Turbine

Abstract

The present invention provides a turbine, comprising: a casing; a first airfoil body, arranged inside the casing; a first inner frame, coupled to the radial inner end of the first airfoil body; a first inner wing, protruding from the first inner frame along the axial direction of the casing; a second airfoil body, arranged inside the casing; a second inner frame, coupled to the radial inner end of the second airfoil body; a second inner wing, protruding from the second inner frame along the axial direction of the casing; and a plurality of protruding pins, arranged between the first inner wing and the second inner wing, for cooling air existing on the radial inner side of the first inner wing and the second inner wing to flow in through an inlet and pass through and then be discharged through an outlet, a downstream area of ​​the first airfoil body is divided into a first area and a second area, a first flow path and a second flow path are formed between the plurality of protruding pins, a circumferential width of the first flow path increases from the inlet toward the outlet, and a circumferential width of the second flow path decreases from the inlet toward the outlet.

Description

Technical Field

[0001] The present invention relates to a turbine, and more particularly, to a turbine that generates power for generating electric power by passing high-temperature combustion gas or steam through the inside of the turbine. Background Art

[0002] A turbine is a device that generates power for generating electricity by using a fluid (especially gas) passing through the turbine. Therefore, a turbine is usually used together with a generator. The turbine may include a gas turbine (Gasturbine), a steam turbine (Steam turbine), a wind turbine (Wind power turbine), etc. A gas turbine is a device that mixes compressed air and natural gas and burns them to generate combustion gas, and uses the combustion gas generated in this way to generate power for generating electricity. A steam turbine is a device that generates power for generating electricity by using steam generated by heating water. A wind turbine is a device that converts wind power into power for generating electricity.

[0003] If we study the gas turbine in the turbine, the gas turbine includes a compressor, a combustor, and a turbine. The compressor is alternately provided with a plurality of compressor stators and compressor moving blades in the compressor housing. In addition, the compressor inhales external air through the compressor inlet scroll strut. The air inhaled in this way is compressed by the compressor stators and compressor moving blades in the process of passing through the compressor. The combustor receives the compressed air compressed in the compressor and mixes it with the fuel. In addition, the combustor ignites the fuel mixed with the compressed air with an igniter to generate high-temperature and high-pressure combustion gas. The combustion gas generated in this way is supplied to the turbine. The turbine is alternately provided with a plurality of turbine stators and turbine moving blades in the turbine housing. In addition, the turbine receives the combustion gas generated in the combustor and passes it through the inside. The combustion gas passing through the inside of the turbine rotates the turbine moving blades, and the combustion gas that has completely passed through the inside of the turbine is discharged to the outside through the turbine diffuser.

[0004] If we look at the steam turbine among turbines, the steam turbine includes an evaporator and a turbine. The evaporator heats water received from the outside to generate steam. The turbine has a plurality of turbine stators and turbine blades alternately arranged in a turbine housing, similar to the turbine in a gas turbine. However, the turbine in a steam turbine rotates the turbine blades by passing the steam generated in the evaporator instead of the combustion gas through the turbine.

[0005] On the other hand, the turbine includes a turbine stator and a turbine rotor arranged inside the turbine stator. The turbine stator includes: a turbine housing; turbine vanes, which are coupled to the inner circumferential surface of the turbine housing and arranged in multi-stage along the flow direction of the fluid and guide the fluid; and a U-ring, which is coupled to the inner end of the turbine vanes in the radial direction. The turbine rotor includes: a turbine disk, which is arranged inside the turbine housing; and multi-stage turbine blades, which are provided on the outer circumferential surface of the turbine disk and arranged between adjacent turbine vanes and rotated by the flow of the fluid.

[0006] A wheel-space is formed between adjacent U-rings and turbine disks, and cooling air is supplied to the wheel-space in order to cool the various components of the turbine heated by high-temperature fluid (combustion gas or steam). The cooling air supplied to the wheel-space cools the various components of the turbine while flowing radially outward (i.e., egress). Generally, using too much cooling air for turbine cooling reduces the efficiency of the entire turbine, while using too little cooling air may cause overheating and damage to various components of the turbine, so it is important to supply cooling air in an optimal amount.

[0007] At this time, according to the existing turbine, since a first area with a higher pressure than the above-mentioned wheelbase and a second area with a lower pressure than the above-mentioned wheelbase are formed in the downstream area of ​​the turbine stator blades or the downstream area of ​​the turbine moving blades, there is a problem that an ingress phenomenon occurs in which a high-temperature fluid flows into the wheelbase in the above-mentioned first area, and in the above-mentioned second area, excessive cooling air is output (Egress) from the wheelbase to the space where the above-mentioned turbine stator blades and turbine moving blades are located. Summary of the invention

[0008] The present invention is developed to solve the above-mentioned problems, and its purpose is to provide a turbine that prevents the ingress phenomenon of high-temperature fluid flowing into the wheelbase from the radially outer side, and controls the amount of cooling air discharged from the wheelbase to the radially outer side (i.e., egress) to be optimal.

