A flow guide device for cooling working fluid at turbine inlet

Abstract

The present invention provides a flow guide device for cooling the working medium at the turbine inlet, comprising a body axially restricted between the combustion chamber and the turbine, an annular cavity inside the body, at least one working medium flow channel for guiding the working medium from the combustion chamber to the turbine, the working medium flow channel at least comprising a tapered section with two guide plates gradually approaching each other, and the guide plates on both sides are fixedly connected to the inner and outer surfaces of the annular cavity. The advantages of the present invention are: the working medium is accelerated and cooled through the working medium flow channel before flowing into the turbine inlet, thereby solving the restriction of the heat load of the turbine blades on the combustion chamber outlet temperature; in addition, the initial velocity of the working medium entering the turbine inlet is higher, which can improve the efficiency of the turbine stage, generate greater thrust, reduce the output of the SFC in the startup stage, and reduce the power consumption of the combustion engine.

Description

Technical Field

[0001] The invention relates to the technical field of turbine working medium pretreatment, and in particular to a flow guiding device for cooling working medium at a turbine inlet. Background Art

[0002] Modern gas turbines are constantly developing towards high parameters and high efficiency. Improving the combustion chamber outlet temperature (i.e., turbine inlet temperature) can increase the output of gas turbines and improve the efficiency of gas turbines, which is the current development direction of equipment. However, with the continuous increase in turbine inlet temperature, the temperature of the gas in the turbine has far exceeded the allowable temperature of the blade material, and the increase in gas temperature also leads to an increase in blade heat load and thermal stress, which poses a severe challenge to turbine design.

[0003] Turbine blades rotate and work in a high-temperature environment for a long time. The high-temperature resistance of turbine blades is currently the main bottleneck factor restricting the increase of the combustion chamber outlet temperature. At present, gas turbine manufacturers generally use a combination of high-temperature resistant materials and secondary cooling air systems to improve the high-temperature resistance of turbine inlet blades. These high-temperature resistant materials are expensive, require extremely high manufacturing technology, and have a high scrap rate, accounting for a large proportion of the gas turbine production cost. The secondary cooling air system cools the subsequent turbine blades by extracting air from the intermediate stage of the compressor; this method will reduce the operating efficiency of the compressor, thereby affecting the overall operating efficiency of the gas turbine. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a guide device for automatically cooling the high-temperature working fluid in the combustion chamber and then sending it into the turbine inlet, thereby solving the problem of turbine cooling and overcoming the restriction of the high-temperature resistance of the turbine on the efficiency of the combustion engine.

[0005] The present invention solves the above technical problems through the following technical solutions: a guide device for cooling the working fluid at the turbine inlet, comprising a main body axially restricted between the combustion chamber and the turbine, the main body having an annular cavity inside, the annular cavity being provided with at least one working fluid flow channel for guiding the working fluid from the combustion chamber to the turbine, the working fluid flow channel comprising at least a tapered section where guide plates on both sides gradually approach each other, and the guide plates on both sides are fixedly connected to the inner and outer surfaces of the annular cavity.

[0006] The present invention adds a guide device between the combustion chamber and the turbine, and the high-temperature flue gas at the combustion chamber outlet advances into the turbine along the working medium flow channel. Since the working medium flow channel includes at least a tapered section, the passing flue gas working medium can be accelerated and cooled, so that the high-temperature flue gas flowing out of the combustion chamber flows into the turbine inlet after being cooled by the guide device, thereby solving the restriction of the thermal load of the turbine blades on the combustion chamber outlet temperature, and can increase the engine output and improve the engine efficiency. In addition, since the working medium will be accelerated after passing through the guide device, the initial velocity entering the turbine inlet is higher, which can improve the turbine stage efficiency, generate greater thrust, and reduce the SFC output in the startup stage. The SFC power consumption is the main factor of the engine's own power consumption. Therefore, the engine power consumption can also be reduced by setting the guide device.

[0007] Preferably, the working medium flow channel is arranged in a spiral shape, and the speed direction of the working medium leaving the flow guide device is consistent with the direction of the turbine inlet flow channel.

[0008] Preferably, the working fluid flow channel also includes an outlet section connected to the turbine inlet, and the working fluid flow channel composed of the tapered section and the outlet section is a tapered flow channel or a convergent flow channel as a whole. The outlet section of the convergent flow channel includes two diffusers that cooperate with the ends of the two guide plates, and at least one side of the diffuser is bent toward the outside of the working fluid flow channel to expand the working fluid flow area.

