CN102539135A - Thermal mechanical fatigue test system for hollow air-cooled turbine blade - Google Patents
Thermal mechanical fatigue test system for hollow air-cooled turbine blade Download PDFInfo
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- CN102539135A CN102539135A CN2011104601314A CN201110460131A CN102539135A CN 102539135 A CN102539135 A CN 102539135A CN 2011104601314 A CN2011104601314 A CN 2011104601314A CN 201110460131 A CN201110460131 A CN 201110460131A CN 102539135 A CN102539135 A CN 102539135A
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Abstract
The invention discloses a thermal mechanical fatigue test system for a hollow air-cooled turbine blade, which includes a loading subsystem, a heating subsystem, an air cooling subsystem, a water cooling subsystem and a controlling subsystem, wherein the loading subsystem vertically clamps the turbine blade; the heating subsystem is horizontally placed in the middle part of the loading subsystem for heating the turbine blade; the air cooling subsystem is horizontally arranged and connected with the loading subsystem through a pipeline; the water cooling subsystem is horizontally arranged and connected with the loading subsystem and the heating subsystem through the pipeline; and the controlling subsystem is arranged at the upper part of the heating subsystem and connected with the loading subsystem, the heating subsystem and the air cooling subsystem through a cable. The thermal mechanical fatigue test system is used for simulating the working stress field, the temperature field and the loading spectrum of the examination cross section of the hollow air-cooled turbine blade. The thermal mechanical fatigue test system satisfactorily overcomes the difficulty for simulating the working stress field, the temperature field and the loading spectrum of the examination cross section of the hollow air-cooled turbine blade, and provides the technical basis and the safety guarantee for the safe and reliable working of the aero engine.
Description
(1) technical field
The present invention relates to aero engine turbine blades thermal mechanical fatigue pilot system; Particularly relate to a kind of hollow cooled turbine blade thermal mechanical fatigue pilot system; It is a kind of test unit that can simulate turbo blade examination section stress field, temperature field and loading spectrum, belongs to the Aero-Space technical field of engines.
(2) background technology
The thermal mechanical fatigue of gas-turbine blade (TMF) fault is aeromotor one of topmost failure type during one's term of military service, is to influence the engine turbine blade principal element in serviceable life.At present, the thermal mechanical fatigue test for nickel-base high-temperature single crystal alloy is similar to test specimen based on standard specimen and blade mostly.And actual turbine rotor blade will bear load such as centrifugal force, aerodynamic force in the course of the work, produce stretch, reverse, flexural deformation, be multi-axis stress state; For the turbo blade that has inner chamber, in heating/cooling procedure, positions such as film cooling holes limit and turbulence columns chamfering can produce bigger thermograde, cause significant stress to concentrate, and possibly cause the germinating of crackle.Above-mentioned characteristic is that the approximate test specimen of standard specimen and blade is difficult to simulate.And for monocrystal material, the nuance of technological process and sampling can cause the difference of mechanical property.Therefore, the thermal mechanical fatigue test of carrying out true turbo blade for turbo blade in design the analysis of deciding longevity research, blade fault and prevent significant.
The turbo blade thermal mechanical fatigue pilot system that Russia Central Institute of Aviation Motors (CIAM) develops requires to use the fatigue tester that stretching and torsional load can be provided, and present general fatigue tester can only provide the tensile load of single shaft; This pilot system does not comprise the air cooling subsystem, can't simulate the cooling procedure of hollow turbine vane.The A714D cooled turbine blade heat of Shenyang engine design Research Institute/mechanical compound fatigue tester adopts the nylon tension belt that mechanical load is delivered on the blade, and adjusts the stress distribution of turbo blade through the angle that changes nylon tape and blade; But nylon is wear-resisting, high temperature resistant, tensile strength all is worse than steel; And the environment temperature of thermal mechanical fatigue test unit mechanical load higher, that bear is bigger; Test of long duration can cause problems such as the wearing and tearing of nylon, aging, elongation, causes the loading spectrum control accuracy of this exerciser lower.
