A transition section structure for turbine first-stage blade cold efficiency test

Abstract

The present application relates to the technical field of gas turbine, and particularly discloses a transition section structure for turbine first-stage blade cold efficiency test, which comprises a straight section, a deflection section, a deflection section air inlet end support assembly, a support frame assembly, a hoisting assembly and elastic sealing sheets; the straight section is divided into inner and outer walls, and both are welded on a cascade test section cover plate; the inner and outer walls are connected by a plurality of support frames at the air inlet end; the deflection section is also divided into inner and outer walls, and the inner and outer walls are connected by a plurality of support frames at both ends, wherein the plurality of support frames at the air inlet end are provided with positioning pins for connecting the inner and outer walls; the transition section guides the airflow to smoothly transition from the combustion chamber outlet to the cascade test section inlet in the limited space of a test cabin, so as to provide a specific inlet airflow angle for the test blade; the transition section is divided into two sections, the straight section is welded on the cascade test section, and both ends of the deflection section of the transition section are supported, so that the torsional deformation of the deflection section of the transition section is effectively reduced, the thermal stress is reduced, and the service life of the transition section is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbine technology, in particular to a transition section structure for turbine first-stage blade cold efficiency test. BACKGROUND

[0002] In order to master the cold efficiency characteristics of the first-stage blade of the turbine, the cascade cold efficiency test bench is widely used at home and abroad to carry out comprehensive cold efficiency characteristic test of the blade under static condition. In order to promote the rapid development of gas turbine in China, the Institute of Engineering Thermophysics, Chinese Academy of Sciences undertakes to build a high-efficiency low-carbon gas turbine test device, in which the TB01A station is mainly used to carry out cascade cold efficiency test under high-temperature and high-pressure conditions (such as H / J, F grade), an experimental system of combustion chamber-turbine coupling working characteristics is established, and the effectiveness and reliability of the internal cooling structure, coating and material of the blade are verified.

[0003] The main structure of the cascade cold efficiency test includes: upstream section (heater, transition section, front measurement section), cascade test section, downstream section (rear measurement section and exhaust section), etc. The upstream section of the existing blade cold efficiency test bench generally adopts a straight section structure. In order to make the test cabin applicable to more types and higher parameters of cascade test, the TB01A test cabin is divided into front and rear sections, the rear cabin is arranged with an exhaust section and a cooling spray structure, and the front cabin is arranged with a heater outside. In order to meet the real flue gas conditions of the turbine blade, the combustion chamber is used to heat the inlet air of the cascade, the main gas is passed through the front cabin, and the cascade test section is arranged between the two cabins. In the existing similar design, the installation angle of the blade casing of the test cabin is adjusted to maintain the straight upstream section structure, and the inlet gas flow angle is simulated, but the TB01A test cabin needs to be greatly changed, and the reconstruction time and cost are high. In order to meet the arrangement requirements of the combustion chamber, the cascade test section and the exhaust section on the test cabin, a compact curved transition section structure is designed, which can convert the axial exhaust of the combustion chamber into tangential exhaust with circumferential speed in the limited space of the front cabin, and provide appropriate inlet gas flow angle for the cascade test piece. The working medium in the transition section has been fully combusted and has not been expanded to do work, and due to the different relative positions of the combustion chamber outlet and the cascade test section inlet and the certain requirement of the blade cold efficiency test piece for the inlet gas flow angle, the transition section will simultaneously bear high-temperature deformation and high-speed airflow deflection caused torsional deformation, which causes large deformation and stress of the transition section and reduces the service life. How to effectively reduce the torsional deformation of the transition section is the key to further improve the service life of the transition section for turbine first-stage blade cold efficiency test. Therefore, a transition section structure for turbine first-stage blade cold efficiency test is provided. SUMMARY

[0004] The purpose of the present application is to provide a transition section structure for turbine first-stage blade cold efficiency test to solve the problems in the background art.

[0005] In order to achieve the above object, the present application provides the following technical scheme: a transition section structure for turbine first-stage blade cold efficiency test, comprising a transition section, the transition section comprising a deflection section, a support frame assembly, a lifting assembly and an elastic sealing sheet connecting the inner walls of the two sections, a straight section and a support assembly at the gas inlet end of the deflection section;

[0006] The support frame assembly is composed of a first deflection section gas inlet end support frame, a positioning pin locking washer I, a gas inlet end inner and outer wall positioning pin, a second deflection section gas inlet end support frame, a deflection section gas outlet end support frame and a straight section support frame.

[0007] The deflection section gas inlet end support assembly is composed of a ring, a bracket, a ring nut, a ring locking washer, an outer wall positioning pin and a positioning pin locking washer II.

[0008] The straight section comprises a straight section outer wall and a straight section inner wall, the straight section outer wall and the straight section inner wall are connected by a straight section support frame at the gas inlet end of the straight section, and the straight section outer wall and the straight section inner wall are both welded to the cascade test section cover plate at the gas outlet end of the straight section.

[0009] The deflection section comprises a deflection section outer wall and a deflection section inner wall, a plurality of first deflection section gas inlet end support frames and second deflection section gas inlet end support frames are evenly distributed between the deflection section outer wall and the deflection section inner wall at the gas inlet end of the deflection section, the deflection section outer wall and the deflection section inner wall are connected by the first deflection section gas inlet end support frames and the second deflection section gas inlet end support frames at the gas inlet end of the deflection section, the second deflection section gas inlet end support frame is welded with a gas inlet end inner and outer wall positioning pin, the outer wall of the gas inlet end of the deflection section falls on the bracket, the bracket is provided with an outer wall positioning pin connected with the deflection section outer wall, the bracket is provided with a ring surrounding the deflection section outer wall, and the deflection section inner and outer walls are connected by the deflection section gas outlet end support frame at the gas outlet end of the deflection section.

