CN116659871A - A transition section structure of an aeroengine turbine blade for cold and heat fatigue tests - Google Patents

Abstract

An aeroengine turbine blade cold and heat fatigue test transfer section structure, along the direction from the air intake to the air outlet, including four sections of pipe body components connected in sequence, the transition section, the stability section, the test section, and the exhaust section, each section of pipe The body assembly includes an inlet flange, an exhaust flange, an outer water jacket and an inner water jacket; ring bosses are respectively arranged on the opposite end faces of the inlet flange and the exhaust flange, and the ring bosses The platform is set along the circumference of the ventilation hole of the inlet flange and the exhaust flange; the two ends of the inner water jacket are respectively butt welded with the annular bosses of the inlet flange and the exhaust flange Form the weld. The annular boss not only plays the role of welding, but also makes the outer peripheral surface of the formed weld be located in the cooling water flow channel formed by the outer water jacket and the inner water jacket. When the cooling water in the cooling water flow channel flows, it can act on the weld seam To the cooling effect, avoid weld cracks, improve the temperature resistance of the pipe body components and the number of cycles.

Description

An aeroengine turbine blade transition section structure for cold and heat fatigue tests

technical field

The invention relates to the test technology of aero-engine components, in particular to a structure of an adapter section for aero-engine turbine blade cold and heat fatigue tests.

Background technique

As the thrust-to-weight ratio of aero-engines continues to increase and the temperature in front of the turbine continues to increase, more stringent requirements are placed on the high-temperature performance of turbine blades. When the engine is in service, the turbine blades not only bear a large aerodynamic load, but also need to withstand the continuous impact of high-temperature gas in the combustion chamber. Compared with the mechanical vibration load, the coupling effect of temperature and aerodynamic load is the main load form that the turbine blade bears during its service. When the engine starts and stops, the temperature level of the inner and outer surfaces of the blade changes sharply, forming a large temperature gradient in the thickness direction of the blade. As a result, the blade generates a large amount of heat exchange in a short period of time, thereby forming a large thermal stress inside and outside the blade, which has a serious impact on the high-temperature performance and life of the blade. In order to investigate the thermal fatigue resistance of turbine blades, a thermal fatigue test of turbine blades is required.

The principle of the thermal fatigue test of the turbine blade is to use a certain cyclic load and time history to simulate the temperature alternating load of the turbine blade during the engine start-work-stop process, and use the heating system to apply the gas temperature load. Compressed air passes through the main gas pipeline and is heated by the heating system to the temperature required for the test, and then enters the test transfer section. The main function of the test transfer section is to transfer the high-temperature gas generated by the heating system to meet the test requirements. The shape and size of the flow channel provide installation space for the gas parameter measurement device, clamp and contain the test piece, and ensure the inlet and outlet angles of the test blades.

Figure 1 is a schematic diagram of the overall structure of the transition section of the existing turbine blade thermal fatigue test. The entire test transition section is divided into four parts, namely the transition section, the stability section, the test section and the exhaust section. During the test, after leaving the combustion chamber, the high-temperature gas passes through the transition section, the stabilization section, the test section and the exhaust section in turn, and finally is discharged into the atmosphere, and the sections are connected by flanges. In order to ensure the normal operation of each section, cooling water is passed through each section, and the cooling water cools the inner runner in a straight-through manner. However, in the overall structure of the transition section of the existing turbine blade thermal fatigue test, the water jacket and the flange in each section are connected by lap welding (as shown at A in Figure 2), and the cooling The water failed to effectively cool the weld. During the heat and cold fatigue test of the turbine blade, the existing test transition section was at high temperature. Cracks will appear at the weld seam where the sleeve and the flange are lap welded, making it impossible to continue the test. Therefore, the existing test adapter section has problems such as low temperature resistance and few available test cycles.

Contents of the invention

The main purpose of the present invention is to propose an aeroengine turbine blade thermal fatigue test transfer section structure, aiming to solve the problem that the existing test transfer section cannot be cooled at the welding seam, cracks are prone to occur, and the existing test transfer section has The problem of low temperature resistance and few available test cycles.