[0009] The present invention provides a turbine, which includes: a casing; a first airfoil body, which is arranged inside the casing and allows fluid flowing inside the casing to pass through; a first inner frame, which is connected to the radial inner end of the first airfoil body; a first inner wing, which protrudes from the first inner frame along the axial direction of the casing; a second airfoil body, which is arranged inside the casing and is arranged between the first airfoil body and the first airfoil body adjacent to each other along the flow direction of the fluid; the second inner frame, which is connected to the radial inner end of the second airfoil body and is arranged adjacent to the first inner frame; the second inner wing, which protrudes from the second inner frame along the axial direction of the casing and is arranged adjacent to the first inner wing; and a plurality of protruding pins, which are arranged on the first inner frame. The cooling air existing on the radial inner side of the first inner wing and the second inner wing flows in through the inlet and is discharged to the radial outer side through the outlet after passing through. The downstream area of ​​the first airfoil body based on the flow direction of the fluid flowing inside the shell is divided into a first area and a second area. The pressure of the second area is lower than that of the first area. A first flow path and a second flow path are formed between the plurality of protruding pins. The circumferential width of the first flow path increases from the inlet toward the outlet, and the outlet is connected to the first area. The circumferential width of the second flow path decreases from the inlet toward the outlet, and the outlet is connected to the second area.

[0010] The first region may correspond to a downstream region of a trailing edge of the first airfoil, and the second region may correspond to a downstream region of a flow path between a pressure side and a suction side of the first airfoil.

[0011] The first airfoil body may be coupled to the inner circumferential surface of the shell and direct the fluid flowing inside the shell toward the second airfoil body side, and the second airfoil body may be configured to be separated from the inner circumferential surface of the shell toward the inside in the radial direction and rotated by the fluid flowing inside the shell.

[0012] The second airfoil body may be coupled to the inner circumferential surface of the shell and guide the fluid flowing inside the shell toward the first airfoil body side, and the first airfoil body may be configured to separate from the inner circumferential surface of the shell toward the inner side in the radial direction and rotated by the fluid flowing inside the shell.

[0013] The first inner wing and the second inner wing may be arranged alternately along a radial direction of the housing, and the plurality of protruding pins may be provided on a surface of the first inner wing that is opposite to the second inner wing.

[0014] The first inner wing and the second inner wing may be arranged alternately along a radial direction of the housing, and the plurality of protruding pins may be provided on a surface of the second inner wing that is opposite to the first inner wing.

[0015] The multiple protruding pins may include: a first protruding pin; a second protruding pin, configured to be separated from the first protruding pin along a circumferential direction, and configured to be inclined toward the first protruding pin as it moves from the inlet toward the outlet, thereby forming the second flow path between the second protruding pin and the first protruding pin; and a third protruding pin, configured to be separated from the second protruding pin along a direction in which the second protruding pin separates from the first protruding pin, and forming the first flow path between the third protruding pin and the second protruding pin.

[0016] The thickness of the first to third protruding pins in the circumferential direction may be smaller than the width of the first and second flow paths in the circumferential direction.

[0017] The first protruding pin and the third protruding pin may be aligned along the axial direction of the housing.

[0018] The first protruding pin and the third protruding pin may be arranged to be inclined along a rotation direction of a wheel arranged inside the housing with reference to an axial direction of the housing as they go from the inlet toward the outlet.

[0019] In addition, the present invention provides a turbine, which includes: a casing; a first airfoil body, arranged inside the casing, for passage of fluid flowing inside the casing; a first inner frame, coupled to the radial inner end of the first airfoil body; a first inner wing, protruding from the first inner frame along the axial direction of the casing; a second airfoil body, arranged inside the casing, and arranged between the first airfoil body and the first airfoil body adjacent to each other along the flow direction of the fluid; the second inner frame, coupled to the radial inner end of the second airfoil body, and arranged adjacent to the first inner frame; the second inner wing, protruding from the second inner frame along the axial direction of the casing, and arranged adjacent to the first inner wing; and a plurality of protruding pins, arranged between the first inner wing and the second inner wing, and arranged along the circumference of the casing. The first inner wing and the second inner wing are separated from each other in direction, and cooling air existing on the radial inner side of the first inner wing and the second inner wing flows in through the inlet and is discharged to the radial outer side through the outlet after passing through. The downstream side area of ​​the first airfoil body based on the flow direction of the fluid flowing inside the shell is divided into a first area and a second area. The pressure of the second area is lower than that of the first area. A first flow path and a second flow path are formed between the first inner wing and the second inner wing. The first flow path is connected to the first area. The second flow path is configured to be adjacent to the first flow path along the circumferential direction of the shell and connected to the second area. The multiple protruding pins are respectively configured on the multiple second flow paths, and are configured to be opposite to the second area, and block the second flow path to prevent the cooling air flowing into the inlet from flowing to the second area.