[0010] The deflection section inner wall is welded with an elastic sealing sheet, the elastic sealing sheet is inserted into the straight section inner wall, the deflection section outer wall and the straight section outer wall have an axial gap δ5, two L-shaped insertion plates are welded on the outer wall of the transition section and are inserted into each other, an axial gap δ6 and a radial gap δ7 are reserved between the two L-shaped insertion plates, and a multi-stage sealing is formed.

[0011] The lifting assembly comprises a rotating pin shaft, a lifting bracket, a lifting lug, a lifting lug locking washer and a lifting lug nut.

[0012] The lifting lug and the lifting bracket are assembled together by the rotating pin shaft, the lifting lug locking washer and the lifting lug nut to form the lifting assembly, and the lifting assembly is spot-welded on the deflection section gas outlet end of the deflection section outer wall.

[0013] Several air film pores are provided at points a, b, and f on the risk stress zone of the inner wall of the deflection section and the inner wall of the straight section to reduce the temperature and stress in the risk zone. A ring of air film pores is provided at point e on the side of the weld seam connecting the inner wall of the straight section and the cover plate of the blade cascade test section to reduce the temperature gradient of the connecting weld seam and reduce thermal stress. Circular crack-stopping holes are provided at points g at the four corners of the probe mounting holes on the inner wall of the straight section to prevent cracking at the four corners of the probe mounting holes.

[0014] As a preferred embodiment of the present invention, the outer wall of the deflection section is welded to the elastic sealing sheet at the air inlet of the transition section, the elastic sealing sheet at the air inlet of the transition section is inserted into the flow guide bushing of the combustion chamber, the flame tube is welded to the elastic sealing sheet at the tail end of the flame tube, and the elastic sealing sheet at the tail end of the flame tube is inserted into the inner wall of the deflection section; the air inlet support assembly of the deflection section is bolted to the test chamber, and a moving blade test piece is provided at one end of the straight section.

[0015] As a preferred embodiment of the present invention, the straight section support frame is welded to the inner wall of the straight section and has sliding friction contact with the inner wall of the straight section; the deflection section exhaust end support frame is welded to the inner wall of the deflection section and has sliding friction contact with the inner wall of the deflection section.

[0016] In a preferred embodiment of the present invention, the first deflection section air intake end support frame is welded to the inner wall of the deflection section and has sliding friction contact with the outer wall of the deflection section; a pad with a threaded hole is welded inside the trapezoidal upper bottom edge of the second deflection section air intake end support frame, and a positioning pin locking washer I is provided between the positioning pins of the inner and outer walls of the air intake end and the pad; the positioning pins of the inner and outer walls of the deflection section air intake end are connected to the pad by threads, and the positioning pins of the inner and outer walls of the deflection section air intake end extend into the positioning holes of the outer wall of the deflection section, with axial and radial deformation gaps reserved. To prevent excessive torsion of the inner wall of the deflection section while allowing axial and radial deformation of the inner wall, thus reducing thermal stress on the inner wall of the deflection section; the axial clearance between the inner and outer wall positioning pins of the intake end and the positioning hole of the outer wall of the deflection section is δ1, and satisfies 2.8mm≤δ1≤3.2mm; the axial clearance between the inner and outer wall positioning pins of the intake end and the positioning hole of the outer wall of the deflection section is δ2, and satisfies 0.3mm≤δ2≤1mm; the radial clearance between the inner and outer wall positioning pins of the intake end and the positioning hole of the outer wall of the deflection section is δ... r And satisfy 0.3mm≤δ r ≤1mm, δ1 size meets the requirement of contact between the positioning pins on the inner and outer walls of the intake end and the positioning holes on the outer wall of the deflection section after maximum thermal deformation, δ2, δ r The size meets the limiting requirements of the positioning holes on the outer wall of the deflection section for the positioning pins on the inner and outer walls of the air inlet after thermal deformation, and is used to prevent excessive torsional deformation of the inner wall of the deflection section.

[0017] As a preferred technical scheme of the present application, the hanger is fixed on the cover plate of the cascade test section by bolts, and the axial direction of the hoisting assembly is the same as the direction of the incoming air of the transition section.

[0018] As a preferred technical scheme of the present application, the outer wall positioning pin and the outer wall of the deflection section are provided with a positioning pin locking gasket II, axial and radial gaps are reserved between the outer wall positioning pin and the positioning hole of the outer wall of the deflection section, the axial gap between the outer wall positioning pin and the side wall of the air inlet end of the positioning hole of the outer wall of the deflection section is δ3, and satisfies 5mm≤δ5≤10mm, the axial gap between the outer wall positioning pin and the side wall of the air exhaust end of the positioning hole of the outer wall of the deflection section is δ4, and satisfies 0.3mm≤δ4≤1mm, the radial gap between the outer wall positioning pin and the side wall of the positioning hole of the outer wall of the deflection section is δ rr , and satisfies 0.3mm≤δ rr ≤1mm, δ4 and δ rr satisfy the limiting requirements of the positioning hole of the outer wall of the deflection section on the outer wall positioning pin after thermal deformation, and are used for preventing excessive deformation of the outer wall of the deflection section; the bracket realizes sliding friction contact with the outer wall of the deflection section through the circular arc groove, and the ring hoop is connected with the bracket through the ring hoop nut and the ring hoop locking gasket.