In order to achieve the above object, the present invention proposes a transition section structure for the thermal fatigue test of the turbine blade of an aero-engine, along the direction from the air intake to the air outlet, including the transition section, the stability section, the test section, and the four sections of the exhaust section connected in sequence. Sectional pipe body assembly, each section of pipe body assembly includes an inlet flange, an exhaust flange, an outer water jacket and an inner water jacket; An annular boss, and the annular boss is arranged along the circumference of the ventilation hole of the inlet flange and the exhaust flange; the two ends of the inner water jacket are respectively connected to the inlet flange and the exhaust flange The annular boss of the flange is butt welded to form a weld; the air passage hole and the middle through hole of the inner water jacket form a gas flow channel; The flange and the exhaust side are connected by flange; the inner wall of the outer water jacket and the outer wall of the inner water jacket are separated to form a cooling water flow channel, and the peripheral surface of the weld is located on the cooling water flow channel; a water inlet port is provided on the outer water jacket pipe and water outlet pipe, and connected to the cooling water channel.

Preferably, a first water storage groove is provided at one end of the outer water jacket, and a second water storage groove is provided at the other end; and both the first water storage groove and the second water storage groove are located near the welding seam.

Preferably, the first water storage groove is set at one end of the flange near the exhaust side, and the water inlet pipe is connected to the first water storage groove; the second water storage groove is set at the end close to the air intake side. At one end of the flange, the water outlet pipe is connected to the second water storage groove; the direction of the water flow in the cooling water flow channel is opposite to the direction of the air flow in the gas flow channel.

Preferably, both the water inlet pipe and the water outlet pipe are arranged obliquely, the water outlet end of the water inlet pipe faces, and the water inlet end of the water outlet pipe faces the weld seam.

Preferably, the included angle between the central axis of the water inlet pipe, the water outlet pipe and the central axis of the inner water jacket is 45 degrees.

Preferably, the radial depth h of the first water storage groove and the second water storage groove is greater than or equal to 10 mm.

Preferably, an annular groove is provided on the outer side of the annular boss on the inlet flange and the exhaust flange, and an annular clip edge is provided on the end face of the outer water jacket, and the annular clip edge is snapped on the edge of the annular groove. on the side wall.

Preferably, external threads are provided on the outer peripheral surface of the water inlet end of the water inlet interface pipe, and external threads are provided on the outer peripheral surface of the water outlet end of the water outlet interface pipe.

Preferably, limit stoppers are respectively provided on the water inlet interface pipe and the water outlet interface pipe, and a sealing gasket is provided on the end surface of the limit stopper close to the external thread.

Preferably, the wall thickness of the annular boss is consistent with the wall thickness of the inner water jacket.

Owing to adopting above-mentioned technical scheme, the beneficial effect of the present invention is as follows:

(1) In the present invention, an annular boss is respectively provided on the opposite end faces of the inlet flange and the exhaust flange, and the end face of the annular boss is used for butt welding with the end face of the inner water jacket To form a weld, the annular boss not only plays the role of welding, but also makes the outer peripheral surface of the formed weld be located in the cooling water flow channel formed by the outer water jacket and the inner water jacket. When the cooling water in the cooling water flow channel flows, it can It plays a role in cooling the weld. During the test, because the welds at both ends of the inner water jacket in each section of the pipe body assembly have been effectively cooled, it can effectively avoid the lap welding of the inner water jacket and the flange during the test. Cracks will appear at the joints, which improves the temperature resistance of the pipe body components and the number of cycles.

(2) In the present invention, the heat exchange efficiency at the weld seam is improved, the temperature at the weld seam is further reduced, and the cooling effect is improved by providing a water storage groove structure at both ends of the outer water jacket near the weld seam.

(3) In the present invention, the direction of the water flow in the cooling water channel is opposite to the direction of the air flow in the gas channel, which can further enhance the cooling effect.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention. For those skilled in the art, other drawings can also be obtained according to the structures shown in these drawings without creative effort.