[0009] Preferably, it also includes an adjustment ring cavity that is coaxially matched with the end of the body and can rotate relative to the body; the adjustment ring cavity is consistent with the axial size of the inner cavity of the annular cavity; the adjustment ring cavity can rotate to switch the working fluid flow channel in the flow guide device between a tapered flow channel and a zoom flow channel.

[0010] Preferably, the interior of the adjustment ring cavity is provided with a tapered outlet and a zoom outlet that can be connected with the end of the tapered section in the annular cavity, the tapered outlet includes two guide plates that are connected with the end of the guide plate and gradually approach each other; the zoom outlet includes two expansion plates; the tapered outlet and the zoom outlet are arranged in the cavity of the adjustment ring cavity at intervals along the circumferential direction.

[0011] Preferably, an optical axis with a radius smaller than the inner diameter of the annular cavity is coaxially arranged at the end of the main body, the adjustment ring cavity is sleeved on the optical axis, and the end of the optical axis is locked by a nut with a diameter not larger than the outer diameter of the inner layer of the adjustment ring cavity; the front end of the adjustment ring cavity is tightly attached to the end face of the end of the annular cavity, and they are freely matched circumferentially; the end of the adjustment ring cavity is axially tightly attached to the turbine inlet, and they are freely matched circumferentially.

[0012] Preferably, it also includes a driving mechanism fixedly matched with the outer surface of the adjustment ring cavity, the driving mechanism includes a flange plate penetrating the outer periphery of the adjustment ring cavity, the flange plate is provided with a locking piece fixedly matched with the outer surface of the adjustment ring cavity, the locking piece fixes the adjustment ring cavity and the flange plate in the circumferential direction, and the flange plate can rotate inside the gas turbine.

[0013] Preferably, the driving mechanism also includes at least two fixing plates which are symmetrically arranged on the center of the flange and fixedly matched with the inside of the gas turbine; the flange and the fixing plate are respectively provided with a pin shaft and an arc groove which match each other, the arc groove is concentric with the flange, the pin shaft is axially passed through and fixed in the arc groove, and the pin shaft can slide freely in the arc groove.

[0014] Preferably, a cylinder is further provided on the fixing plate, and the cylinder seat and the cylinder rod are respectively hingedly matched with the fixing plate and the flange, and the hinge axes are parallel to the axial direction of the flange.

[0015] Preferably, the locking member includes a connecting rod and a locking plate, the two ends of the connecting rod are respectively hingedly matched with the flange and the locking plate, the hinge axis points to the axis of the flange, and a plurality of locking rods protrude radially from the outer periphery of the adjustment ring cavity, and the locking plate is also hingedly matched with the locking rod.

[0016] The advantages of the flow guide device for cooling the working medium at the turbine inlet provided by the present invention are as follows: by adding the flow guide device between the combustion chamber and the turbine, the high-temperature flue gas at the combustion chamber outlet advances into the turbine along the working medium flow channel. Since the working medium flow channel at least includes a tapered section, the passing flue gas working medium can be cooled down at an accelerated rate, so that the high-temperature flue gas flowing out of the combustion chamber flows into the turbine inlet after being cooled down by the flow guide device. Automatic cooling of the working medium can be achieved without the need for an additional cold source, and the whole process does not require the reduction of the engine operating efficiency. The operation is simple and the heat load of the turbine blades is solved. The restriction of the combustion chamber outlet temperature can increase the engine output and improve the engine efficiency. In addition, since the working fluid will be accelerated after passing through the guide device, the initial velocity entering the turbine inlet is higher, which can improve the turbine stage efficiency, generate greater thrust, and reduce the SFC output during the startup phase. The SFC power consumption is the main factor in the engine's own power consumption. Therefore, the engine power consumption can be reduced by setting the guide device. By introducing the adjustment ring cavity, the working fluid flow channel can be easily switched between the gradually converging flow channel and the zooming flow channel, and the most suitable flow channel structure can be selected according to work needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 An axial front view of the body of a flow guide device for cooling a working medium at a turbine inlet provided by an embodiment of the present invention;

[0018] Figure 2 A schematic diagram of a zoom flow channel of a flow guide device for cooling a working medium at a turbine inlet provided by an embodiment of the present invention;

[0019] Figure 3 An exploded view of a flow guide device for cooling a working medium at a turbine inlet provided by an embodiment of the present invention;

[0020] Figure 4A schematic diagram of the assembly of a tapered outlet of a flow guide device for cooling a working medium at a turbine inlet provided by an embodiment of the present invention;