[0019] As a preferred technical scheme of the present application, the straight section support frame and the deflection section air exhaust end support frame are both trapezoidal structures lacking a bottom side, and the two waists extend in an arc shape to the two sides of the upper bottom side of the trapezoid at the intersection with the bottom side, and the first deflection section air inlet end support frame is also a trapezoidal structure lacking a bottom side, but the two waists extend to the two sides along the inner wall contour line of the deflection section at the junction with the bottom side.

[0020] As a preferred technical scheme of the present application, the axial gap between the middle section of the straight section outer wall and the outer wall of the deflection section is δ5, and satisfies 1.7mm≤δ5≤2.8mm, the axial gap is sealed by two L-shaped insert pieces respectively welded on the straight section outer wall and the outer wall of the deflection section, the axial gap δ6 of the two L-shaped insert pieces is equal to δ5, the radial gap is δ7, and satisfies 3.5mm≤δ7≤4.5mm, δ5, δ6 and δ7 satisfy that the straight section outer wall and the outer wall of the deflection section do not contact after thermal deformation under the premise of ensuring sealing performance.

[0021] Compared with the prior art, the present application has the following beneficial effects:

[0022] (1) The transition section structure for the turbine first-stage blade cold efficiency test provided by the present application realizes smooth transition of the air flow from the combustion chamber outlet to the cascade test section inlet in the limited space of the test cabin through folding and guiding, provides a specific inlet flow angle for the turbine first-stage blade inlet, and saves the modification time and cost;

[0023] (2), the transition section structure for turbine first stage moving blade cold efficiency test provided by the application is divided into a deflection section and a straight section, the straight section provides a specific inlet flow angle for the moving blade cascade, and the subsection can avoid excessive cumulative deformation of the transition section cascade test section end caused by airflow deflection when the transition section is not subsectioned;

[0024] (3), the transition section structure for turbine first stage moving blade cold efficiency test provided by the application sets a support frame in sliding friction contact with the inner wall in the inner and outer walls of the deflection section exhaust end, sets a support frame in sliding friction contact with the outer wall in the inner and outer walls of the deflection section inlet end, and sets a positioning pin, so that the torsional deformation of the inner wall of the deflection section can be effectively transmitted to the support frame and the outer wall of the deflection section, and then the deformation of the outer wall of the deflection section is released through the rotation of the suspended rotating pair and the sliding deformation along the semicircular groove of the bracket, so that the torsional deformation of the transition section can be effectively reduced, the thermal stress can be reduced, and the service life can be prolonged. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 It is a schematic view of the transition section structure;

[0026] Figure 2 It is a schematic view of the support frame (a is the deflection section inlet end support frame (with pin hole), b is the deflection section inlet end support frame, c is the deflection section exhaust end support frame and the straight section support frame);

[0027] Figure 3 It is a schematic view of the gap between the positioning pin and the outer wall of the deflection section and the gap between the outer walls (a is the gap between the inlet end inner and outer walls positioning pin and the outer wall positioning hole, b is the gap between the outer wall positioning pin and the outer wall positioning hole, c is the gap between the outer wall of the deflection section and the outer wall of the straight section);

[0028] Figure 4 It is a schematic view of the support frame distribution (a is the straight section support frame distribution, b is the deflection section exhaust end support frame distribution, and the view direction is the inlet-exhaust direction);

[0029] Figure 5 It is a schematic view of the transition section inner wall connection and gas film hole distribution;

[0030] Figure 6 It is a schematic view of the transition section, combustion chamber and cascade test section arrangement.

[0031] Figure: 100, transition section; 2, elastic sealing sheet at the air inlet end of the transition section; 3, flow guide bushing; 4, combustion chamber casing; 5, elastic sealing sheet at the tail end of the flame tube; 6, flame tube; 7, cover plate of the cascade test section; 8, test vane; 110, deflection section; 111, outer wall of the deflection section; 112, inner wall of the deflection section; 113, air inlet end of the deflection section; 114, air outlet end of the deflection section; 120, support frame assembly; 121, first air inlet end support frame of the deflection section; 122, positioning pin locking washer I; 123, positioning pin of the inner and outer walls at the air inlet end; 124, second air inlet end support frame of the deflection section; 125, air outlet end support frame of the deflection section; 126, straight section support frame; 130, hoisting assembly; 131, rotating pin shaft; 132, hanger; 133, lifting lug; 134, lifting lug locking washer; 135, lifting lug nut; 140, elastic sealing sheet; 150, straight section; 151, outer wall of the straight section; 152, inner wall of the straight section; 153, air inlet end of the straight section; 154, air outlet end of the straight section; 160, air inlet end support assembly of the deflection section; 161, ring; 162, bracket; 163, ring nut; 164, ring locking washer; 165, outer wall positioning pin; 166, positioning pin locking washer II;

[0032] δ1: axial gap between the positioning pin of the inner and outer walls at the air inlet end and the positioning hole of the outer wall of the deflection section at the air inlet end side wall;

[0033] δ2: axial gap between the positioning pin of the inner and outer walls at the air inlet end and the positioning hole of the outer wall of the deflection section at the air outlet end side wall;

[0034] δ r : radial gap between the positioning pin of the inner and outer walls at the air inlet end and the positioning hole of the outer wall of the deflection section;