Figure 1 is a schematic diagram of the overall structure of the transition section of the existing turbine blade thermal fatigue test;

Fig. 2 is the structural representation of lap welding of inner water jacket and flange in the existing structure;

Fig. 3 is the structural representation of each section pipe body assembly among the present invention;

FIG. 4 is a method diagram at B in FIG. 3 .

Description of reference numerals: 1. Transition section; 2. Stability section; 3. Test section; 4. Exhaust section; 9. Exhaust edge flange; 10. Water inlet pipe; 11. Annular boss; 12. Ventilation hole; 13. Weld seam; 14. First water storage groove; 15. Second water storage groove Groove; 16, annular groove; 17, annular card edge; 18, limit block; 19, gasket.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relationship between the components in a certain posture (as shown in the accompanying drawings). Relative positional relationship, movement conditions, etc., if the specific posture changes, the directional indication will also change accordingly.

In addition, the descriptions involving "first", "second" and so on in the present invention are only for descriptive purposes, and should not be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined as "first" and "second" may explicitly or implicitly include at least one of these features. In addition, the technical solutions of the various embodiments can be combined with each other, but it must be based on the realization of those skilled in the art. When the combination of technical solutions is contradictory or cannot be realized, it should be considered that the combination of technical solutions does not exist , nor within the scope of protection required by the present invention.

As shown in Fig. 1 and Fig. 3, an aeroengine turbine blade cooling and heat fatigue test transition section structure provided by the present invention includes a transition section 1, a stabilizing section 2, and a test Section 3 and the four-section pipe body assembly of exhaust section 4. During the experiment, the gas flow enters from transition section 1 and finally discharges from exhaust section 4. Each section of pipe body assembly includes inlet flange 5, exhaust Side flange 9, outer water jacket 7 and inner water jacket 8; ring-shaped bosses 11 are respectively arranged on the opposite end faces of the inlet side flange 5 and the exhaust side flange 9, and the ring-shaped bosses 11 are arranged along the The peripheral configuration of the ventilation holes 12 of the gas side flange 5 and the exhaust side flange 9; 11 butt welding to form a weld 13; the ventilation hole 12 and the middle through hole of the inner water jacket 8 jointly form a gas flow channel; the outer water jacket 7 is set outside the inner water jacket 8, and the two ends are respectively connected to the air inlet Flange 5 and exhaust flange 9 are connected; the inner wall surface of the outer water jacket 7 and the outer wall surface of the inner water jacket 8 are spaced apart to form a cooling water flow channel, and the peripheral surface of the weld 13 is located on the cooling water flow channel; in the outer water jacket 7 is provided with a water inlet interface pipe 10 and a water outlet interface pipe 6, which are connected to the cooling water flow channel. Annular bosses 11 are respectively provided on the opposite end faces of the intake flange 5 and the exhaust flange 9, and the end faces of the annular bosses 11 and the end faces of the inner water jacket 8 are butt welded to form weld seams. 13. The annular boss 11 not only plays the role of welding, but also makes the outer peripheral surface of the weld 13 formed in the cooling water channel formed by the outer water jacket 7 and the inner water jacket 8. When the cooling water in the cooling water channel flows , can play a role in cooling the weld 13. In the test process, since the welds at both ends of the inner water jacket 8 in each section of the pipe body assembly have been effectively cooled, it can effectively avoid the inner water jacket and the flange during the test. Cracks will appear at the welding seam 13, which improves the temperature resistance and cycle times of the pipe body assembly. In addition, the use of butt welding can ensure that the direction of thermal deformation is consistent.

As shown in Figure 3, one end of the outer water jacket 7 is provided with a first water storage groove 14, and the other end is provided with a second water storage groove 15; and the first water storage groove 14, the second water storage groove 15 They are all located near the weld seam 13. The two ends of the outer water jacket 7 are provided with a water storage groove structure near the weld 11, which improves the heat exchange efficiency at the weld 11, further reduces the temperature at the weld 11, and improves the cooling effect.