(3) summary of the invention
(1) goal of the invention
The invention provides a kind of hollow cooled turbine blade thermal mechanical fatigue pilot system; It has overcome the deficiency of prior art; Preferably resolve the difficult point of hollow cooled turbine blade examination working stress field, cross section, temperature field and loading spectrum simulation; Guaranteed carrying out smoothly of aero engine turbine blades thermal mechanical fatigue test, for the safe and reliable work of aeromotor provides technical foundation and safety guarantee.
(2) technical scheme
A kind of hollow cooled turbine blade thermal mechanical fatigue pilot system of the present invention; Mainly comprise 5 sub-systems: load subsystem, the subsystem of heating, air cooling subsystem, water-cooled subsystem and RACS, the position annexation between them is: load subsystem in the vertical direction clamping turbo blade; The subsystem of heating is placed horizontally at and loads the subsystem middle part, and turbo blade is heated; Air cooling subsystem horizontal positioned links to each other with the loading subsystem through pipeline; Water-cooled subsystem horizontal positioned links to each other with the subsystem of heating with the loading subsystem through pipeline; RACS is positioned over the subsystem top of heating, and links to each other with loading subsystem, the gentle hail of the subsystem of heating system through cable.The present invention can be used for the simulation of hollow cooled turbine blade examination working stress field, cross section, temperature field and loading spectrum.
Said loading subsystem is made up of fatigue tester and turbo blade unit clamp, behind the turbo blade unit clamp clamping turbo blade, is placed on the chuck of fatigue tester again; It is used to provide the thermal mechanical fatigue test required mechanical load.Fatigue tester is that choose in market, and the tensile load of single shaft can be provided.The turbo blade unit clamp is Design and Machining voluntarily, and material is a heat-resisting alloy mould steel, the surface processing of turning blue.The turbo blade unit clamp is made up of last fork block, following fork block, pin (* 4), fork (* 2), the approximate part of the turbine disk, baffle plate (* 2), screw (* 4), hold-down bolt (* 4), blade built-up jig and pad (* 40).Wherein, upper and lower fork block is the step shaft-like part, is individually fixed in the upper and lower chuck of fatigue tester; Fork 11,3 is connected with upper and lower fork block through pin 12,2; Fork 11 is connected with blade built-up jig 9 through pin 10; Baffle plate is connected through the approximate part of the screw 7 and the turbine disk; The approximate part of the turbine disk is fixed on the fork 3 with pin 4 through the pin hole that is provided with on it.This fork is provided with the Y shape part of through hole for it; The approximate part of this turbine disk is its T profiles that is provided with through hole, blind hole and tongue-and-groove; This baffle plate is its rectangular slab materials and parts that are provided with through hole; This blade built-up jig is branch half formula step rectangle sheet construction, and is respectively arranged with endoporus, water-cooled hole and vent port: its endoporus matches with the integral shroud of workpiece for measurement turbo blade, is used to transmit mechanical load, and hole number is one; Its water-cooled hole links to each other with the water-cooled subsystem, is used for the cooled blade built-up jig, and hole number is one; Its vent port is used to discharge the inside cooling draught of turbo blade, and hole number is two.4 hold-down bolts 8 are fixed together two parts of blade built-up jig, see Fig. 3.For the ease of the reliable delivery of mechanical load, for not with the turbo blade of integral shroud, need be at the blade tip position of turbo blade through casting or weld special-shaped integral shroud.The tenon of turbo blade matches with the tongue-and-groove of the approximate part of the turbine disk, is used to simulate the mounting condition of turbo blade on the turbine disk.The approximate part of the turbine disk has the air cooling passage, links to each other with the air cooling subsystem; Cooling draught enters into the inner chamber of turbo blade through the air cooling passage, carries out the inside cooling of turbo blade.2 baffle plates prevent to skid off when turbo blade from bearing mechanical load the leakage of tongue-and-groove and cooling draught through the both sides of 4 screw retention at the approximate part tongue-and-groove of the turbine disk.4 pins connect fork block 1 and fork 3, fork 3 and the approximate part 5 of the turbine disk, blade built-up jig 9 and fork 11, fork 11 and last fork block 13 down respectively.Be reserved with gap (thickness of the size=pad in gap * 10) between two parts that each pin connects, can insert 10 pads just.The assembly that is connected by pin is called the joint, and this turbine unit clamp has 4 joints.Through the combination (promptly changing the number of the left and right sides, gap pad) that changes each joint pad; Can adjust the angle of turbo blade and fatigue tester main shaft; Realize the eccentric tension of turbo blade, the tensile load of single shaft is decomposed the turbo blade of sening as an envoy to produce component crooked, torsional deflection.In conjunction with said method, adjust the tensile load of fatigue tester simultaneously, can realize the simulation of turbo blade examination working stress field, cross section.