[0035] δ3: axial gap between the outer wall positioning pin and the positioning hole of the outer wall of the deflection section at the air inlet end side wall;

[0036] δ4: axial gap between the outer wall positioning pin and the positioning hole of the outer wall of the deflection section at the air outlet end side wall;

[0037] δ rr : radial gap between the outer wall positioning pin and the positioning hole of the outer wall of the deflection section;

[0038] δ5: axial gap between the outer wall of the deflection section and the outer wall of the straight section;

[0039] δ6: axial gap of the L-shaped insertion piece of the outer wall;

[0040] δ7: radial gap of the L-shaped insertion piece of the outer wall;

[0041] a: gas film hole I of the inner wall of the deflection section; b: gas film hole II of the inner wall of the deflection section;

[0042] c: lower gas film hole of the hanger of the inner wall of the deflection section; d: lower gas film hole of the support frame of the inner wall of the deflection section;

[0043] e: straight section inner wall weld protection gas film hole; f: straight section inner wall gas film hole;

[0044] g: straight section inner wall crack stop hole; h: straight section inner wall support frame lower gas film hole. DETAILED DESCRIPTION

[0045] The preferred embodiments of the present application are described in detail below with reference to the accompanying drawings, so that the advantages and features of the present application can be more easily understood by those skilled in the art, and the scope of protection of the present application is more clearly defined.

[0046] Embodiment: Please refer to Figure 1 The present application provides a technical solution: a transition section structure for turbine first-stage blade cold efficiency test, comprising a transition section 100, the transition section 100 comprising a deflection section 110, a support frame assembly 120, a hoisting assembly 130 and an elastic sealing sheet 140 connecting the inner walls of the two sections, a straight section 150 and a deflection section inlet end support assembly 160.

[0047] As shown in Figure 1 , the support frame assembly 120 is composed of a first deflection section inlet end support frame 121, a positioning pin locking washer I 122, an inlet end inner and outer wall positioning pin 123, a second deflection section inlet end support frame 124, a deflection section exhaust end support frame 125 and a straight section support frame 126.

[0048] As shown in Figure 1 , the deflection section inlet end support assembly 160 is composed of a ring 161, a bracket 162, a ring nut 163, a ring locking washer 164, an outer wall positioning pin 165 and a positioning pin locking washer II 166.

[0049] As shown in Figure 1 , the straight section 150 comprises a straight section outer wall 151 and a straight section inner wall 152, the straight section outer wall 151 and the straight section inner wall 152 are connected by the straight section support frame 126 at the straight section inlet end 153, and the straight section outer wall 151 and the straight section inner wall 152 are both welded to the cascade test section cover plate 7 at the straight section outlet end 154.

[0050] As shown in Figure 1As shown, the deflection section 110 includes a deflection section outer wall 111 and a deflection section inner wall 112, and a plurality of first deflection section intake end support frames 121 and second deflection section intake end support frames 124 are uniformly distributed between the deflection section outer wall 111 and the deflection section inner wall 112 at the deflection section intake end 113. The deflection section outer wall 111 and the deflection section inner wall 112 are connected at the deflection section intake end 113 by the first deflection section intake end support frames 121 and the second deflection section intake end support frames 124. The second deflection section intake end support frames 124 are welded with intake end inner-outer wall positioning pins 123. The outer wall of the deflection section intake end 113 falls on a bracket 162, which is provided with outer wall positioning pins 165 connected with the deflection section outer wall 111. The bracket 162 is provided with a ring 161 surrounding the deflection section outer wall 111. The deflection section inner-outer wall is connected at the deflection section exhaust end 114 by a deflection section exhaust end support frame 125.

[0051] As shown in Figure 1 The deflection section inner wall 112 is welded with an elastic sealing sheet 140, which is inserted into the flat section inner wall 152. The deflection section outer wall 111 and the flat section outer wall 151 are axially prearranged with a gap δ5. Two L-shaped insertion plates are welded to the outer wall of the transition section 100 and are inserted into each other. An axial gap δ6 and a radial gap δ7 are prearranged between the two L-shaped insertion plates to form a multi-stage sealing.

[0052] As shown in Figure 1 The hoisting assembly 130 includes a rotating pin shaft 131, a hanger 132, an ear 133, an ear locking washer 134, and an ear nut 135.

[0053] The ear 133 and the hanger 132 are assembled together by the rotating pin shaft 131, the ear locking washer 134, and the ear nut 135 to form the hoisting assembly 130, which is spot-welded to the deflection section exhaust end 114 of the deflection section outer wall 111.

[0054] As shown in Figure 5As shown, the a, b, f positions on the risk stress zone of the deflection section inner wall 112 and the straight section inner wall 152 are provided with a plurality of air film holes for reducing the risk zone temperature and stress, the air film holes at the c, d and h positions corresponding to the lug position and the support bracket position of the deflection section inner wall 112 are provided for reducing the adverse effects of the impact holes on the inner wall cooling of the outer wall of the lug 133, the deflection section exhaust end support bracket 125 and the straight section support bracket 126, a ring of air film holes is provided at the e position on one side of the welding seam connecting the straight section inner wall 152 and the cascade test section cover plate 7 for reducing the temperature gradient of the connecting welding seam and reducing the thermal stress, and circular crack arrest holes are provided at the g positions of the four corners of the probe mounting hole of the straight section inner wall 152 for preventing cracking at the four corners of the probe mounting hole; wherein the air film holes at the a position are deflection section inner wall air film holes I; the air film holes at the b position are deflection section inner wall air film holes II; the air film holes at the c position are deflection section inner wall lug lower air film holes; the air film holes at the d position are deflection section inner wall support bracket lower air film holes; the air film holes at the e position are straight section inner wall welding seam protection air film holes; the air film holes at the f position are straight section inner wall air film holes; the holes at the g position are straight section inner wall crack arrest holes; and the air film holes at the h position are straight section inner wall support bracket lower air film holes.

