Axial floating mounting seat structure of ignition electric nozzle of gas turbine

Abstract

The invention belongs to the technical field of gas turbine ignition, and particularly relates to an axial floating mounting seat structure of a gas turbine ignition electric nozzle, which comprises a fixed sleeve, a compression spring and a floating bushing, the fixed sleeve is fixed on the combustion chamber casing; the floating bushing is arranged in the fixed sleeve in a sliding manner; the compression spring abuts against the outer end face of the floating bush. Air pressure in a flow guide channel between the combustion chamber casing and the flow guider can push the floating bush to slide from the extending station to the contracting station. The floating lining is used for installing the ignition electric nozzle and driving the ignition end of the ignition electric nozzle to move telescopically in the combustion area. According to the scheme, axial floating of the ignition electric nozzle can be controlled through the air pressure of introduced air in the running process of the gas turbine, so that after the gas turbine is started, the ignition electric nozzle is automatically compressed, the ignition electric nozzle is far away from a combustion chamber, the probability that the ignition electric nozzle is damaged at high temperature is reduced, and the service life of the ignition electric nozzle is prolonged.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbine ignition, and in particular relates to an axial floating mounting seat structure of a gas turbine ignition nozzle. Background Art

[0002] The ignition nozzle is one of the components of the gas turbine ignition system. Data show that 60% to 70% of ignition system failures are caused by the ignition nozzle. As a part that performs ignition work in the flame tube for a long time, the ignition nozzle faces a relatively severe environment. At the same time, with the development of gas turbine technology and the increase in power, the performance requirements for the ignition nozzle are becoming more and more stringent. If the ignition nozzle is in the flame for a long time, it will seriously affect the service life of the ignition nozzle.

[0003] Therefore, it is necessary to design an axial floating mounting seat structure to control the telescopic movement of the ignition nozzle in different operating stages of the gas turbine. Summary of the invention

[0004] In order to solve the above problems existing in the prior art, the present invention provides an axial floating mounting seat structure for an ignition nozzle of a gas turbine.

[0005] The technical solution adopted by the present invention is: An axial floating mounting seat structure of a gas turbine ignition nozzle comprises a fixed sleeve, a compression spring and a floating bushing; The combustion chamber assembly of the gas turbine includes a combustion chamber casing, a deflector and a flame tube; the combustion chamber casing is provided with a mounting cavity; the flame tube is provided in the mounting cavity, and has a combustion zone for fuel combustion in the flame tube; the deflector is provided between the combustion chamber casing and the flame tube, and a cooling hole three is provided on the side wall of the deflector to connect the inside and the outside thereof; The fixed sleeve is fixed on the combustion chamber casing; the floating bushing is arranged in the fixed sleeve, and an extension position and a retraction position are arranged in the axial direction of the fixed sleeve, and the floating bushing slides between the extension position and the retraction position; the compression spring is arranged in the fixed sleeve and abuts against the outer end surface of the floating bushing, and the compression spring is used to make the floating bushing slide from the retraction position to the extension position; a guide channel is provided between the combustion chamber casing and the guide device, and the guide channel is connected with the barrel mouth of the inner end of the fixed sleeve, so that the air pressure in the guide channel can be used to push the floating bushing to slide from the extension position to the retraction position; the floating bushing is used to install the ignition nozzle, and drive the ignition end of the ignition nozzle to telescope and move in the combustion zone.

[0006] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: a spring mounting cavity is arranged inside the outer end of the fixed sleeve, and a cooling hole is arranged on the cavity wall of the spring mounting cavity. The cooling hole is connected to the cold air source and is used for cooling the compression spring.

[0007] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: the cooling hole includes cooling hole one and cooling hole two; cooling hole two is opposite to the outer end of the compression spring, and when the compression spring is in a compressed state, cooling hole one is opposite to the inner end of the compression spring.

[0008] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: the fixed sleeve includes a pressure cap, a cap cover and a mounting seat; the mounting seat is plugged into the combustion chamber casing, the cap cover is connected to the outer end of the mounting seat, and the pressure cap is threadedly connected to the outer end of the cap cover; the second cooling hole is arranged on the pressure cap, and the first cooling hole is arranged on the cap cover; bolts fix the cap cover and the mounting seat to the combustion chamber casing.

[0009] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: the floating bushing is cylindrical; a first outer protrusion protruding radially outward is provided on the edge of the outer end of the floating bushing; two step surfaces are provided on the inner wall of the fixed sleeve, and the first outer protrusion slides between the two step surfaces; the handle end of the ignition nozzle is fixedly connected to the center hole of the floating bushing.