[0020] The first region may correspond to a downstream region of a trailing edge of the first airfoil, and the second region may correspond to a downstream region of a flow path between a pressure side and a suction side of the first airfoil.

[0021] The first airfoil body may be coupled to the inner circumferential surface of the shell and direct the fluid flowing inside the shell toward the second airfoil body side, and the second airfoil body may be configured to be separated from the inner circumferential surface of the shell inwardly along the radial direction and rotated by the fluid flowing inside the shell.

[0022] The second airfoil body may be coupled to the inner circumferential surface of the shell and guide the fluid flowing inside the shell to the first airfoil body side, and the first airfoil body may be configured to be separated from the inner circumferential surface of the shell inwardly along the radial direction and rotated by the fluid flowing inside the shell.

[0023] The first inner wing and the second inner wing may be arranged alternately along a radial direction of the housing, and the plurality of protruding pins may be provided on a surface of the first inner wing that is opposite to the second inner wing.

[0024] The first inner wing and the second inner wing may be arranged alternately along a radial direction of the housing, and the plurality of protruding pins may be provided on a surface of the second inner wing that is opposite to the first inner wing.

[0025] The circumferential width of the plurality of protruding pins may be kept constant from the inlet toward the outlet.

[0026] The circumferential width of the plurality of protruding pins may increase from the inlet toward the outlet.

[0027] Any one of the plurality of protruding pins may be formed as a curved surface that is convex toward the adjacent other protruding pin as it moves from the inlet toward the outlet.

[0028] In addition, the present invention provides a turbine, which includes: a casing; a first airfoil body, arranged inside the casing, for fluid flowing inside the casing to pass through; a first inner frame, coupled to the radial inner end of the first airfoil body; a first inner wing, protruding from the first inner frame along the axial direction of the casing; a second airfoil body, arranged inside the casing, and arranged between the first airfoil body and the first airfoil body adjacent to each other along the flow direction of the fluid; the second inner frame, coupled to the radial inner end of the second airfoil body, and arranged to be adjacent to the first inner frame; the second inner wing, protruding from the second inner frame along the axial direction of the casing, and arranged to be adjacent to the first inner wing; and a plurality of protruding pins, arranged between the first inner wing and the second inner wing, and arranged to be separated from each other along the circumferential direction of the casing, for the first inner wing and the second inner wing to be provided in the semicircular space between the first inner wing and the second inner wing. The cooling air on the inner side in the radial direction flows in through the inlet and is discharged to the outer side in the radial direction through the outlet. The downstream area of ​​the first airfoil body is divided into a first area and a second area based on the flow direction of the fluid flowing inside the shell. The pressure of the second area is lower than that of the first area. A first flow path and a second flow path are formed between the first inner wing and the second inner wing. The first flow path is connected to the first area. The second flow path is configured to be adjacent to the first flow path along the circumferential direction of the shell and connected to the second area. The multiple protruding pins are respectively configured on the multiple second flow paths, and are configured to be opposite to the second area, and block the second flow path to prevent the cooling air flowing into the inlet from flowing to the second area. The multiple protruding pins are configured to be inclined along the rotation direction of the wheel disk based on the axial direction of the shell as they move from the inlet toward the outlet.

[0029] According to the turbine involved in the present invention, there are multiple protruding pins between the first inner wing and the second inner wing, and a first flow path and a second flow path are formed between the above-mentioned multiple protruding pins. The circumferential width of the above-mentioned first flow path increases from the inlet toward the outlet, and the outlet is connected to the above-mentioned first area. The circumferential width of the above-mentioned second flow path decreases from the inlet toward the outlet, and the outlet is connected to the above-mentioned second area, so that the static pressure (Static pressure) of the cooling air discharged to the outside in the radial direction through the above-mentioned first flow path can have a larger value than the static pressure of the cooling air discharged through the above-mentioned second flow path. Therefore, in addition to preventing the high-temperature fluid from being input (Ingress) from the above-mentioned first area into the above-mentioned first flow path, the amount of cooling air output (Egress) to the above-mentioned second area through the above-mentioned second flow path can also be adjusted to an optimal amount.