[0055] As shown in Figure 6 , the deflection section outer wall 111 is welded to the transition section inlet end elastic sealing sheet 2, the transition section inlet end elastic sealing sheet 2 is inserted into the flow guide bushing 3 of the combustion chamber, the flame tube 6 is welded to the flame tube tail end elastic sealing sheet 5, and the flame tube tail end elastic sealing sheet 5 is inserted into the deflection section inner wall 112; the deflection section inlet end support assembly 160 is bolted to the test chamber, and one end of the straight section 150 is provided with a blade test piece 8.

[0056] As shown in Figure 1 , the straight section support bracket 126 is welded in the straight section outer wall 151 and is in sliding friction contact with the straight section inner wall 152, thereby supporting the straight section inner and outer walls while not hindering the expansion of the straight section inner wall after heating and reducing the thermal stress of the straight section inner wall. The deflection section exhaust end support bracket 125 is welded in the deflection section outer wall 111, and the deflection section exhaust end support bracket 125 is in sliding friction contact with the deflection section inner wall 112, allowing the deflection section inner wall to achieve a larger axial deformation and reducing the thermal stress; more deflection section exhaust end support brackets are provided on the impact surface of the airflow turning than on other surfaces to absorb and transmit the force of the airflow on the deflection section inner wall.

[0057] As shown in Figure 1 , Figure 2 (a) and Figure 3(a) as shown, the first deflection section inlet end support frame 121 is welded on the deflection section inner wall 112, and is in sliding friction contact with the deflection section outer wall 111, so that the deflection section inner wall can realize large axial deformation, reducing thermal stress; the trapezoidal upper base of the second deflection section inlet end support frame 124 is internally welded with a gasket with a threaded hole, the inlet end inner and outer wall positioning pin 123 is provided with a positioning pin locking gasket I 122 between the gasket, the inlet end inner and outer wall positioning pin 123 of the deflection section 110 is connected with the gasket through threads, and the inlet end inner and outer wall positioning pin 123 of the deflection section 110 is deeply inserted into the positioning hole of the deflection section outer wall 111, axial and radial deformation gaps are reserved, which are used to prevent the deflection section inner wall from excessive torsion, and also allow the deflection section inner wall to deform axially and radially, reducing the thermal stress of the deflection section inner wall; the axial gap between the inlet end inner and outer wall positioning pin 123 and the inlet end side wall of the deflection section outer wall positioning hole is δ1, and satisfies 2.8mm≤δ1≤3.2mm, the axial gap between the inlet end inner and outer wall positioning pin 123 and the exhaust end side wall of the deflection section outer wall positioning hole is δ2, and satisfies 0.3mm≤δ2≤1mm, the radial gap between the inlet end inner and outer wall positioning pin 123 and the deflection section outer wall positioning hole side wall is δ r , and satisfies 0.3mm≤δ r ≤1mm, the size of δ1 satisfies the requirement of contact after the maximum thermal deformation of the inlet end inner and outer wall positioning pin 123 and the deflection section outer wall positioning hole, the sizes of δ2 and δ r satisfy the limiting requirement of the deflection section outer wall positioning hole to the inlet end inner and outer wall positioning pin 123 after thermal deformation, which is used to prevent the deflection section inner wall from excessive torsional deformation.

[0058] As shown in Figure 1 , the hanger 132 is fixed on the cascade test section cover plate 7 by bolts, the axial direction of the hanger assembly is the same as the inlet air direction of the transition section 100, which plays a role of suspension support, and can also reduce the force of the deflection section inner wall on the deflection section outer wall through rotational deformation.

[0059] As shown in Figure 1 and Figure 3 (b), the outer wall positioning pin 165 and the deflection section outer wall 111 are provided with a positioning pin locking gasket II 166, axial and radial gaps are reserved between the outer wall positioning pin 165 and the positioning hole of the deflection section outer wall 111, the axial gap between the outer wall positioning pin 165 and the inlet end side wall of the positioning hole of the deflection section outer wall 111 is δ3, and satisfies 5mm≤δ5≤10mm, the axial gap between the outer wall positioning pin 165 and the exhaust end side wall of the positioning hole of the deflection section outer wall 111 is δ4, and satisfies 0.3mm≤δ4≤1mm, the radial gap between the outer wall positioning pin 165 and the side wall of the positioning hole of the deflection section outer wall 111 is δ rr , and satisfies 0.3mm≤δ rr ≤1mm, δ4 and δ rrThe size meets the limiting requirements of the outer wall positioning hole of the deflection section to the outer wall positioning pin after thermal deformation, which is used to prevent excessive deformation of the outer wall of the deflection section; the bracket 162 realizes sliding friction contact with the outer wall 111 of the deflection section through the circular arc groove, and the ring hoop 161 is connected with the bracket 162 through the ring hoop nut 163 and the ring hoop locking washer 164.

[0060] As shown in Figure 2 (b) and Figure 2 (c), the straight section support frame 126 and the deflection section exhaust end support frame 125 are trapezoidal structures without bottom edges, and the two waists at the intersection with the bottom edge extend in an arc shape to the two sides of the upper base of the trapezoid. The first deflection section inlet end support frame 121 is also a trapezoidal structure without a bottom edge, but the two waists at the intersection with the bottom edge extend to both sides along the inner wall contour line of the deflection section.