The said subsystem of heating is made up of high-frequency induction furnace and load coil, connects mutually therebetween; It is used to provide the thermal mechanical fatigue test required thermal force.High-frequency induction furnace is that choose in market.Load coil is a self design, adopts two-tube branch half formula structure, sees Fig. 9, and it is made up of 2 copper pipes, connecting copper piece and plastic water pipes, the two ends of plastic water pipe respectively with an end socket of 2 copper pipes, connecting copper piece is fixed together 2 copper pipes.2 copper pipes and connecting copper piece constitute current return; 2 copper pipes and plastic water pipe constitute the chilled(cooling) water return (CWR).Load coil links to each other with high-frequency induction furnace, and copper pipe inside is connected with chilled water.Through the shape of change load coil and the distance of load coil and turbine blade surface, can cause different magnetic leakages in different zones, produce required thermograde at turbine blade surface.In conjunction with said method, adjust the power input of high-frequency induction furnace simultaneously, can realize the simulation of turbo blade examination working temperature field, cross section.
Said air cooling subsystem is made up of air compressor, decompression venting valve, air mass flow amount controller and three-way connection, connects mutually through pipeline therebetween; It is used to provide the thermal mechanical fatigue test required cooling draught.Air compressor, decompression venting valve, air mass flow amount controller, pipeline and three-way connection are market and choose.Air compressor provides continuously but pressure, all unsettled air-flow of flow; Behind decompression venting valve, it is constant that air-flow pressure keeps; Behind the air mass flow amount controller, it is constant that air flow rate keeps.Exit at the air mass flow amount controller is equipped with three-way connection.An outlet of three-way connection links to each other with the air cooling passage of the approximate part of the turbine disk, is used to simulate the inside cooling of turbo blade; Another outlet is equipped with normally closed solenoid valve, and by RACS control, is used to simulate the external forced cooling of turbo blade.
Said water-cooled subsystem is made up of water pump and water storage tank, connects mutually through pipeline therebetween; It is used for the cooling of thermal mechanical fatigue process of the test instrument and equipment.Water pump, pipeline and water storage tank are market and choose.Be divided into two parts after the chilled water process water pump supercharging in the water storage tank: a part gets into high-frequency induction furnace, is used to cool off high-frequency induction furnace and load coil; Another part gets into the water-cooled hole of blade built-up jig, is used for the cooled blade built-up jig.Two parts chilled water is got back to water storage tank after accomplishing the cooling to instrument and equipment, constitutes the chilled water circulation.
Said RACS is made up of load controller, temperature controller and normally closed solenoid valve, connects mutually through cable therebetween; It is used for the synchro control of each subsystem of thermal mechanical fatigue test.Load controller is equipped with by fatigue tester, input mechanical load waveform, output mechanical load voltage signal.The mechanical load voltage signal divides two-way: the one tunnel is input to fatigue tester, and the turbo blade unit clamp is loaded; Another road is input to temperature controller.Temperature controller is design voluntarily, and matches with high-frequency induction furnace, input mechanical load voltage signal, and according to the increase of mechanical load voltage signal/reduce, the ON/OFF signal of output high-frequency induction furnace and the pass of normally closed solenoid valve/open signal.Normally closed solenoid valve is that choose in market.
(3) advantage and effect
A kind of hollow cooled turbine blade thermal mechanical fatigue pilot system of the present invention, compared with prior art, advantage is:
The first, the turbo blade unit clamp that adopts stainless steel to make can transmit mechanical load reliably; Through changing the combination of joint pad, can adjust the angle of turbo blade and fatigue tester main shaft simply and easily, realize the simulation of turbo blade examination working stress field, cross section.
The second, load coil adopts two-tube branch half formula structure, utilizes connecting copper piece and plastic water pipe, and current return and chilled(cooling) water return (CWR) are separated, and can produce complex-shaped load coil, and be convenient to dismounting; The use of connecting copper piece has increased the stability of load coil, and has reduced the contact resistance of copper pipe, has avoided load coil overheated.