[0010] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: a limiting protrusion is provided on the middle inner wall of the cap cover, and one end surface of the limiting protrusion is used as a step surface; the cooling hole is located outside the limiting protrusion.

[0011] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: an eccentric bushing is arranged on the wall of the flame tube, and an eccentric hole for the ignition end of the ignition nozzle to pass through is arranged on the eccentric bushing, and the hole diameter of the eccentric hole is larger than the outer diameter of the ignition end.

[0012] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: a floating ring is arranged on the side wall of the deflector; the floating ring is slidably matched with the ignition nozzle, and the floating ring is slidably matched with the deflector; when the floating bushing moves to the retraction position, the ignition end of the ignition nozzle is retracted to the eccentric hole.

[0013] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: a burner nozzle is arranged on the front side of the combustion zone, and the burner nozzle includes an outer sequence nozzle and an inner sequence nozzle, and the outer sequence nozzle and the inner sequence nozzle are separated by an air separation ring; when the floating sleeve moves to the extension position, the ignition end of the ignition nozzle extends to the rear of the outer sequence nozzle to ignite the fuel sprayed from the outer sequence nozzle.

[0014] As an alternative or supplement to the above-mentioned axial floating mounting seat structure: the combustion chamber casing is in a circular shape, and an air intake passage is arranged on the inner ring side of the combustion chamber casing; the axial floating mounting seat structure is installed on the side wall on the outer ring side of the combustion chamber casing; when the gas turbine is started, the air in the air intake passage flows to the ignition nozzle through the gap between the combustion chamber casing and the guide vane, and compresses the floating bushing to the contraction position.

[0015] The beneficial effects of the present invention are as follows: in this scheme, the air pressure introduced during the operation of the gas turbine can be used to control the axial floating of the ignition nozzle, so that after the gas turbine is started, the ignition nozzle is automatically compressed to keep the ignition nozzle away from the combustion chamber, thereby reducing the probability of the ignition nozzle being damaged at high temperature and increasing the service life of the ignition nozzle. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below.

[0017] Figure 1 It is a schematic diagram of the extended state of the ignition nozzle; Figure 2 It is a schematic diagram of the retracted state of the ignition nozzle; Figure 3 This is the state diagram of the ignition nozzle when it is used on a gas turbine; Figure 4 This is the installation status diagram of the eccentric bushing and floating ring.

[0018] In the figure: 1-axial floating mounting seat structure; 101-pressure cap; 102-compression spring; 103-cap cover; 104-sealing ring; 105-floating bushing; 106-mounting seat; 107-first flange; 108-second flange; 109-first end of spring; 110-second end of spring; 111-groove; 112-cooling hole one; 113-cooling hole two; 114-limiting protrusion; 117-external thread end; 118-center hole; 119-contact surface; 2-combustion chamber assembly; 201-combustion chamber casing; 203-bolt; 204-cooling hole three; 205-flame tube; 206-external sequence nozzle; 207-combustion zone; 208-intake channel; 209-deflector; 210-eccentric bushing; 211-floating ring; 3-ignition nozzle; 31-ignition end. DETAILED DESCRIPTION

[0019] The technical solution in this embodiment will be clearly and completely described below in conjunction with the accompanying drawings. The described embodiments are only some of the embodiments, not all of them. Based on the embodiments in this solution, all other embodiments obtained by ordinary technicians in this field without making creative work are within the protection scope of this solution.

[0020] like Figure 3 As shown, the combustion chamber assembly 2 of the gas turbine includes a combustion chamber casing 201, a deflector 209 and a flame tube 205; a mounting cavity is arranged in the combustion chamber casing 201; the flame tube 205 is arranged in the mounting cavity, and a combustion zone 207 for fuel combustion is provided in the flame tube 205; the deflector 209 is arranged between the combustion chamber casing 201 and the flame tube 205, and a cooling hole 204 is arranged on the side wall of the deflector 209 to connect the inside and the outside thereof.

[0021] The combustion chamber casing 201 is in a circular shape, and an air intake passage 208 is arranged on the inner ring side of the combustion chamber casing 201; a flow guide passage is provided between the combustion chamber casing 201 and the guide device 209, and the air intake passage 208 is connected to the flow guide passage.

[0022] like Figures 1 to 4 As shown, this embodiment designs an axial floating mounting seat structure 1 of a gas turbine ignition nozzle 3 , and the axial floating mounting seat structure 1 is mounted on the side wall of the outer ring side of the combustion chamber casing 201 .