As shown in Figure 1, the first water storage groove 14 is arranged at one end close to the exhaust flange 9, and the water inlet pipe 10 is connected to the first water storage groove 14; the second water storage groove The groove 15 is arranged at one end close to the flange 5 of the air inlet side, and the water outlet pipe 6 is connected to the second water storage groove 15; through the aforementioned structure, the direction of the water flow in the cooling water flow channel is opposite to the direction of the air flow in the gas flow channel, further To enhance the cooling effect.

As shown in FIG. 3 , the water inlet pipe 10 and the water outlet pipe 6 are arranged obliquely. Specifically, the included angle between the central axis of the water inlet pipe 10 , the water outlet pipe 6 and the central axis of the inner water jacket 8 is 45 degrees. By adjusting the inflow and outflow angles of the cooling water, the position of the weld 11 can be fully cooled, the working temperature of the weld is reduced, and the deformation is reduced, which further solves the problem of low temperature resistance of the existing test transition section.

As shown in FIG. 4 , in order to ensure the water storage capacity in the water storage grooves and ensure the cooling effect, the radial depth h of the first water storage groove 14 and the second water storage groove 15 is ≥ 10mm.

As shown in Fig. 4, an annular groove 16 is provided on the outer side of the annular boss 11 on the inlet flange 5 and the exhaust flange 9, and an annular clip edge 17 is arranged on the end face of the outer water jacket 7. The clamping edge 17 is clamped on the side wall of the annular groove 16 . The clamping structure formed by the annular clamp edge 17 and the annular groove 16 facilitates the installation of the outer water jacket 7, and at the same time, under the condition of hydraulic pressure in the cooling water channel, the outer wall of the annular clamp edge 17 can be closely attached to the ring groove 16. The side wall plays a sealing effect, forming a self-sealing structure.

As shown in FIG. 3 , external threads are provided on the outer peripheral surface of the water inlet end of the water inlet interface pipe 10 , and external threads are provided on the outer peripheral surface of the water outlet end of the water outlet interface pipe 6 . External threads are provided to facilitate the connection of cooling water pipelines. Further, limit stoppers 18 are respectively provided on the water inlet interface pipe 10 and the water outlet interface pipe 6 , and a sealing gasket 19 is provided on the end surface of the limit stopper 18 close to the external thread. A limit block 18 is provided to limit the connection position of the cooling water pipeline. When the cooling water pipeline is screwed on the external thread, the end surface of the cooling water pipeline abuts against the gasket 19 to form a sealing structure.

As shown in FIG. 3 , the wall thickness of the annular boss 11 is consistent with the wall thickness of the inner water jacket 8 . The uniform wall thickness structure can well avoid the formation of a smooth transition between the cooling water flow channel and the gas flow channel at the docking position, and improve the smoothness of the gas flow and the smoothness of the cooling water flow.

Through test comparison, the maximum gas temperature that the test transition section of the existing structure can withstand is 1000°C, and at the highest temperature, after about 200 cycles of cooling and heating, cracks will appear in the weld seam of the test transition section, making The test cannot continue. However, using the adapter section structure provided by the present invention, a certain type of engine low-pressure turbine guide vane thermal fatigue test was carried out. During the test, the maximum temperature of the gas was 1200°C, and the test adapter section was subjected to a total of 2,400 test cycles. The problem of cracks in the weld seam of the test transition section occurred, which saved the test cycle and test cost. On the test surface, the invention optimizes the cooling water flow path and the position of the weld, adjusts the inflow and outflow angle of the cooling water, so that the weld position can be fully cooled, the working temperature of the weld is reduced, and the deformation is reduced, which solves the problem of the resistance of the existing test transition section. The problem of low temperature capacity.

The above is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. Under the inventive concept of the present invention, the equivalent structural transformation made by using the description of the present invention and the contents of the accompanying drawings, or direct/indirect Application in other related technical fields is included in the patent protection scope of the present invention.