The 3rd; Adopt decompression venting valve and air mass flow amount controller; Can accurately control the cooling gas flow of turbo blade, and combine the use of three-way connection and normally closed solenoid valve, the variation of the inside and outside cooling draught of turbo blade in the time of can simulating the aeromotor parking.
The 4th, utilize RACS will load, heat and the air cooling process has been carried out synchro control, can simulate the loading spectrum of turbo blade thermal mechanical fatigue test more accurately.
(4) description of drawings
The loading spectrum synoptic diagram of Fig. 1 thermal mechanical fatigue testing requirements
Fig. 2 thermal mechanical fatigue test system architecture block diagram
Fig. 3 turbo blade unit clamp positive two is surveyed view
Fig. 4 integral shroud vertical view
Fig. 5 (a) blade built-up jig front view
Fig. 5 (b) blade built-up jig left view
Fig. 5 (c) blade built-up jig cut-open view
Fig. 6 (a) turbine disk is similar to the test specimen front view
Fig. 6 (b) turbine disk is similar to the test specimen left view
Fig. 7 (a) pad front view
Fig. 7 (b) pad left view
Fig. 8 (a) left and right sides, gap pad number is 0-10;
Fig. 8 (b) left and right sides, gap pad number is 5-5;
Fig. 8 (c) left and right sides, gap pad number is 10-0
The two-tube branch half formula load coil vertical view of Fig. 9
Symbol description is following among the figure:
1: following fork block 16: copper pipe
2: pin 17: copper pipe
3: fork 18: connecting copper piece
4: pin 19: plastic water pipe
5: 1. the turbine disk is similar to part: the endoporus of blade built-up jig 9
6: baffle plate (* 2) 2.: the water-cooled hole of blade built-up jig 9
7: screw 3.: the vent port of blade built-up jig 9
8: hold-down bolt (* 4) 4.: the air cooling passage of the approximate test specimen 5 of the turbine disk
9: blade built-up jig F: mechanical load/kN
10: pin T: temperature/℃
11: fork t: time/s
12: pin O-A: load phase
13: go up fork block A-B: peak value keeps the stage
14: turbo blade B-C: unloading phase
15: pad C-D: valley keeps the stage
(5) embodiment
Below in conjunction with accompanying drawing, be that the technical scheme that realization examination working stress field, cross section, temperature field and loading spectrum simulation are taked further specifies to a kind of hollow cooled turbine blade thermal mechanical fatigue pilot system of the present invention.The loading spectrum of hollow cooled turbine blade thermal mechanical fatigue test is as shown in Figure 1, is divided into loading (O-A), peak value maintenance (A-B), unloading (B-C) and valley and keeps (C-D) four-stage.The examination cross section of turbo blade is the blade middle section.Through Finite Element Method, the peak value that calculates at loading spectrum keeps the stage turbo blade to examine the working stress field and the temperature field in cross section, and with this target as stress field under the test condition and temperature field simulation.Hollow cooled turbine blade thermal mechanical fatigue pilot system is formed as shown in Figure 2.
(1) simulation of turbo blade examination working stress field, cross section
The simulation of turbo blade examination working stress field, cross section realizes through loading subsystem.Under test condition, the stress field of turbo blade depends on the tensile load of fatigue tester and the angle of turbo blade and fatigue tester main shaft.