[0023] The axial floating mounting seat structure 1 includes components such as a fixed sleeve, a compression spring 102 and a floating bushing 105 .

[0024] The fixed sleeve is fixed on the combustion chamber casing 201 when in use. Specifically, the outer end of the fixed sleeve is located outside the combustion chamber casing 201, and the inner end of the fixed sleeve extends into the guide channel between the combustion chamber casing 201 and the guide device 209, so as to utilize the air in the guide channel to compress the floating bushing 105.

[0025] The fixed sleeve includes a pressure cap 101, a cap cover 103 and a mounting seat 106. The mounting seat 106 is cylindrical, and a second flange 108 is provided at the upper end of the mounting seat 106. When installed, the mounting seat 106 is plugged into the combustion chamber casing 201, and the second flange 108 is closely attached to the outer wall of the combustion chamber casing 201. The cap cover 103 is in the shape of a circular sleeve, and a first flange 107 is arranged at the lower end of the cap cover 103; during installation, the cap cover 103 is coaxially arranged on the mounting seat 106, the first flange 107 is affixed to the second flange 108, and the bolts 203 pass through the flange holes of the first flange 107 on the cap cover 103 and the flange holes of the second flange on the mounting seat 106, and both are fixed to the combustion chamber casing 201; a second cooling hole 113 is arranged on the pressure cap 101, and the second cooling hole 113 is located on the groove wall of the groove 111, so that the outer end of the compression spring 102 (the end away from the center of the gas turbine, that is, the first end 109 of the spring) can be cooled by using the second cooling hole 113. The pressure cap 101 is in a circular shape, and the lower end of the pressure cap 101 is an external thread end 117. When in use, the pressure cap 101 is coaxially threadedly connected to the outer end of the cap cover 103 (the end away from the center of the gas turbine), and a groove 111 is provided inside the outer end of the pressure cap 101. The groove 111 is used to accommodate the outer end of the compression spring 102 (the end away from the center of the gas turbine, i.e., the first end 109 of the spring) to limit the outer end of the compression spring 102. When the ignition nozzle 3 extends into the center of the fixed sleeve, a gap is formed between the pressure cap 101 and the ignition nozzle 3, and the air entering from the cooling hole 2 113 and the cooling hole 1 112 is discharged from the gap after cooling the spring.

[0026] A spring installation cavity is provided inside the outer end of the fixed sleeve (i.e., the end away from the center of the gas turbine), and cooling holes are provided on the cavity wall of the spring installation cavity. The cooling holes (the cooling holes include cooling hole 112 and cooling hole 2 113) are connected to the cold air source and are used to cool the compression spring 102. In order to prevent the elastic force of the compression spring 102 from being reduced under high temperature, the service life of the compression spring 102 and the axial floating mounting seat structure 1 can be effectively improved by cooling the compression spring 102. The cooling hole 2 113 is opposite to the outer end of the compression spring 102. When the compression spring 102 is in a compressed state, the cooling hole 112 is opposite to the inner end of the compression spring 102 (the end close to the center of the gas turbine, i.e., the second end 110 of the spring), thereby improving the cooling efficiency of the cooling hole on the compression spring 102.

[0027] The floating bushing 105 is slidably arranged in the fixed sleeve, and an extension position and a retraction position are arranged in the axial direction of the fixed sleeve, and the floating bushing 105 can slide between the extension position and the retraction position. The compression spring 102 is arranged in the fixed sleeve and abuts against the outer end surface of the floating bushing 105. The compression spring 102 is used to make the floating bushing 105 slide from the retraction position to the extension position; there is a guide channel between the combustion chamber casing 201 and the guide 209, and the guide channel is connected to the barrel mouth of the inner end of the fixed sleeve. When the air pressure in the guide channel is increased to above the set numerical range, the air pressure in the guide channel pushes the floating bushing 105 to slide from the extension position to the retraction position; and when the air pressure in the guide channel is reduced to below the set numerical range, the spring's own elastic force is greater than the air pressure driving force, and the compression spring 102 pushes the floating bushing 105 to move inward, so that it slides from the retraction position to the extension position.

[0028] The floating bushing 105 is cylindrical; a first outer protrusion protruding radially outward is provided at the edge of the outer end of the floating bushing 105; two step surfaces are provided on the inner wall of the fixed sleeve, and the first outer protrusion slides between the two step surfaces. Specifically, a limiting protrusion 114 is provided on the inner wall of the middle part of the cap 103, and one end surface of the limiting protrusion 114 is used as a step surface; the cooling hole 112 is located on the outer side of the limiting protrusion 114. A sealing ring 104 is also provided at the upper end of the floating bushing 105. When the floating bushing 105 is in the contraction position, the sealing ring 104 cooperates with the limiting protrusion 114 to seal.