[0061] Figure 3 As shown in (c), the axial gap between the straight section outer wall 151 and the middle section of the deflection section outer wall 111 is δ5, and satisfies 1.7mm≤δ5≤2.8mm. The outer axial gap is sealed by two L-shaped inserts respectively welded on the straight section outer wall 151 and the deflection section outer wall 111. The axial gap δ6 of the two L-shaped inserts is equal to δ5, and the radial gap δ7 satisfies 3.5mm≤δ7≤4.5mm. The sizes of δ5, δ6 and δ7 meet the premise of ensuring sealing performance, and the straight section outer wall and the deflection section outer wall after thermal deformation do not contact after deformation.

[0062] Assembly process: a transition section structure for cold efficiency test of a turbine first stage blade, referring to Figure 4 a, first, the straight section support frame 126 is welded in the straight section outer wall 151, and the straight section outer wall 151 and the straight section inner wall 152 are welded on the cascade test section cover plate 7, to complete the installation of the straight section of the transition section; referring to Figure 2 a, the gasket with screw holes is welded in the second deflection section inlet end support frame 124; referring to Figure 1 After the deflection section inner and outer walls, the second deflection section inlet end support frame 124 and the inlet end inner and outer wall positioning pins 123 are trial positioned to ensure the gap of the positioning pins, one side of the first deflection section inlet end support frame 121 and the second deflection section inlet end support frame 124 is welded on the deflection section inner wall 112, then the other side of the support frame trapezoidal lower bottom side is pushed, so that the trapezoidal upper side of the support frame is in complete contact with the inner contour of the deflection section outer wall 111, and then the remaining side of the support frame trapezoidal lower bottom side is welded. After complete contact, the deformation of the inlet end of the deflection section inner wall 112 can be fully unloaded to the first deflection section inlet end support frame 121, the second deflection section inlet end support frame 124 and the deflection section outer wall 111; then the locking positioning pin locking washer I 122 and the inlet end inner and outer wall positioning pin 123 are installed;

[0063] Referring toFigure 1 , the trial bracket 162 and the deflection segment 110, the outer wall positioning pin 165 after the positioning pin gap, the locking positioning pin locking washer II 166 and the outer wall positioning pin 165, the ring 161 is installed on the bracket 162 through the ring nut 163, the ring locking washer 164; the lifting assembly 130 is provided with two groups, first the lifting lug 133, the lifting bracket 132, the rotating pin shaft 131, the lifting lug locking washer 134, the lifting lug nut 135 are assembled together, then the lifting assembly 130 is spot welded on the exhaust end of the deflection segment outer wall 111, the deflection segment inner wall 112 is assembled into the straight segment inner wall 152, and the combustion chamber and the cascade test section are trial assembled, and then the connecting weld of the lifting lug 133 and the deflection segment outer wall 111 is formally welded, and then the lifting lug nut 135 and the lifting lug locking washer 134 are locked.

[0064] Reference Figure 6 As shown in the deflection segment outer wall 111, the transition segment inlet elastic sealing sheet 2 is welded, and is inserted into the combustion chamber guide bushing 3, the flame tube 6 is welded with the flame tube tail end elastic sealing sheet 5, and is inserted into the deflection segment inner wall 112; the inner and outer walls of the straight segment 150 are welded on the cascade test section cover plate 7, the cascade test section cover plate 7 is partially made of high-temperature alloy, and the material of the transition segment inner wall belongs to the same category of high-temperature alloy, so as to avoid arranging dissimilar material connecting welds in the area with large temperature gradient; the deflection segment inlet support assembly 160 is installed on the test cabin through bolts;

[0065] The straight segment support frame is welded in the straight segment outer wall, and is in sliding friction contact with the straight segment inner wall, so as to support the inner and outer walls of the straight segment, prevent the expansion of the straight segment inner wall after being heated, and reduce the thermal stress of the straight segment inner wall; the deflection segment exhaust end support frame is welded in the deflection segment outer wall, and is in sliding friction contact with the deflection segment inner wall, so that the deflection segment inner wall can realize large axial deformation; the deflection segment inlet support frame is welded on the deflection segment inner wall, and is in sliding friction contact with the deflection segment outer wall, so that the deflection segment inner and outer walls form staggered constraints, and the stability of the deflection segment inner and outer walls is improved; more deflection segment exhaust end support frames are arranged on the impact surface of airflow deflection than on other surfaces, so as to absorb and transmit the force of airflow on the deflection segment inner wall; the axial direction of the lifting assembly is the same as the inlet airflow direction of the transition segment, so as to play a role in suspension and support, and can also reduce the force of the deflection segment inner wall on the deflection segment outer wall through rotation deformation.