The mechanical load of hollow cooled turbine blade thermal mechanical fatigue pilot system is produced by fatigue tester.The turbo blade unit clamp is as shown in Figure 3, by down fork block 1, pin 2, fork 3, pin 4, the approximate part 5 of the turbine disk, baffle plate 6 (* 2), screw 7 (* 4), hold-down bolt 8 (* 4), blade built-up jig 9, pin 10, fork 11, pin 12, go up fork block 13 and pad 15 (* 40) constitutes.Wherein, last fork block 13 and following fork block 1 are individually fixed in the upper and lower chuck of fatigue tester.For the ease of the reliable delivery of mechanical load, for not with the turbo blade of integral shroud, need or weld special-shaped integral shroud in the casting of the blade tip position of turbo blade, as shown in Figure 4.Blade built-up jig 9 is for dividing half a formula formula step rectangle sheet construction, have endoporus 1., the water-cooled hole 2. with vent port 3., shown in Fig. 5 (a) and (b), (c).1. the endoporus of blade built-up jig 9 matches with the integral shroud of turbo blade 14, is used to transmit mechanical load; 2. the water-cooled hole links to each other with the water-cooled subsystem, is used for cooled blade built-up jig 9, prevents that blade built-up jig 9 is because the overheated undercapacity that causes in the thermal mechanical fatigue process of the test; 3. vent port is used to discharge the inside cooling draught of turbo blade 14.Hold-down bolt 8 is fixed together two parts of blade built-up jig 9.The tenon of turbo blade 14 matches with the tongue-and-groove of the approximate part 5 (Fig. 6 (a) and (b)) of the turbine disk, is used to simulate the mounting condition of turbo blade on the turbine disk.The approximate part 5 of the turbine disk has air cooling passage 4. (Fig. 6 (a) and (b)), links to each other with the air cooling subsystem; 4. cooling draught enters into the inner chamber of turbo blade 14 through the air cooling passage, carries out the inside cooling.Baffle plate 6 is fixed on the both sides that the turbine disk is similar to part 5 tongue-and-grooves through screw 7, prevents that turbo blade 14 from skidding off the leakage of tongue-and-groove and cooling draught when bearing mechanical load.
The tensile load that fatigue tester produces is delivered to the turbine disk and is similar to part 5 behind fork block 1, pin 2, fork 3, pin 4 down; The tongue-and-groove of the approximate part 5 of the turbine disk matches with the tenon of turbo blade 14, and mechanical load is delivered on the turbo blade 14; 1. the integral shroud of turbo blade 14 matches with the endoporus of blade built-up jig 9, and mechanical load is continued upwards to transmit; Behind mechanical load via pins 10, fork 11, the pin 12, be passed to fork block 13.
The assembly that is connected by pin 2,4,10 and 12 is called the joint, and the turbo blade unit clamp has four joints: following fork block 1 and fork 3 that pin 2 connects; Fork 3 that pin 4 connects and the approximate part 5 of the turbine disk; Blade built-up jig 9 and fork 11 that pin 10 connects; Fork 11 and last fork block 13 that pin 12 connects.Be reserved with gap (thickness of the size=pad in gap * 10) between two parts that each pin connects, can insert 10 pads 15 just, pad 15 is shown in Fig. 7 (a) and (b).(joint that following fork block 1, pin 2 and fork 3 constitute is an example in combination through changing each joint pad 15; Shown in Fig. 8 (a) and (b), (c); The number of the left and right sides, gap pad 15 is respectively 0-10,5-5,10-0); Can adjust the angle of turbo blade 14 and fatigue tester main shaft, realize the eccentric tension of turbo blade 14, the tensile load of single shaft decomposed the turbo blade 14 of sening as an envoy to produce component crooked, torsional deflection.In conjunction with said method, adjust the tensile load of fatigue tester simultaneously, can realize the simulation of working stress field, turbo blade 14 examination cross section.
The material of turbo blade unit clamp is 30CrMnSiA, the surface processing of turning blue.Fatigue tester is the Css-280 electo hydraulic servocontrolled fatigue testing machine, maximum load ± 100kN, and load controller is equipped with.
(2) simulation of turbo blade examination working temperature field, cross section
Simulation to working temperature field, turbo blade 14 examination cross section need be by the gentle hail of the subsystem of heating system.Under test condition, distance, the power input of high-frequency induction furnace and the cooling gas flow of turbo blade 14 on the shape of load coil, load coil and turbo blade 14 surfaces depended in the temperature field of turbo blade 14.Loading and peak value at loading spectrum keep the stage, and turbo blade 14 inside are connected with the cooling draught of 0.1MPa, 8g/s, and amounting to volumetric flow rate is 371SLPM (standard liter/min).