Claims (10)

1. An aeroengine turbine blade cold and heat fatigue test transfer section structure, along the air intake to the air outlet direction, including a transition section (1), a stabilization section (2), a test section (3), and an exhaust The four-section pipe body assembly of section (4), characterized in that: Each pipe body assembly includes inlet flange (5), exhaust flange (9), outer water jacket (7) and inner water jacket (8); The opposite end faces of the side flanges (9) are respectively provided with annular bosses (11), and the annular bosses (11) are arranged along the air passages of the inlet side flange (5) and the exhaust side flange (9). The circumferential setting of the hole (12); the two ends of the inner water jacket (8) are butt-welded with the annular bosses (11) of the inlet side flange (5) and the exhaust side flange (9) respectively to form a welded joint. slit (13); the air passage hole (12) and the middle through hole of the inner water jacket (8) jointly form a gas flow channel; the outer water jacket (7) is sleeved outside the inner water jacket (8), and both ends They are respectively connected with the inlet side flange (5) and the exhaust side flange (9); the inner wall surface of the outer water jacket (7) and the outer wall surface of the inner water jacket (8) are arranged at intervals to form a cooling water flow channel, welded The peripheral surface of the slit (13) is located on the cooling water flow channel; the outer water jacket (7) is provided with a water inlet interface pipe (10) and a water outlet interface pipe (6), which are connected to the cooling water flow channel. 2. The aeroengine turbine blade cold and heat fatigue test adapter section structure as claimed in claim 1, characterized in that: a first water storage groove (14) is provided at one end of the outer water jacket (7), and a first water storage groove (14) is provided at the other end. The second water storage groove (15); and the first water storage groove (14) and the second water storage groove (15) are both located near the weld (13). 3. The aeroengine turbine blade thermal fatigue test transfer section structure according to claim 2, characterized in that: the first water storage groove (14) is arranged at one end close to the exhaust edge flange (9) , the water inlet interface pipe (10) is connected on the first water storage groove (14); the second water storage groove (15) is arranged at one end near the inlet edge flange (5), and the water outlet interface pipe ( 6) Connected to the second water storage groove (15); the direction of the water flow in the cooling water flow channel is opposite to the direction of the air flow in the gas flow channel. 4. The adapter section structure of the turbine blade of an aero-engine as claimed in claim 3, characterized in that: the water inlet interface pipe (10) and the water outlet interface pipe (6) are all inclined settings, and the water inlet interface The water outlet end of the pipe (10) and the water inlet end of the water outlet interface pipe (6) are all towards the weld seam (13). 5. aero-engine turbine blade cooling and heat fatigue test transition section structure as claimed in claim 4, is characterized in that: the central axis of described water inlet mouthpiece (10), water outlet mouthpiece (6) and inner water jacket ( 8) The angle between the central axes is 45 degrees. 6. The aeroengine turbine blade cold and heat fatigue test adapter section structure as claimed in claim 2, characterized in that: the radial direction of the first water storage groove (14) and the second water storage groove (15) Depth h≥10mm. 7. The adapter section structure of the turbine blade of an aero-engine as claimed in claim 1, characterized in that: on the intake side flange (5) and the exhaust side flange (9), the annular boss ( 11) An annular groove (16) is provided on the outer side, and an annular clip edge (17) is provided on the end face of the outer water jacket (7), and the annular clip edge (17) is clipped on the side wall of the annular groove (16) . 8. The aeroengine turbine blade cooling and heat fatigue test adapter section structure as claimed in claim 1, characterized in that: an external thread is arranged on the outer peripheral surface of the water inlet end of the water inlet interface pipe (10), and an external thread is arranged on the water outlet interface pipe (10). (6) The outer peripheral surface of the water outlet is provided with external threads. 9. The structure of the transition section for the thermal fatigue test of the turbine blade of the aero-engine as claimed in claim 9, characterized in that: limit stops are respectively arranged on the water inlet interface pipe (10) and the water outlet interface pipe (6) (18), a gasket (19) is arranged on the end face of the limit block (18) close to the external thread. 10. The aeroengine turbine blade thermal fatigue test adapter section structure according to claim 1, characterized in that: the wall thickness of the annular boss (11) is consistent with the wall thickness of the inner water jacket (8).