[0030] In addition, according to the turbine involved in the present invention, a first flow path connected to the first area and a second flow path arranged to be adjacent to the first flow path along the circumferential direction of the above-mentioned shell and connected to the second area are formed between the first inner wing and the second inner wing, and a plurality of protruding pins are respectively arranged on the above-mentioned plurality of second flow paths and arranged to be opposite to the above-mentioned second area, and block the above-mentioned second flow paths to prevent the cooling air flowing into the inlet from flowing to the above-mentioned second area, so that the cooling air supplied to the wheelbase can be concentrated only on the above-mentioned first flow path and discharged to the above-mentioned first area, thereby preventing the high-pressure fluid existing in the first area from being input (Ingress) into the wheelbase. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a partially cutaway perspective view showing the interior of a turbine included in the turbine.

[0032] Figure 2 It is shown Figure 1 A three-dimensional diagram of the input (Ingress) and output (Egress) phenomena generated in .

[0033] Figure 3 It is shown in Figure 1 and Figure 2 A diagram showing the appearance of multiple protruding pins arranged between the first inner wing and the second inner wing.

[0034] Figure 4 As Figure 3 The top view of the plurality of protruding pins shown is a diagram showing the first embodiment of the present invention.

[0035] Figure 5 It is a diagram showing a second embodiment of the present invention.

[0036] Figure 6It is a diagram showing a third embodiment of the present invention.

[0037] Figure 7 It is a diagram showing a fourth embodiment of the present invention.

[0038] Figure 8 It is a diagram showing a fifth embodiment of the present invention. DETAILED DESCRIPTION

[0039] The present invention is described with reference to the embodiments shown in the accompanying drawings, but this is only illustrative, and those skilled in the art will understand various modifications and other equivalent embodiments based on this. Therefore, the true technical protection scope of the present invention should be determined based on the technical ideas of the attached claims.

[0040] Reference Figures 1 to 8 The turbine 100 according to the present invention includes a casing 110, a first airfoil 120, a first inner frame 121, a first inner wing 122, a second airfoil 130, a second inner frame 131, a second inner wing 132, a wheel 140 and a plurality of rim seals 10, 20, 30, 40, 50.

[0041] On the other hand, with reference to the figure, the radial direction of the shell 110 is represented by R, the circumferential direction of the shell 110 is represented by C, the length direction of the imaginary axis passing through the center of the shell 110 (i.e., the axial direction of the shell 110) is represented by X, the flow direction of the high-temperature fluid (combustion gas or steam) flowing inside the shell 110 is represented by D1, and the rotation direction of the wheel 140 is represented by D2. Among them, the flow direction D1 of the high-temperature fluid is included in the axial direction X, which is equivalent to any one of the axial directions X. Furthermore, the flow direction D1 of the high-temperature fluid is Figures 4 to 8 The cooling air flowing through the plurality of protruding pins 10, 20, 30, 40, 50 has the same flow direction. In addition, the rotation direction D2 of the wheel 140 is included in the circumferential direction C and corresponds to one of the circumferential directions C.

[0042] Reference Figures 1 to 3 The shell 110 is formed into a hollow shape and contains the first airfoil 120, the first inner frame 121, the first inner wing 122, the second airfoil 130, the second inner frame 131, the second inner wing 132 and a plurality of rim seals 10 therein.

[0043] The first airfoil body 120 is accommodated inside the housing 110 and is arranged in multi-stage along the axial direction X, and a high-temperature fluid passes through. The first inner frame 121 is coupled to the inner end of the first airfoil body 120 in the radial direction R. The first inner wing 122 protrudes from the first inner frame 121 along the axial direction X.

[0044] The second airfoil body 130 is accommodated inside the housing 110 and is arranged in multi-stage along the axial direction X, and is arranged between the first airfoil bodies 120, and a high-temperature fluid passes through. The second inner frame 131 is coupled to the inner end of the second airfoil body 130 in the radial direction R, and is arranged adjacent to the first inner frame 121. The second inner wing 132 protrudes from the second inner frame 131 along the axial direction X, and is arranged adjacent to the first inner wing 122.

[0045] The plurality of protruding pins 10, 20, 30, 40, 50 are disposed between the first inner wing 122 and the second inner wing 132, and are disposed to be separated from each other along the circumferential direction C. In addition, in the plurality of protruding pins 10, 20, 30, 40, 50, cooling air existing in the wheelbase 111 on the inner side in the radial direction R of the first inner wing 122 and the second inner wing 132 flows in through the inlet 10c and passes through, and is then discharged to the outer side in the radial direction R through the outlet 10d.

[0046] Reference Figure 2 The downstream area of ​​the first airfoil body 120 based on the flow direction D1 of the fluid is divided into a first area showing high pressure and a second area showing low pressure. For ease of explanation, in the figure, the first area is represented as + and the second area is represented as -.

[0047] The first region + corresponds to the downstream region of the trailing edge of the first airfoil 120, and is distributed to be separated from each other along the circumferential direction C. The second region - corresponds to each downstream region of the flow path between the pressure side and the suction side of the first airfoil, and is distributed along the circumferential direction C between the first region +.