1) turbo blade 14 inner colded simulations
It is big that hollow cooled turbine blade thermal mechanical fatigue is tested required cooling gas flow, and require pressure, the constant flow of air-flow.Cooling draught is provided by the air cooling subsystem.The air cooling subsystem is made up of air compressor, decompression venting valve, air mass flow amount controller and three-way connection, and is as shown in Figure 2.Air compressor provides continuously but pressure, all unsettled air-flow of flow; Air-flow is behind decompression venting valve, and pressure stabilizes to 0.45MPa; Air-flow is behind the air mass flow amount controller, and stability of flow is 371SLPM.Exit at the air mass flow amount controller is equipped with three-way connection.4. an outlet of three-way connection links to each other with the air cooling passage of the approximate part 5 of the turbine disk, and another outlet is equipped with normally closed solenoid valve.Loading and the peak value maintenance stage; Normally closed solenoid valve is closed; Cooling draught all through the air cooling passage of the approximate part 5 of the turbine disk 4.; Tenon bottom by turbo blade 14 gets into its inner chamber, and discharges from film cooling holes, blade tip vent port and trailing edge vent port, accomplishes the inside cooling to turbo blade 14.
The air compressor model is TA-125, air capacity 2.0m
3/ min, power 15kW, the highest discharge pressure 0.7MPa; The decompression venting valve model is QTY-25, range of regulation 0.05～0.85MPa, maximum input pressure 1MPa; Air mass flow amount controller model is V10FC-VC, flow control scope 250～500SLPM, maximum withstand voltage 1MPa, operting differential pressure 0.03～0.5MPa, accuracy ± 0.8%.
2) heat fatigue load applies
Turbo blade thermal mechanical fatigue testing requirements rate temperature change is fast, adopts the mode of high-frequency induction to heat.The thermal force of the hollow air turbine blade of the present invention thermal mechanical fatigue pilot system is provided by high-frequency induction furnace.
The used load coil of the present invention adopts two-tube branch half formula structure; Constitute by copper pipe 16, copper pipe 17, connecting copper piece 18 and plastic water pipe 19; The two ends of plastic water pipe 19 respectively with an end socket of copper pipe 16,17, connecting copper piece 18 is fixed together copper pipe 16,17; As shown in Figure 9.Copper pipe 16, copper pipe 17 and connecting copper piece 18 constitute current return; Copper pipe 16, copper pipe 17 and plastic water pipe 19 formation chilled(cooling) water return (CWR)s.Load coil directly links to each other with high-frequency induction furnace.Through the shape of change load coil and the distance of load coil and turbo blade 14, can cause different magnetic leakages in different zones, produce required thermograde on the surface of turbo blade 14.In conjunction with said method, adjust the power input of high-frequency induction furnace simultaneously, can realize the simulation of working temperature field, turbo blade 14 examination cross section.
The high-frequency induction furnace model is SPG-30B, power input 5～30kW, and oscillation frequency 50～200kHz, chilled water requires 0.2MPa, 6L/min, and is equipped with temperature controller.
(3) simulation of turbo blade examination cross section loading spectrum
Thermal mechanical fatigue test load spectrum requires stress and the temperature in turbo blade 14 examination cross sections to change simultaneously, need be to loading, heat and the air cooling subsystem carries out synchro control.The synchro control of each subsystem is accomplished by RACS.
RACS is made up of load controller, temperature controller and normally closed solenoid valve, and is as shown in Figure 2.Load controller input mechanical load waveform, output mechanical load voltage signal is to fatigue tester and temperature controller.After fatigue tester receives the mechanical load voltage signal, the turbo blade unit clamp is loaded.After temperature controller receives the mechanical load signal; According to the increase of mechanical load voltage signal/reduce; The ON/OFF signal of output high-frequency induction furnace and the pass of normally closed solenoid valve/open signal: when the mechanical load voltage signal increases; High-frequency induction furnace is opened, and turbo blade 14 is heated; When the mechanical load voltage signal reduced, high-frequency induction furnace was closed, and opened normally closed solenoid valve simultaneously, made half the cooling draught directly blow to turbo blade 14 surfaces, and air is to the external forced cooling of turbo blade 14 when being used to simulate the aeromotor parking; When the mechanical load voltage signal was constant, the state of high-frequency induction furnace and normally closed solenoid valve remained unchanged.
Load controller is equipped with by the Css-280 electo hydraulic servocontrolled fatigue testing machine, output voltage-5V～5V; Temperature controller is design voluntarily, and matches with the SPG-30B high-frequency induction furnace, input voltage-5V～5V, output double switch signal.