[0029] The ignition nozzle 3 of the gas turbine is mounted on the floating bushing 105. When the floating bushing 105 moves along the axial direction of the fixed sleeve, the ignition nozzle 3 is driven to move synchronously, so that the ignition end 31 of the ignition nozzle 3 moves telescopically in the combustion zone 207. The external thread at the handle end of the ignition nozzle 3 is screwed and fixed on the internal thread of the center hole 118 of the floating bushing 105 and pressed against the contact surface 119 of the floating bushing 105. At the same time, the ignition end 31 of the ignition nozzle 3 passes through the floating bushing 105 and extends out of the axial floating mounting seat structure 1.

[0030] An eccentric bushing 210 is provided on the wall of the flame tube 205. An eccentric hole is provided on the eccentric bushing 210 for the ignition end 31 of the ignition nozzle 3 to pass through. The diameter of the eccentric hole is larger than the outer diameter of the ignition end 31, thereby preventing the ignition nozzle 3 from colliding with the flame tube 205. A floating ring 211 is provided on the side wall of the deflector 209; the floating ring 211 is in sliding cooperation with the ignition nozzle 3, and the floating ring 211 is in sliding cooperation with the deflector 209; when the floating bushing 105 moves to the contraction position, the ignition end 31 of the ignition nozzle 3 contracts to the eccentric hole, thereby reducing the influence of the combustion flame on the ignition nozzle 3.

[0031] A burner nozzle is arranged at the front side of the combustion zone 207, and the burner nozzle includes an outer sequence nozzle 206 and an inner sequence nozzle, and the outer sequence nozzle 206 and the inner sequence nozzle are separated by an air isolation ring; when the floating sleeve 105 moves to the extended position, the ignition end 31 of the ignition nozzle 3 extends to the rear of the outer sequence nozzle 206 to ignite the fuel sprayed from the outer sequence nozzle 206.

[0032] When the axial floating mounting seat structure 1 of this embodiment is used, the axial floating mounting seat structure 1 is mounted on the combustion chamber casing 201, and the ignition nozzle 3 is mounted on the axial floating mounting seat structure 1. When the gas turbine is started, as the operating power of the gas turbine increases, the air entering the intake passage 208 also gradually increases. Since part of the air will flow to the ignition nozzle 3 through the guide passage between the combustion chamber casing 201 and the guide 209, the air pressure in the guide passage at the ignition nozzle 3 will increase as the operating power of the gas turbine increases. When the air pressure rises above the set range, the air pressure squeezes the end face of the floating bushing 105 and compresses the floating bushing 105 to the retracted position. Conversely, when the operating power of the gas turbine decreases, the compression spring 102 will push the floating bushing 105 to return to the extended position.

[0033] The elastic force of the compression spring 102 should match the set range of the air pressure in the guide channel, the fuel spraying range of the burner nozzle, the operating power of the gas turbine and other values, so that when the ignition nozzle 3 is in the extended position or the retracted position, it should be ensured that the ignition nozzle 3 can ignite smoothly.

[0034] The above embodiments are merely examples for the purpose of clarifying the description, and are not intended to limit the implementation methods; it is not necessary and impossible to list all implementation methods exhaustively. However, obvious changes or modifications derived therefrom are still within the scope of protection of the present technology.

Claims

1. An axial floating mounting seat structure for a gas turbine ignition nozzle, characterized in that: It comprises a fixed sleeve, a compression spring (102) and a floating bushing (105); A combustion chamber assembly (2) of a gas turbine comprises a combustion chamber casing (201), a flow guide (209) and a flame tube (205); a mounting cavity is arranged in the combustion chamber casing (201); the flame tube (205) is arranged in the mounting cavity, and a combustion zone (207) for fuel combustion is provided in the flame tube (205); the flow guide (209) is arranged between the combustion chamber casing (201) and the flame tube (205), and a cooling hole (204) is provided on a side wall of the flow guide (209) to connect the inside and outside thereof; The fixed sleeve is fixed on the combustion chamber casing (201); the floating sleeve (105) is arranged in the fixed sleeve, and an extension position and a retraction position are arranged in the axial direction of the fixed sleeve, and the floating sleeve (105) slides between the extension position and the retraction position; the compression spring (102) is arranged in the fixed sleeve and abuts against the outer end surface of the floating sleeve (105), and the compression spring (102) is used to make the floating sleeve (105) slide from the retraction position to the extension position; a guide channel is provided between the combustion chamber casing (201) and the guide device (209), and the guide channel is connected to the barrel mouth of the inner end of the fixed sleeve, so that the floating sleeve (105) can be pushed by the air pressure in the guide channel to slide from the extension position to the retraction position; the floating sleeve (105) is used to install the ignition nozzle (3) and drive the ignition end (31) of the ignition nozzle (3) to move telescopically in the combustion zone (207).