[0048] When the turbine 100 is a turbine included in a gas turbine or a steam turbine, the casing 110 is a turbine casing, the first airfoil body 120 is equivalent to one of a turbine stator blade and a turbine rotor blade, and the second airfoil body 130 is equivalent to the other.

[0049] [Example 1] For example, refer to Figure 3 When the first airfoil body 120 is a turbine stator blade coupled to the inner circumference of the housing 110 and guiding the high-temperature fluid to the downstream side, and the second airfoil body 130 is a turbine moving blade configured to be separated from the inner circumference of the housing 110 and rotated as the high-temperature fluid passes through, the first inner frame 121 is equivalent to a U-ring coupled to the inner end of the turbine stator blade in the radial direction R, and the second inner frame 131 is equivalent to a platform. In addition, the second inner frame 131 is coupled to the outer circumference of the wheel disc 140 disposed inside the housing 110, and the second airfoil body 130 is provided on the outer circumference of the second inner frame 131.

[0050] [Example 2] On the contrary, although not shown in the figure, when the first airfoil body 120 is a turbine moving blade that is separated from the inner peripheral surface of the housing 110 and rotates as the high-temperature fluid passes through, and the second airfoil body 130 is a turbine stator that is coupled to the inner peripheral surface of the housing 110 and guides the high-temperature fluid to the downstream side, the second inner frame 131 is equivalent to a U-ring coupled to the inner end of the turbine stator in the radial direction R, and the first inner frame 121 is equivalent to a platform. In addition, the first inner frame 121 is coupled to the outer peripheral surface of the wheel disc 140 disposed inside the housing 110, and the first airfoil body 120 is provided on the outer peripheral surface of the first inner frame 121.

[0051] Although in Figure 3 Only the above-mentioned Example 1 is illustrated in the figure, but it is only an example, and in the present invention, the above-mentioned Example 2 can also be implemented. Figure 3 In the figure, it is shown that the turbine stator blade 120 is combined with the inner circumferential surface of the turbine housing 110, the U-ring 121 is combined with the inner side of the turbine stator blade 120 in the radial direction R, and the downstream side of the turbine stator blade 120 is provided with a turbine moving blade 130, a platform 131 and a wheel disc 140, and the above-mentioned multiple protruding pins 10, 20, 30, 40, 50 are located on the downstream side of the above-mentioned turbine stator blade 120, but this is just an example. Of course, the present invention can also be implemented as follows: the above-mentioned turbine stator blade 120 and U-ring 121 are provided on the downstream side of the above-mentioned turbine moving blade 130, platform 131 and wheel disc 140, and the above-mentioned multiple protruding pins 10, 20, 30, 40, 50 are located on the downstream side of the above-mentioned turbine moving blade 130.

[0052] In other words, assuming that the turbine is equivalent to a turbine in a gas turbine or a steam turbine, and when the turbine stators and turbine moving blades inside the turbine casing are alternately arranged in multiple stages, the above-mentioned multiple protruding pins 10, 20, 30, 40, 50 can be provided between the downstream side of the turbine stators and the upstream side of the turbine moving blades, in addition to being provided between the downstream side of the turbine stators and the upstream side of the turbine moving blades.

[0053] Refer again Figure 1 and Figure 2 , the first inner wing 122 and the second inner wing 132 may be arranged alternately with each other along the radial direction R. Figure 3 Although the figure shows a case where the first inner wing 122 is arranged on the outer side of the second inner wing 132 in the radial direction R, this is only an example, and the first inner wing 122 may also be arranged on the inner side of the second inner wing 132 in the radial direction R.

[0054] Reference Figure 3 , the plurality of protruding pins 10, 20, 30, 40, 50 may be provided on the opposite surface of the first inner wing 122 to the second inner wing 132. However, this is only an example, and although not shown in the figure, the plurality of protruding pins 10, 20, 30, 40, 50 may also be provided on the opposite surface of the second inner wing 132 to the first inner wing 122.

[0055] Reference Figure 4 and Figure 5 In the first and second embodiments of the present invention, a plurality of first flow paths 10a and a plurality of second flow paths 10b are formed between the plurality of protruding pins 10 and 20. The plurality of first flow paths 10a and the plurality of second flow paths 10b are alternately arranged along the circumferential direction C. The first flow path 10a is formed in a shape in which the width in the circumferential direction C gradually increases from the inlet 10c toward the outlet 10d, and is connected to the first region +. The second flow path 10b is formed in a shape in which the width in the circumferential direction C gradually decreases from the inlet 10c toward the outlet 10d, and is connected to the second region -.

