the end part of the high-speed flexible shaft, the oil ducts penetrate through the axial lead of the high-speed flexible shaft and enter the mandrel, and the oil ducts are communicated with an oil duct outlet positioned on the side wall of the mandrel after being opened with a certain length on the axial lead of the mandrel; the turbine disc is arranged at the bottom end of the mandrel through the switching section and can rotate along with the mandrel; the turbine disc is fixed with the blade in a joggle mode;
the high-cycle excitation system comprises a high-frequency excitation cylinder (7), a bracket (8), a high-frequency excitation valve (14), an oil tank and an oil pump (15); the bracket (8) is fixedly arranged on the mandrel (10); one end of the high-frequency excitation cylinder (7) is fixed on the bracket, and the other end of the high-frequency excitation cylinder is in rigid contact with the blade; the high-frequency excitation cylinder is communicated with an oil pipe (9) arranged on the support (8), and the oil pipe (9) is communicated with an oil passage outlet arranged on the mandrel; an oil duct inlet on the high-speed flexible shaft (11) is hermetically connected with an external oil pipe, the external oil pipe is connected with an oil tank, and a high-frequency excitation valve (14) and an oil pump (15) are arranged on the external oil pipe;
the crack detection system comprises a strain gauge (3), a pressure sensor (4), a displacement sensor (5) and a high-speed camera; the strain gauge is adhered to the end part of a mortise of the engine rotor, the pressure sensor is arranged at the tenon joint of the turbine disc and the blade, the displacement sensor is adhered to the root part of the tenon of the engine rotor, and the high-speed camera focuses on the tenon joint of the turbine disc and the blade; signals of the strain gauge (3), the pressure sensor (4) and the displacement sensor (5) are connected with a moving ring terminal (12) of the high-speed slip ring through leads arranged in the mandrel and the high-speed flexible shaft, a static ring terminal (13) of the high-speed slip ring is connected with a microcomputer measurement and control system through a lead, the high-speed slip ring transmits detection signals acquired by the high-cycle excitation system and the crack detection system to the microcomputer measurement and control system, and transmits control signals of the microcomputer measurement and control system to the high-cycle excitation system; the high-speed camera is connected with the microcomputer measurement and control system to transmit the acquired images.
2. The high-low circumference compound fatigue test device of the turbine engine rotor joggle structure according to claim 1, characterized in that the support contains a plurality of support arms that use the dabber axle center as the center, arrange along dabber radius direction, the dabber on set up with support arm quantity the same, just the position is to the oil duct export of support arm, a high frequency excitation jar is all installed to each support arm tip, high frequency excitation jar and the blade rigid contact that corresponds, an oil pipe (9) is evenly arranged on every support arm, oil pipe (9) one end links to each other with high frequency excitation jar, the other end links to each other with the oil duct export that corresponds the position.
3. The high-low circumference composite fatigue test device of the turbine engine rotor joggle joint structure according to claim 1, characterized in that the high-frequency excitation cylinder (7) is provided with a load sensor, the load sensor is connected with the high-speed slip ring through a lead arranged inside the core shaft and the high-speed flexible shaft, and is electrically connected with the microcomputer measurement and control system through the high-speed slip ring.
4. The high-low cycle composite fatigue test device for the rotor joggle structure of the turbine engine as claimed in claim 3, characterized in that the microcomputer measurement and control system comprises an industrial personal computer and a strain gauge (16); the industrial personal computer is respectively connected with the high-frequency excitation valve (14), the load sensor and the strain gauge; the strain gauge is connected with a strain gauge (3), a pressure sensor (4) and a displacement sensor (5) in the crack detection system and used for carrying out dynamic strain sampling and transmission on the deformation of the end part of the mortise of the engine rotor and converting an analog signal into a digital signal.
5. The high-low circumference composite fatigue test device for the rotor joggle structure of the turbine engine according to claim 1, characterized in that the inlet end of the oil passage of the high-speed flexible shaft (11) is hermetically connected with a shaft sleeve through a rotary oil seal, and the external oil pipe is hermetically connected with the shaft sleeve.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110389024A (en) * | 2019-06-17 | 2019-10-29 | 浙江大学 | A kind of all composite fatigue experimental rigs of turbine engine rotor mortise structure height and method |
| CN114112256A (en) * | 2021-10-20 | 2022-03-01 | 中国航发四川燃气涡轮研究院 | Excitation device and excitation method for rotor dynamics test |
| CN115307855A (en) * | 2022-07-21 | 2022-11-08 | 南京航空航天大学 | Rotor blade high cycle fatigue test method and device considering centrifugal force effect |
-
2019
- 2019-06-17 CN CN201920907118.0U patent/CN209878307U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110389024A (en) * | 2019-06-17 | 2019-10-29 | 浙江大学 | A kind of all composite fatigue experimental rigs of turbine engine rotor mortise structure height and method |
| CN114112256A (en) * | 2021-10-20 | 2022-03-01 | 中国航发四川燃气涡轮研究院 | Excitation device and excitation method for rotor dynamics test |
| CN114112256B (en) * | 2021-10-20 | 2023-06-13 | 中国航发四川燃气涡轮研究院 | Exciting device and exciting method for rotor dynamics test |
| CN115307855A (en) * | 2022-07-21 | 2022-11-08 | 南京航空航天大学 | Rotor blade high cycle fatigue test method and device considering centrifugal force effect |
| CN115307855B (en) * | 2022-07-21 | 2023-07-04 | 南京航空航天大学 | Rotor blade high-cycle fatigue test method and device considering centrifugal force effect |
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