2. The axial floating mounting seat structure of the gas turbine ignition nozzle according to claim 1 is characterized in that: A spring installation cavity is provided inside the outer end of the fixed sleeve, and a cooling hole is provided on the cavity wall of the spring installation cavity. The cooling hole is connected to a cold air source and is used for cooling the compression spring (102).

3. The axial floating mounting seat structure of the gas turbine ignition nozzle according to claim 2 is characterized in that: The cooling holes include cooling hole one (112) and cooling hole two (113); cooling hole two (113) is opposite to the outer end of the compression spring (102); when the compression spring (102) is in a compressed state, cooling hole one (112) is opposite to the inner end of the compression spring (102).

4. The axial floating mounting seat structure of the gas turbine ignition nozzle according to claim 3 is characterized in that: The fixing sleeve comprises a pressing cap (101), a cap cover (103) and a mounting seat (106); the mounting seat (106) is plugged into a combustion chamber casing (201), the cap cover (103) is connected to the outer end of the mounting seat (106), and the pressing cap (101) is threadedly connected to the outer end of the cap cover (103); the second cooling hole (113) is arranged on the pressing cap (101), and the first cooling hole (112) is arranged on the cap cover (103); and the bolts (203) fix the cap cover (103) and the mounting seat (106) to the combustion chamber casing (201).

5. The axial floating mounting seat structure of the gas turbine ignition nozzle according to claim 4 is characterized in that: The floating bushing (105) is cylindrical; a first outer convex portion protruding radially outward is provided on the edge of the outer end of the floating bushing (105); two step surfaces are provided on the inner wall of the fixed sleeve, and the first outer convex portion slides between the two step surfaces; the handle end of the ignition nozzle (3) is fixedly connected to the center hole (118) of the floating bushing (105).

6. The axial floating mounting seat structure of the gas turbine ignition nozzle according to claim 5 is characterized in that: A limiting protrusion (114) is provided on the middle inner wall of the cap cover (103), and one end surface of the limiting protrusion (114) is used as a step surface; the cooling hole 1 (112) is located outside the limiting protrusion (114).

7. The axial floating mounting seat structure of the gas turbine ignition nozzle according to any one of claims 1 to 6, characterized in that: An eccentric bushing (210) is arranged on the wall of the flame tube (205), and an eccentric hole for the ignition end (31) of the ignition nozzle (3) to pass through is arranged on the eccentric bushing (210), and the hole diameter of the eccentric hole is larger than the outer diameter of the ignition end (31).

8. The axial floating mounting seat structure of the gas turbine ignition nozzle according to claim 7, characterized in that: A floating ring (211) is provided on the side wall of the deflector (209); the floating ring (211) is in sliding cooperation with the ignition nozzle (3); the floating ring (211) is in sliding cooperation with the deflector (209); when the floating bushing (105) moves to the contraction position, the ignition end (31) of the ignition nozzle (3) contracts to the eccentric hole.

9. The axial floating mounting seat structure of the gas turbine ignition nozzle according to any one of claims 1 to 6, characterized in that: A burner nozzle is provided at the front side of the combustion zone (207), the burner nozzle comprising an outer sequence nozzle (206) and an inner sequence nozzle, the outer sequence nozzle (206) and the inner sequence nozzle being separated by an air isolation ring; when the floating bushing (105) moves to the extension position, the ignition end (31) of the ignition nozzle (3) extends to the rear of the outer sequence nozzle (206) to ignite the fuel sprayed from the outer sequence nozzle (206).

10. The axial floating mounting seat structure of the gas turbine ignition nozzle according to claim 9, characterized in that: The combustion chamber casing (201) is in the shape of a ring, and an air intake passage (208) is arranged on the inner ring side of the combustion chamber casing (201); the axial floating mounting seat (106) structure is mounted on the side wall of the outer ring side of the combustion chamber casing (201); when the gas turbine is started, the air in the air intake passage (208) flows to the ignition nozzle (3) through the gap between the combustion chamber casing (201) and the guide vane (209), and compresses the floating bushing (105) to the contraction position.

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