[0021] Figure 5 A schematic diagram of a scaled outlet assembly of a flow guide device for cooling a turbine inlet working medium provided by an embodiment of the present invention;

[0022] Figure 6 A schematic diagram of the coordination state of the driving mechanism and the adjusting ring cavity of the flow guide device for cooling the working medium at the turbine inlet provided by an embodiment of the present invention;

[0023] Figure 7 A schematic diagram of the matching form of a flow guide device and a driving mechanism for cooling a working medium at a turbine inlet provided by an embodiment of the present invention;

[0024] Figure 8 A schematic diagram of the matching manner of the end faces of the main body and the adjusting ring cavity of the flow guide device for cooling the working fluid at the turbine inlet provided in an embodiment of the present invention. DETAILED DESCRIPTION

[0025] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

[0026] This embodiment provides a flow guide device for cooling the working medium at the turbine inlet, which is used to guide the flue gas working medium discharged from the combustion chamber outlet of the gas turbine to the turbine. Figure 1 and Figure 2 , including a body 1 axially restricted between a combustion chamber and a turbine, the body 1 having an annular cavity 11 matched with an outlet of the combustion chamber, a working fluid flow channel 12 for guiding the working fluid from the combustion chamber to the turbine is arranged in the annular cavity 11, the working fluid flow channel 12 at least includes a tapered section 121 gradually approached by guide plates 13 on both sides, the guide plates 13 on both sides are fixedly connected to the inner and outer surfaces of the annular cavity 11, thereby separating the flow channel of the tapered section 121 from other parts of the annular cavity 11, and can be used to fix the inner and outer surfaces of the annular cavity 11; technicians in this field can set multiple working fluid flow channels 12 in the annular cavity 11 as needed, or only set one working fluid flow channel 12; when the number of working fluid flow channels is small and the fixing effect of the guide plates 13 on the inner and outer surfaces of the annular cavity 11 is not good, other fixed connection structures can be set in the annular cavity 11 area outside the guide plates 13 to strengthen the structural strength of the annular cavity 11.

[0027] According to the relevant knowledge of engineering thermodynamics, the influence of cross-sectional area on various flow characteristics can be summarized as follows: one-dimensional steady isentropic flow has the flow characteristics of expansion acceleration or compression deceleration. The flow in the reducing flow channel is expansion acceleration. The flow velocity of the working fluid increases continuously along the pipeline, while the pressure, density and temperature decrease continuously.

[0028] In this embodiment, a guide device is added between the combustion chamber and the turbine, and the high-temperature flue gas at the combustion chamber outlet advances into the turbine along the working fluid flow channel. Since the working fluid flow channel 12 includes at least a tapered section 121, the passing flue gas working fluid can be accelerated and cooled, so that the high-temperature flue gas flowing out of the combustion chamber is cooled by the guide device and then flows into the turbine inlet, thereby solving the restriction of the thermal load of the turbine blades on the combustion chamber outlet temperature, and can increase the engine output and improve the engine efficiency. In addition, since the working fluid will be accelerated after passing through the guide device, the initial velocity entering the turbine inlet is higher, which can improve the turbine stage efficiency, generate greater thrust, and reduce the output of the starting frequency converter (SFC) during the startup phase. The power consumption of the SFC is the main factor of the engine's own power consumption. Therefore, the engine power consumption can also be reduced by providing the guide device.

[0029] In order to reduce the speed loss of the working fluid entering the turbine from the guide device, the working fluid flow channel 12 is preferably a spiral flow channel, so as to pre-swirl the working fluid and make the speed direction of the working fluid leaving the guide device consistent with the direction of the turbine inlet flow channel; based on this requirement, technical personnel in this field can adaptively set the shape of the working fluid flow channel 12, maintain a natural transition inside the working fluid flow channel 12 and make the outlet direction of the working fluid flow channel 12 consistent with the turbine inlet direction.

[0030] refer to Figure 2 The working fluid flow channel 12 also includes an outlet section 122 connected to the turbine inlet. Those skilled in the art can set the working fluid flow channel 12 composed of the tapered section 121 and the outlet section 122 as a tapered flow channel or a convergent flow channel as a whole according to needs; the outlet section 122 of the convergent flow channel includes two diffusers 14 matched with the ends of the two guide plates 13, one of the diffusers 14 is bent toward the outside of the working fluid flow channel 12 to expand the working fluid flow area, and those skilled in the art can choose to bend the diffuser 14 on any side outward, or both diffusers 14 are bent outward.