(4) cooling of instrument and equipment
In order to guarantee the normal operation of instrument and equipment in the thermal mechanical fatigue process of the test, need cool off instrument and equipment.Chilled water is provided by the water-cooled subsystem, in order to save water resource, adopts the recirculated water cooling.
The water-cooled subsystem is made up of water pump and water storage tank, and is as shown in Figure 2.Be divided into two parts after the chilled water process water pump supercharging in the water storage tank: a part gets into high-frequency induction furnace, is used to cool off high-frequency induction furnace and load coil; 2. the water-cooled hole of another part entering blade built-up jig 9 is used for cooled blade built-up jig 9.Two parts chilled water is got back to water storage tank after accomplishing the cooling to instrument and equipment, constitutes the chilled water circulation.When the water temperature of water storage tank reaches 40 ℃, need to change chilled water.
Water storage tank capacity 1.0m
3Model of pump 1WZB-25-0.37, flow 1.8m
3/ h.
Claims (4)
1. hollow cooled turbine blade thermal mechanical fatigue pilot system is characterized in that: it comprises and loads subsystem, the subsystem of heating, air cooling subsystem, water-cooled subsystem and RACS; Load subsystem in the vertical direction clamping turbo blade; The subsystem of heating is placed horizontally at and loads the subsystem middle part, and turbo blade is heated; Air cooling subsystem horizontal positioned links to each other with the loading subsystem through pipeline; Water-cooled subsystem horizontal positioned links to each other with the subsystem of heating with the loading subsystem through pipeline; RACS is positioned over the subsystem top of heating, and links to each other with loading subsystem, the gentle hail of the subsystem of heating system through cable; It is used for the simulation of hollow cooled turbine blade examination working stress field, cross section, temperature field and loading spectrum;
Said loading subsystem is made up of fatigue tester and turbo blade unit clamp, behind the turbo blade unit clamp clamping turbo blade, is placed on the chuck of fatigue tester again; It is used to provide the thermal mechanical fatigue test required mechanical load; Fatigue tester provides the tensile load of single shaft; The turbo blade unit clamp is Design and Machining voluntarily, and the turbo blade unit clamp is by last fork block, fork block, pin, fork, the approximate part of the turbine disk, baffle plate, screw, hold-down bolt, blade built-up jig and pad constitute down; Wherein, upper and lower fork block is the step shaft-like part, is individually fixed in the upper and lower chuck of fatigue tester; Fork (11), (3) are connected with upper and lower fork block through pin (12), (2); Fork (11) is connected with blade built-up jig (9) through pin (10); Baffle plate is connected through the approximate part of the screw (7) and the turbine disk; The approximate part of the turbine disk is fixed on the fork (3) through pin hole and the pin (4) that is provided with on it; This fork is provided with the Y shape part of through hole for it; The approximate part of this turbine disk is its T profiles that is provided with through hole, blind hole and tongue-and-groove; This baffle plate is its rectangular slab materials and parts that are provided with through hole; This blade built-up jig is branch half formula step rectangle sheet construction, and is respectively arranged with endoporus, water-cooled hole and vent port: its endoporus matches with the integral shroud of workpiece for measurement turbo blade, is used to transmit mechanical load; Its water-cooled hole links to each other with the water-cooled subsystem, is used for the cooled blade built-up jig; Its vent port is used to discharge the inside cooling draught of turbo blade; 4 hold-down bolts (8) are fixed together two parts of blade built-up jig, for the ease of the reliable delivery of mechanical load, for not with the turbo blade of integral shroud, need be at the blade tip position of turbo blade through casting or weld special-shaped integral shroud; The tenon of turbo blade matches with the tongue-and-groove of the approximate part of the turbine disk, is used to simulate the mounting condition of turbo blade on the turbine disk; The approximate part of the turbine disk has the air cooling passage, links to each other with the air cooling subsystem; Cooling draught enters into the inner chamber of turbo blade through the air cooling passage, carries out the inside cooling of turbo blade; 2 baffle plates prevent to skid off when turbo blade from bearing mechanical load the leakage of tongue-and-groove and cooling draught through the both sides of 4 screw retention at the approximate part tongue-and-groove of the turbine disk; 4 pins connect fork block (1) and fork (3), fork (3) and the approximate part (5) of the turbine disk, blade built-up jig (9) and fork (11), fork (11) and last fork block (13) down respectively; Be reserved with the gap between two parts that each pin connects and insert 10 pads just; The assembly that is connected by pin is called the joint; This turbine unit clamp has 4 joints; Promptly change the number of the left and right sides, gap pad through the combination that changes each joint pad; The angle of adjustment turbo blade and fatigue tester main shaft, the eccentric tension of realization turbo blade decomposes the turbo blade of sening as an envoy to the tensile load of single shaft and produces component crooked, torsional deflection; In conjunction with said method, adjust the tensile load of fatigue tester simultaneously, can realize the simulation of turbo blade examination working stress field, cross section;