[0056] The plurality of protruding pins 10 and 20 include a first protruding pin 11, a second protruding pin 12, and a third protruding pin 13. The first protruding pin 11 and the third protruding pin 13 are arranged to be separated from each other along the circumferential direction C. The second protruding pin 12 is arranged between the first protruding pin 11 and the third protruding pin 13, and is arranged in a manner inclined toward the first protruding pin 11 from the inlet 10c toward the outlet 10d. In addition, the first flow path 10a is formed between the second protruding pin 12 and the third protruding pin 13, and the second flow path 10b is formed between the second protruding pin 12 and the first protruding pin 11.

[0057] Thus, a first flow path 10a connected to the first area + and a second flow path 10b connected to the second area - are formed between the multiple protruding pins 10, 20. The first flow path 10a is formed in a diffuser shape whose width in the circumferential direction C gradually increases from the inlet 10c toward the outlet 10d, and the second flow path 10b is formed in a nozzle shape whose width in the circumferential direction C gradually decreases from the inlet 10c toward the outlet 10d, so that the static pressure on the outlet 10d side of the first flow path 10a can be further increased compared with the static pressure on the outlet 10d side of the second flow path 10b.

[0058] Therefore, the static pressure on the outlet 10d side of the first flow path 10a is higher than that of the prior art, so the high-temperature fluid existing in the first region + cannot flow into the first flow path 10a side through the outlet 10d of the first flow path 10a, thereby preventing the ingress phenomenon that occurs in the conventional turbine. In addition, since the static pressure on the outlet 10d side of the second flow path 10b is lower than that of the prior art, it is possible to prevent the cooling air from being excessively output (Egress) to the second region - through the second flow path 10b.

[0059] Reference Figure 4 and Figure 5 According to the first and second embodiments of the present invention, the thickness of each of the plurality of protruding pins 10 and 20 in the circumferential direction C is smaller than the width of the first flow path 10a and the second flow path 10b in the circumferential direction C. That is, the plurality of protruding pins 10 and 20 may be formed so that the thickness of each of the plurality of protruding pins 10 and 20 in the circumferential direction C is smaller than any of the widths of the first flow path 10a and the second flow path 10b in the circumferential direction C from the inlet 10c to the outlet 10d.

[0060] Reference Figure 4 In the plurality of protruding pins 10 according to the first embodiment of the present invention, the first protruding pin 11 and the third protruding pin 13 may be arranged to be parallel to each other and aligned along the axial direction X. Furthermore, the second protruding pin 12 may be arranged to be inclined along the circumferential direction C with the axial direction X as a reference as it moves from the inlet 10c toward the outlet 10d.

[0061] Reference Figure 5In the plurality of protruding pins 20 according to the second embodiment of the present invention, the first protruding pin 11 and the third protruding pin 13 may be configured to be inclined along the rotation direction D2 of the wheel disc 140 with the axial direction X as the reference as they move from the inlet 10c toward the outlet 10d. Furthermore, the second protruding pin 12 may be configured to be inclined along the rotation direction D2 of the wheel disc with the axial direction X as the reference as they move from the inlet 10c toward the outlet 10d. At this time, the second protruding pin 12 has a greater degree of inclination with the axial direction X as the reference than the first protruding pin 11 and the third protruding pin 13. In this case, the velocity vector in the circumferential direction C can be increased to the flow of the cooling air flowing along the first flow path 10a and the second flow path 10b, thereby improving the performance of the plurality of protruding pins 20.

[0062] Reference Figures 6 to 8 According to the third to fifth embodiments of the present invention, the plurality of protruding pins 30, 40, 50 are configured to completely close the outlet 10d of the second flow path 10b described in detail in the first and second embodiments of the present invention. Specifically, the plurality of protruding pins 30, 40, 50 are respectively arranged on the second flow path 10b and arranged so that the downstream end faces the second region-, and block the second flow path 10b to prevent the cooling air flowing into the inlet 10c from flowing toward the second region-.

[0063] In this case, the cooling air flowing from the wheelbase 111 into the inlet 10c of the plurality of protruding pins 30, 40, 50 is all concentrated in the first flow path 10a and discharged to the first region +. Therefore, according to the third to fifth embodiments of the present invention, the static pressure on the outlet 10d side of the first flow path 10a is significantly increased compared with the prior art, and the high-temperature air existing in the first region + can be prevented from flowing in through the outlet 10d of the first flow path 10a from the source.

[0064] Reference Figure 6 According to the third embodiment of the present invention, the plurality of protruding pins 30 are formed so that the width of the circumferential direction C remains constant from the inlet 10c toward the outlet 10d. Also, the plurality of protruding pins 30 are arranged parallel to each other and are arranged to be separated along the circumferential direction C at the same interval.