[0031] The working fluid flow rate through the tapered flow channel can reach subsonic speed at the fastest, while the working fluid flow rate through the zoom flow channel can reach supersonic speed at the fastest. Users can determine the specific flow channel form based on the requirements of cooling and power; refer to Figure 3-Figure 5 This embodiment provides an adjustment ring cavity 2 that can cooperate with the end of the body 1 along the axial direction. By rotating the adjustment ring cavity 2, the working fluid flow channel 12 can be conveniently adjusted to a tapered flow channel or a zoom flow channel.

[0032] The axial dimensions of the adjusting ring cavity 2 are consistent with those of the inner cavity of the annular cavity 11. The cavity of the adjusting ring cavity 2 is provided with a tapered outlet 21 and a zoom outlet 22 which can be connected with the end of the tapered section 121 in the annular cavity 11 to make a natural transition of the working fluid flow channel 12; the tapered outlet 21 includes two guide plates 23 which are connected with the end of the guide plate 13 and gradually approach each other, and the zoom outlet 22 sets the expansion plates 14 on both sides thereof in the adjusting ring cavity 2, and the tapered outlet 21 and the zoom outlet 22 are arranged in the cavity of the adjusting ring cavity 2 at intervals along the axial direction, so that the adjusting ring cavity 2 can be rotated to switch the outlet structure which cooperates with the end of the tapered section 121, so that the working fluid flow channel 12 can be switched between the tapered flow channel and the zoom flow channel.

[0033] refer to Figure 3 The end of the body 1 is provided with an optical axis 15 with a radius smaller than the inner diameter of the annular cavity 11 along the axial direction, and the adjusting ring cavity 2 is provided with a through hole 24 that matches the optical axis 15 along the axial direction. The adjusting ring cavity 2 is sleeved on the optical axis 15, and the end of the optical axis 15 is locked by a nut 16 whose diameter is not larger than the inner diameter of the cavity of the adjusting ring cavity 2. Since the size of the optical axis 15 is relatively large, the nut 16 selected in this embodiment has only internal threads and cannot be fixed using conventional tools such as wrenches. It can be tightened or loosened by rotating the adjustment rod inserted radially into the surface of the nut 16. After fixing, the front end of the adjusting ring cavity 2 is tightly attached to the end end face of the annular cavity 11, and the adjusting ring cavity 2 can rotate freely on the optical axis 15; the end of the adjusting ring cavity 2 is tightly attached to the turbine inlet axially and freely matched circumferentially, so that the adjusting ring cavity 2 can rotate and switch the flow channel form without hindrance.

[0034] There is no relative displacement or rotation between the front end of the body 1 and the outlet of the combustion chamber, so the front end of the body 1 can be directly fixedly connected to the outlet of the combustion chamber. When used, the fixing method can be selected according to the actual situation, such as fixed connection by bolts, or other components in the gas turbine can be used to assist in fixing the body 1 so that it remains relatively fixed to the combustion chamber. The adjustment ring cavity 2 and the turbine need to be circumferentially free. When used, the adjustment ring cavity 2 and the turbine can be kept independent of each other, or the turbine and the adjustment ring cavity 2 can be connected together through an axial plug-in structure for auxiliary support; the specific matching method can be adaptively designed based on the technical solution and working principle provided in this embodiment.

[0035] refer to Figure 6 The driving mechanism (not shown) that is fixedly matched with the outer surface of the adjusting ring cavity 2 drives it to rotate relative to the body 1; the driving mechanism includes a flange 31 that is penetrated through the outer periphery of the adjusting ring cavity 2, and the flange 31 is provided with a locking piece 32 that is fixedly matched with the outer surface of the adjusting ring cavity 2. The adjusting ring cavity 2 and the flange 31 are fixedly matched along the circumferential direction by the locking piece 32, and the flange 31 can rotate inside the gas turbine, thereby driving the adjusting ring cavity 2 to rotate together.

[0036] Combination Figure 7 The driving mechanism further comprises at least two fixing plates 33 which are symmetrical with respect to the center of the flange 31. The fixing plates 33 are fixed inside the gas turbine. The specific fixing method can be set adaptively according to the actual working conditions; such as welding, screw connection, clamping and fixing, etc.; the flange 31 and the fixing plate 33 are respectively provided with a pin shaft 34 and an arc groove 35 which cooperate with each other, wherein the arc groove 35 is concentric with the flange 31, so that the rotation of the flange 31 relative to the fixing plate 33 is realized by the relative rotation of the pin shaft 34 in the arc groove 35. In this embodiment, the pin shaft 34 is set on the flange 31, and the arc groove 35 is set on the fixing plate 33. The pin shaft 34 is axially restricted in the arc groove 35 and can slide freely in the arc groove 35.