The said subsystem of heating is made up of high-frequency induction furnace and load coil, connects mutually therebetween; It is used to provide the thermal mechanical fatigue test required thermal force; Load coil is a self design, adopts two-tube branch half formula structure, and it is made up of 2 copper pipes, connecting copper piece and plastic water pipes, the two ends of plastic water pipe respectively with an end socket of 2 copper pipes, connect copper sheet 2 copper pipes be fixed together; 2 copper pipes be connected copper sheet and constitute current return; 2 copper pipes and plastic water pipe constitute the chilled(cooling) water return (CWR); Load coil links to each other with high-frequency induction furnace, and copper pipe inside is connected with chilled water; Through the shape of change load coil and the distance of load coil and turbine blade surface, cause different magnetic leakages in different zones, produce required thermograde at turbine blade surface; In conjunction with said method, adjust the power input of high-frequency induction furnace simultaneously, can realize the simulation of turbo blade examination working temperature field, cross section;
Said air cooling subsystem is made up of air compressor, decompression venting valve, air mass flow amount controller and three-way connection, connects mutually through pipeline therebetween; It is used to provide the thermal mechanical fatigue test required cooling draught; Air compressor provides continuously but pressure, all unsettled air-flow of flow; Behind decompression venting valve, it is constant that air-flow pressure keeps; Behind the air mass flow amount controller, it is constant that air flow rate keeps; Exit at the air mass flow amount controller is equipped with three-way connection, and an outlet of three-way connection links to each other with the air cooling passage of the approximate part of the turbine disk, is used to simulate the inside cooling of turbo blade; Another outlet is equipped with normally closed solenoid valve, and by RACS control, is used to simulate the external forced cooling of turbo blade;
Said water-cooled subsystem is made up of water pump and water storage tank, connects mutually through pipeline therebetween; It is used for the cooling of thermal mechanical fatigue process of the test instrument and equipment; Be divided into two parts after the chilled water process water pump supercharging in the water storage tank: a part gets into high-frequency induction furnace, is used to cool off high-frequency induction furnace and load coil; Another part gets into the water-cooled hole of blade built-up jig, is used for the cooled blade built-up jig; Two parts chilled water is got back to water storage tank after accomplishing the cooling to instrument and equipment, constitutes the chilled water circulation;
Said RACS is made up of load controller, temperature controller and normally closed solenoid valve, connects mutually through cable therebetween; It is used for the synchro control of each subsystem of thermal mechanical fatigue test; Load controller is equipped with by fatigue tester, input mechanical load waveform, output mechanical load voltage signal; The mechanical load voltage signal divides two-way: the one tunnel is input to fatigue tester, and the turbo blade unit clamp is loaded; Another road is input to temperature controller; Temperature controller is design voluntarily, and matches with high-frequency induction furnace, input mechanical load voltage signal, and according to the increase of mechanical load voltage signal/reduce, the ON/OFF signal of output high-frequency induction furnace and the pass of normally closed solenoid valve/open signal.
2. a kind of hollow cooled turbine blade thermal mechanical fatigue pilot system according to claim 1, it is characterized in that: the material of this turbo blade unit clamp is a heat-resisting alloy mould steel, the surface processing of turning blue.
3. a kind of hollow cooled turbine blade thermal mechanical fatigue pilot system according to claim 1, it is characterized in that: the quantity of turbo blade unit clamp Intermediate gasket is 40.
4. a kind of hollow cooled turbine blade thermal mechanical fatigue pilot system according to claim 1, it is characterized in that: the quantity of endoporus, water-cooled hole and vent port is respectively one, one and two in this blade built-up jig.
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