[0065] Reference Figure 7According to the fourth embodiment of the present invention, the plurality of protruding pins 40 are respectively formed into a shape in which the width in the circumferential direction C increases from the inlet 10c toward the outlet 10d. Furthermore, any one of the plurality of protruding pins 40 is formed into a curved surface that bulges toward the other adjacent protruding pins 40 in a curvature manner as it moves from the inlet 10c toward the outlet 10d. In this case, the cooling air flowing into the inlet 10c side of the plurality of protruding pins 40 can be gently guided along the respective opposite surfaces of the plurality of protruding pins 40 to move toward the outlet 10d side of the plurality of protruding pins 40, and the pressure loss that may be generated due to the cooling air flowing in the first flow path 10a can be minimized.

[0066] Reference Figure 8 According to the fifth embodiment of the present invention, the plurality of protruding pins 50 may be arranged to be inclined along the rotation direction D2 of the wheel 140 with reference to the axial direction X as the direction from the inlet 10c toward the outlet 10d. In this case, the velocity vector in the circumferential direction C can be added to the flow of the cooling air flowing along the first flow path 10a, thereby improving the performance of the plurality of protruding pins 50.

[0067] As shown in the above research, the turbine 100 according to the first to fifth embodiments of the present invention has protruding pins 10, 20, 30, 40, 50 of various shapes, which not only prevents the high-temperature fluid from being input (Ingress) from the above-mentioned first area + to the wheelbase 111 side, but also reduces or reduces the amount of cooling air discharged to the second area - and controls the amount of cooling air output (Egress) to be optimal according to the implementer's purpose.

[0068] On the other hand, the shapes of the plurality of protruding pins 10, 20, 30, 40, 50 mentioned above are merely illustrative, and the plurality of protruding pins 10, 20, 30, 40, 50 may obviously also be designed into other shapes not shown in the drawings.

[0069] Description of Reference Numerals

[0070] 100: Turbine 110: Housing

[0071] 120: first airfoil body 121: first inner frame

[0072] 122: first inner wing 130: second airfoil body

[0073] 131: Second inner frame 132: Second inner wing

[0074] +: First area -: Second area

[0075] 10, 20, 30, 40, 50: Protruding pin

[0076] 10a: First flow path 10b: Second flow path

[0077] 10c: Entrance 10d: Exit.

Claims

1. A turbine, wherein: Include: case; A first airfoil body is disposed inside the shell and is used for passage of fluid flowing inside the shell; a first inner frame, coupled to the radial inner end of the first airfoil body; a first inner wing protruding from the first inner frame along the axial direction of the housing; A second airfoil body is disposed inside the housing and between the first airfoil body and the second airfoil body adjacent to each other along a flow direction of the fluid; a second inner frame coupled to a radially inner end of the second airfoil body and arranged adjacent to the first inner frame; a second inner wing protruding from the second inner frame along the axial direction of the housing and arranged adjacent to the first inner wing; as well as A plurality of protruding pins are arranged between the first inner wing and the second inner wing and are arranged to be separated from each other along the circumferential direction of the housing, so that cooling air existing on the radial inner side of the first inner wing and the second inner wing can flow in through the inlet and pass through the outlet to be discharged to the radial outer side. A downstream area of ​​the first airfoil body based on a flow direction of the fluid flowing inside the casing is divided into a first area and a second area, and a pressure in the second area is lower than that in the first area. A first flow path and a second flow path are formed between the plurality of protruding pins, wherein the circumferential width of the first flow path increases from the inlet toward the outlet, and the outlet of the first flow path communicates with the first region, and the circumferential width of the second flow path decreases from the inlet toward the outlet, and the outlet of the second flow path communicates with the second region, in, The first region corresponds to a downstream region of the trailing edge of the first airfoil body, The second region corresponds to a downstream region of a flow path between the pressure side and the suction side of the first airfoil body.

2. The turbine according to claim 1, wherein: The first airfoil body is coupled to the inner circumferential surface of the shell and guides the fluid flowing inside the shell to the second airfoil body side. The second airfoil body is disposed so as to be separated from the inner peripheral surface of the casing toward the inner side in the radial direction, and is rotated by the fluid flowing inside the casing.

3. The turbine according to claim 1, wherein: The second airfoil body is coupled to the inner circumferential surface of the shell and guides the fluid flowing inside the shell to the first airfoil body side. The first airfoil body is disposed so as to be separated from the inner peripheral surface of the casing toward the inner side in the radial direction, and is rotated by the fluid flowing inside the casing.

4. The turbine according to claim 1, wherein: The first inner wings and the second inner wings are arranged to alternate with each other along the radial direction of the shell, The plurality of protruding pins are provided on an opposing surface of the first inner wing that is opposed to the second inner wing.