[0037] refer to Figure 6 , at least one fixed plate 33 is provided with a cylinder 36. In this embodiment, the cylinder seat 361 is hingedly matched with the fixed plate 33, the cylinder rod 362 is hingedly matched with the flange 31, and the hinge axes are parallel to the axial direction of the flange 31. Since the fixed plate 33 is fixed, when the cylinder 36 is extended or contracted, the flange 31 will rotate under the drive of the cylinder rod 362, so that the rotation direction and angle of the flange 31 are controlled by the action of the cylinder 36; in specific use, the cylinder 36 can be replaced with other linear drive devices, and a corresponding power system needs to be set up in addition.

[0038] The locking member 32 includes a connecting rod 321 and a locking plate 322. The two ends of the connecting rod 321 are respectively hinged with the flange 31 and the locking plate 322, and the hinge axes are all directed to the axis of the flange 31, that is, along the radial direction of the flange 31. The outer periphery of the adjusting ring cavity 2 is provided with a plurality of locking rods 25 protruding radially. The locking rods 25 pass through the locking plate 321 and are fastened by nuts, so as to be hinged with the locking plate 321. Figure 6 Only one locking member 32 and locking rod 25 are shown in the figure. In actual use, multiple locking members 32 and locking rods 25 cooperating therewith can be arranged along the circumferential direction as needed, so as to achieve the circumferential fixed cooperation between the flange 31 and the adjustment ring cavity 2. When the axial distance between the flange 31 and the adjustment ring cavity 2 changes, the mutually hinged connecting rod 321 and the locking plate 322 can be adaptively rotated to adjust the spacing, thereby reducing the stress received by the locking member 32 and improving the service life. In order to fix the connecting rod 321 arranged radially along the hinge shaft, the flange 31 also protrudes outward on one side of the locking member 32 to form an annular boss 311, and a hinge shaft that is hinged and cooperated with the connecting rod 321 is arranged radially on the annular boss 311.

[0039] The method of changing the flow channel structure by rotating the adjusting ring cavity 2 by the driving mechanism requires accurate determination of the rotation angle of the driving mechanism to prevent deviation in the flow channel matching, which may lead to partial leakage of the working fluid; Figure 8 In the preferred embodiment, a protrusion 41 and a recess 42 are respectively provided on the end surfaces of the body 1 and the adjusting ring cavity 2. The protrusion 41 can rotate circumferentially in the recess 42. Both ends of the arc of the protrusion 41 and the recess 42 are provided with arc-shaped step surfaces. During the sliding process of the protrusion 41 in the recess 42, the step surfaces at both ends of the protrusion 41 and the recess 42 always maintain partial contact to seal the flow channel. The two extreme positions of the rotation of the protrusion 41 in the recess 42 are tapered sections 121 They cooperate with the tapered outlet 21 and the zoom outlet 22 respectively; thus, the driving stroke of the driving mechanism is determined by the rotation of the protrusion 41 in the recess 42, and precise control can be achieved through electronic devices such as contact switches and travel switches; the protrusion 41 and the recess 42 can be adaptively arranged on the outer surface or inner surface of the body 1 and the adjustment ring cavity 2. When arranged on the inner surface, due to the existence of the optical axis 15, the protrusion 41 and the recess 42 may not be provided with step surfaces for sealing the working fluid flow channel 12 at both ends. Those skilled in the art can also adaptively choose to respectively set a top ball spring and a receiving hole for receiving a top ball on the end surfaces of the body 1 and the adjustment ring cavity 2 that cooperate with each other to achieve precise switching of the working fluid flow channel 12. At this time, the start and stop of the driving mechanism can be controlled by detecting the change of the spring pressure in the top ball spring through a pressure sensor.

[0040] Those skilled in the art should know that the structures, proportions, sizes, etc. illustrated in the drawings of this specification are only used to match the contents disclosed in the embodiments, and are not used to limit the limiting conditions for the implementation of the present invention, so they have no substantial technical significance. Any modification of the structure, change of the proportion relationship or adjustment of the size, without affecting the effects and purposes that can be produced by the present invention, should still fall within the scope of the technical contents disclosed by the present invention. At the same time, the terms such as the number of flow channels, the operation sequence, and the method cited in this embodiment are only for the purpose of description, and are not used to limit the scope of the implementation of the present invention. The changes or adjustments of the relative number and position relationship, and the changes of the operation sequence, without substantially changing the technical contents, should also be regarded as the scope of the implementation of the present invention.