[0066] The fluid domain of the deflection segment 110 and the straight segment 150 is extracted, and the thermal fluid-structure coupling calculation is carried out on the coupled solid structure. The temperature and pressure data calculated by the fluid are transmitted to the solid, and the contact, constraint and other boundary conditions of the solid structure are set. The thermal deformation and thermal stress of the transition segment are calculated. According to the thermal deformation result, the gap of each positioning pin and the gap between the outer walls of the segments are adjusted, and the number and position of the deflection segment exhaust end support frame 125 and the straight segment support frame 126 are adjusted, such as Figure 4As shown, more support frames are arranged on the right wall surface and the upper and lower wall surfaces of the exhaust end of the deflection section 110. According to the thermal stress and strain results, the structure of the risk area is adjusted, and in particular, according to the calculation results of the thermal stress, the arrangement of the film holes in the inner walls of the front and rear sections is adjusted, such as Figure 5 As shown, the film holes are arranged in the inner wall risk stress area at positions a, b and f to reduce the temperature and stress of the risk area, the film holes are arranged at the positions c corresponding to the lug and the positions d and h corresponding to the support frames to reduce the adverse effects of the inner wall cooling caused by the reduced impact holes of the outer wall at the lugs 133 and the support frames, a circle of film holes is arranged at the position e in front of the welding seam connecting the inner wall 152 of the straight section and the cover plate 7 of the cascade test section to reduce the temperature gradient of the connecting welding seam at this position and reduce the thermal stress, and the circular crack arrest holes are arranged at the positions g at the four corners of the probe mounting hole to prevent the four corners of the probe mounting hole from cracking.

[0067] The above embodiments only express the implementation of the present application, and the description is more specific and detailed, but it cannot be understood as a limitation on the scope of the patent. It should be noted that for those skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are all within the scope of the present application.

Claims

1. A transition section structure for turbine blade cooling efficiency test, comprising a transition section (100), characterized in that: the transition section (100) comprises a deflection section (110), a support frame assembly (120), a lifting assembly (130), and a flexible sealing sheet (140) connecting the inner walls of the two sections, a straight section (150), and a deflection section inlet end support assembly (160); the support frame assembly (120) is composed of a first deflection section inlet end support frame (121), a positioning pin locking washer I (122), an inlet end inner and outer wall positioning pin (123), a second deflection section inlet end support frame (124), a deflection section exhaust end support frame (125), and a straight section support frame (126); the deflection section inlet end support assembly (160) is composed of a ring (161), a bracket (162), a ring nut (163), a ring locking washer (164), an outer wall positioning pin (165), and a positioning pin locking washer II (166); the straight section (150) comprises a straight section outer wall (151) and a straight section inner wall (152), the straight section outer wall (151) and the straight section inner wall (152) are connected at the straight section inlet end (153) by the straight section support frame (126), and the straight section outer wall (151) and the straight section inner wall (152) are both welded to the cascade test section cover plate (7) at the straight section outlet end (154); the deflection section (110) comprises a deflection section outer wall (111) and a deflection section inner wall (112), a plurality of first deflection section inlet end support frames (121) and second deflection section inlet end support frames (124) are evenly distributed between the deflection section outer wall (111) and the deflection section inner wall (112) at the deflection section inlet end (113), the deflection section outer wall (111) and the deflection section inner wall (112) are connected at the deflection section inlet end (113) by the first deflection section inlet end support frames (121) and the second deflection section inlet end support frames (124), the second deflection section inlet end support frames (124) are welded with the inlet end inner and outer wall positioning pins (123), the outer wall of the deflection section inlet end (113) falls on the bracket (162), the bracket (162) is provided with the outer wall positioning pin (165) connected with the deflection section outer wall (111), the bracket (162) is provided with the ring (161) surrounding the deflection section outer wall (111), and the deflection section inner and outer walls are connected at the deflection section exhaust end (114) by the deflection section exhaust end support frame (125); the deflection section inner wall (112) is welded with the flexible sealing sheet (140), the flexible sealing sheet (140) is inserted into the straight section inner wall (152), and the deflection section outer wall (111) and the straight section outer wall (151) have an axial gap δ5 in the axial direction, two L-shaped insertion plates welded to the outer wall of the transition section (100) are inserted into each other outwardly, an axial gap δ6 and a radial gap δ7 are reserved between the two L-shaped insertion plates, and a multi-stage sealing is formed. ​ ​ ​ ​ ​ ​ The lifting assembly (130) comprises a rotating pin shaft (131), a lifting bracket (132), a lifting lug (133), a lifting lug locking washer (134), and a lifting lug nut (135); The lifting lug (133) and the lifting bracket (132) are assembled together through the rotating pin shaft (131), the lifting lug locking washer (134), and the lifting lug nut (135) to form the lifting assembly (130), and the lifting assembly (130) is spot-welded on the deflection segment exhaust end (114) of the deflection segment outer wall (111). A plurality of gas film holes are arranged at positions a, b, and f on the risk stress area of the deflection segment inner wall (112) and the straight segment inner wall (152), for reducing the temperature and stress of the risk area. A gas film hole is arranged at position c of the deflection segment inner wall (112) corresponding to the position of the lifting lug, position d of the deflection segment exhaust end support bracket (125), and position h of the straight segment support bracket (126), for reducing the adverse effects of the impact holes on the outer wall on the inner wall cooling at the positions of the lifting lug (133), the deflection segment exhaust end support bracket (125), and the straight segment support bracket (126). A ring of gas film holes is arranged at one side e of the welding seam between the straight segment inner wall (152) and the cascade test section cover plate (7), for reducing the temperature gradient of the connecting welding seam and reducing thermal stress. Circular crack arrest holes are arranged at positions g of the straight segment inner wall (152) at the four corners of the probe mounting hole, for preventing cracking at the four corners of the probe mounting hole.