Claims

1. A flow guide device for cooling working fluid at turbine inlet, characterized in that: The invention comprises a body which is axially limited between a combustion chamber and a turbine, wherein the body has an annular cavity inside, wherein at least one working medium flow channel for guiding working medium from the combustion chamber to the turbine is arranged inside the annular cavity, wherein the working medium flow channel comprises at least a tapered section where guide plates on both sides gradually approach each other, and the guide plates on both sides are fixedly connected to the inner and outer surfaces of the annular cavity; The working medium flow channel is arranged in a spiral shape, the speed direction of the working medium leaving the flow guide device is consistent with the direction of the turbine inlet flow channel, the interior of the working medium flow channel has a natural transition and the outlet direction of the working medium flow channel is consistent with the turbine inlet direction; The working fluid flow channel also includes an outlet section connected to the turbine inlet, the working fluid flow channel formed by the tapered section and the outlet section is a tapered flow channel or a convergent flow channel as a whole, the outlet section of the convergent flow channel includes two diffuser plates matched with the ends of the two guide plates, at least one side of the diffuser plate is bent toward the outside of the working fluid flow channel to expand the working fluid flow area; It also includes an adjustment ring cavity that is coaxially matched with the end of the body and can rotate relative to the body; the axial size of the adjustment ring cavity is consistent with the inner cavity of the annular cavity; the adjustment ring cavity can rotate to switch the working medium flow channel in the guide device between a gradually contracting flow channel and a zooming flow channel.

2. A flow guide device for cooling working medium at turbine inlet according to claim 1, characterized in that: The cavity of the adjustment ring cavity is provided with a tapered outlet and a zoom outlet that can be connected with the end of the tapered section in the annular cavity. The tapered outlet includes two guide plates that are connected with the end of the guide plate and gradually approach each other; the zoom outlet includes two expansion plates; the tapered outlet and the zoom outlet are arranged in the cavity of the adjustment ring cavity at intervals along the circumferential direction.

3. A flow guide device for cooling working medium at turbine inlet according to claim 2, characterized in that: An optical axis with a radius smaller than the inner diameter of the annular cavity is coaxially arranged at the end of the body, the adjustment ring cavity is sleeved on the optical axis, and the end of the optical axis is locked by a nut with a diameter not larger than the outer diameter of the inner layer of the adjustment ring cavity; the front end of the adjustment ring cavity is in close contact with the end face of the end of the annular cavity and is freely matched circumferentially; the end of the adjustment ring cavity is in close contact with the turbine inlet axially and is freely matched circumferentially.

4. A flow guide device for cooling working medium at turbine inlet according to claim 3, characterized in that: It also includes a driving mechanism fixedly matched with the outer surface of the adjustment ring cavity, the driving mechanism includes a flange plate penetrating the outer periphery of the adjustment ring cavity, the flange plate is provided with a locking piece fixedly matched with the outer surface of the adjustment ring cavity, the locking piece fixes the adjustment ring cavity and the flange plate in the circumferential direction, and the flange plate can rotate inside the gas turbine.

5. A flow guide device for cooling working medium at turbine inlet according to claim 4, characterized in that: The driving mechanism also includes a fixing plate which is arranged at least on two symmetrical sides of the center of the flange and fixedly matched with the inside of the gas turbine; the flange and the fixing plate are respectively provided with a pin shaft and an arc groove which match each other, the arc groove is concentric with the flange, the pin shaft is axially penetrated and fixed in the arc groove, and the pin shaft can slide freely in the arc groove.

6. A flow guide device for cooling working medium at turbine inlet according to claim 5, characterized in that: The fixing plate is also provided with a cylinder, and the cylinder seat and the cylinder rod are respectively hingedly matched with the fixing plate and the flange, and the hinge axes are parallel to the axial direction of the flange.

7. A flow guide device for cooling working medium at turbine inlet according to claim 4, characterized in that: The locking member includes a connecting rod and a locking plate. The two ends of the connecting rod are respectively hingedly matched with the flange and the locking plate. The hinge axis points to the axis of the flange. A plurality of locking rods protrude radially from the outer periphery of the adjustment ring cavity. The locking plate is also hingedly matched with the locking rod.

Images