2. The transition section structure for a turbine primary vane cold effect test according to claim 1, characterized by: The deflection segment outer wall (111) is welded to the transition segment inlet end elastic sealing sheet (2), the transition segment inlet end elastic sealing sheet (2) is inserted into the flow guide bushing (3) of the combustion chamber, the flame tube (6) is welded to the flame tube tail end elastic sealing sheet (5), and the flame tube tail end elastic sealing sheet (5) is inserted into the deflection segment inner wall (112). The deflection segment inlet end support assembly (160) is bolted to the test chamber, and one end of the straight segment (150) is provided with a blade test piece (8).

3. The transition piece structure for a turbine first stage blade cooling test according to claim 1, characterized by: The straight segment support bracket (126) is welded in the straight segment outer wall (151) and in sliding frictional contact with the straight segment inner wall (152). The deflection segment exhaust end support bracket (125) is welded in the deflection segment outer wall (111), and the deflection segment exhaust end support bracket (125) is in sliding frictional contact with the deflection segment inner wall (112).

4. The transition piece structure for a turbine first stage blade cooling test according to claim 1, characterized by: The first deflection section inlet end support frame (121) is welded on the deflection section inner wall (112), and the first deflection section inlet end support frame (121) is in sliding friction contact with the deflection section outer wall (111); the trapezoidal upper base of the second deflection section inlet end support frame (124) is internally welded with a gasket with a threaded hole, and a positioning pin locking gasket I (122) is arranged between the inlet end inner and outer wall positioning pin (123) and the gasket; the inlet end inner and outer wall positioning pin (123) of the deflection section (110) is connected with the gasket through threads, and the inlet end inner and outer wall positioning pin (123) of the deflection section (110) penetrates into the positioning hole of the deflection section outer wall (111), and an axial and radial deformation gap is reserved to prevent the deflection section inner wall from being excessively twisted, while allowing the deflection section inner wall to be axially and radially deformed, thereby reducing the thermal stress of the deflection section inner wall; the axial gap between the inlet end inner and outer wall positioning pin (123) and the inlet end side wall of the deflection section outer wall positioning hole is δ1, and satisfies 2.8mm≤δ1≤3.2mm; the axial gap between the inlet end inner and outer wall positioning pin (123) and the exhaust end side wall of the deflection section outer wall positioning hole is δ2, and satisfies 0.3mm≤δ2≤1mm; the radial gap between the inlet end inner and outer wall positioning pin (123) and the deflection section outer wall positioning hole is δ r , and satisfies 0.3mm≤δ r ≤1mm; δ1 satisfies the requirement that the inlet end inner and outer wall positioning pin (123) and the deflection section outer wall positioning hole contact after maximum thermal deformation; δ2 and δ r satisfy the requirement that the deflection section outer wall positioning hole limits the inlet end inner and outer wall positioning pin (123) after thermal deformation, thereby preventing the deflection section inner wall from being excessively twisted and deformed.

5. The transition piece structure for cold efficiency test of a turbine blade according to claim 1, characterized by: The lifting bracket (132) is bolted to the cascade test section cover plate (7), and the axial direction of the lifting assembly is the same as the inlet direction of the transition segment (100).

6. The transition piece structure for cold efficiency test of a turbine blade according to claim 1, characterized by: The outer wall positioning pin (165) and the deflection segment outer wall (111) are provided with a positioning pin locking washer II (166), the outer wall positioning pin (165) and the positioning hole of the deflection segment outer wall (111) are provided with axial and radial gaps, the axial gap of the air inlet end side wall of the positioning hole of the outer wall positioning pin (165) and the deflection segment outer wall (111) is δ3, and satisfies 5mm≤δ5≤10mm, the axial gap of the exhaust end side wall of the positioning hole of the outer wall positioning pin (165) and the deflection segment outer wall (111) is δ4, and satisfies 0.3mm≤δ4≤1mm, the radial gap of the side wall of the positioning hole of the outer wall positioning pin (165) and the deflection segment outer wall (111) is δ rr , and satisfies 0.3mm≤δ rr ≤1mm, δ4, δ rr The size satisfies the limiting requirement of the positioning hole of the deflection segment outer wall to the outer wall positioning pin after thermal deformation, and is used for preventing excessive deformation of the deflection segment outer wall; the bracket (162) realizes sliding friction contact with the deflection segment outer wall (111) through a circular arc groove, and the ring hoop (161) is connected with the bracket (162) through a ring hoop nut (163) and a ring hoop locking washer (164).

7. The transition piece structure for cold efficiency test of a turbine blade according to claim 1, wherein: The straight segment support bracket (126) and the deflection segment exhaust end support bracket (125) are both trapezoidal structures lacking a bottom side, and the intersections of the two sides with the bottom side extend in an arc shape to the two sides of the upper base of the trapezoid. The first deflection segment inlet end support bracket (121) is also a trapezoidal structure lacking a bottom side, but the intersections of the two sides with the bottom side extend to the two sides along the contour line of the deflection segment inner wall.

8. The transition piece structure for cold efficiency test of a turbine blade according to claim 1, characterized by: The axial gap of the outer wall (151) of the straight section and the middle section of the outer wall (111) of the deflection section is δ5, and satisfies 1.7mm≤δ5≤2.8mm, the outer sealing is formed by the two L-shaped inserts welded on the outer wall (151) of the straight section and the outer wall (111) of the deflection section, the axial gap δ6 of the two L-shaped inserts is equal to δ5, the radial gap is δ7, and satisfies 3.5mm≤δ7≤4.5mm, δ5, δ6, δ7 satisfy the sealing performance under the premise of heat deformation, and the outer wall of the straight section and the outer wall of the deflection section are not in contact after deformation.

Images