5. The turbine according to claim 1, wherein: The first inner wings and the second inner wings are arranged to alternate with each other along the radial direction of the shell, The plurality of protruding pins are provided on an opposing surface of the second inner wing that is opposite to the first inner wing.

6. The turbine according to claim 1, wherein: The plurality of protruding pins include: a first protruding pin; a second protruding pin arranged to be separated from the first protruding pin in the circumferential direction and arranged to be inclined toward the first protruding pin as it moves from the inlet toward the outlet, so that the second flow path is formed between the second protruding pin and the first protruding pin; and The third protruding pin is arranged to be separated from the second protruding pin in a direction in which the second protruding pin is separated from the first protruding pin, and the first flow path is formed between the third protruding pin and the second protruding pin.

7. The turbine according to claim 6, wherein: The thickness of the first to third protruding pins in the circumferential direction is smaller than the width of the first and second flow paths in the circumferential direction.

8. The turbine according to claim 6, wherein: The first protruding pin and the third protruding pin are aligned along an axial direction of the housing.

9. The turbine according to claim 6, wherein: The first protruding pin and the third protruding pin are arranged so as to be inclined along the rotation direction of the wheel arranged inside the housing with reference to the axial direction of the housing as they go from the inlet toward the outlet.

10. A turbine, wherein: Include: case; A first airfoil body is disposed inside the shell and is used for passage of fluid flowing inside the shell; a first inner frame, coupled to the radial inner end of the first airfoil body; a first inner wing protruding from the first inner frame along the axial direction of the housing; A second airfoil body is disposed inside the housing and between the first airfoil body and the second airfoil body adjacent to each other along a flow direction of the fluid; a second inner frame coupled to a radially inner end portion of the second airfoil body and arranged adjacent to the first inner frame; a second inner wing protruding from the second inner frame along the axial direction of the housing and arranged adjacent to the first inner wing; as well as A plurality of protruding pins are arranged between the first inner wing and the second inner wing and are arranged to be separated from each other along the circumferential direction of the housing, so that cooling air existing on the radial inner side of the first inner wing and the second inner wing can flow in through the inlet and pass through the outlet to be discharged to the radial outer side. A downstream area of ​​the first airfoil body based on a flow direction of the fluid flowing inside the casing is divided into a first area and a second area, and a pressure in the second area is lower than that in the first area. A first flow path and a second flow path are formed between the first inner wing and the second inner wing, the first flow path is connected to the first region, and the second flow path is arranged adjacent to the first flow path along the circumferential direction of the shell and connected to the second region. The plurality of protruding pins are respectively arranged on the plurality of second flow paths, and are arranged to face the second region, and block the second flow path to prevent the cooling air flowing into the inlet from flowing into the second region. in, The first region corresponds to a downstream region of the trailing edge of the first airfoil body, The second region corresponds to a downstream region of a flow path between the pressure side and the suction side of the first airfoil body.

11. The turbine according to claim 10, wherein: The first airfoil body is coupled to the inner circumferential surface of the shell and guides the fluid flowing inside the shell to the second airfoil body side. The second airfoil body is disposed so as to be separated from the inner peripheral surface of the casing toward the inner side in the radial direction, and is rotated by the fluid flowing inside the casing.

12. The turbine according to claim 10, wherein: The second airfoil body is coupled to the inner circumferential surface of the shell and guides the fluid flowing inside the shell to the first airfoil body side. The first airfoil body is disposed so as to be separated from the inner peripheral surface of the casing toward the inner side in the radial direction, and is rotated by the fluid flowing inside the casing.

13. The turbine according to claim 10, wherein: The first inner wings and the second inner wings are arranged to alternate with each other along the radial direction of the shell, The plurality of protruding pins are provided on an opposing surface of the first inner wing that is opposed to the second inner wing.

14. The turbine according to claim 10, wherein: The first inner wings and the second inner wings are arranged to alternate with each other along the radial direction of the shell, The plurality of protruding pins are provided on an opposing surface of the second inner wing that is opposite to the first inner wing.

15. The turbine according to claim 10, wherein: The circumferential width of the plurality of protruding pins is kept constant from the inlet toward the outlet.

16. The turbine according to claim 10, wherein: The circumferential width of the plurality of protruding pins increases from the inlet toward the outlet.

17. The turbine according to claim 16, wherein: Any one of the plurality of protruding pins is formed as a curved surface that is convex toward the adjacent other protruding pin as it moves from the inlet toward the outlet.

18. A turbine, wherein: Include: case; A first airfoil body is disposed inside the shell and is used for passage of fluid flowing inside the shell; a first inner frame, coupled to the radial inner end of the first airfoil body; a first inner wing protruding from the first inner frame along the axial direction of the housing; A second airfoil body is disposed inside the housing and between the first airfoil body and the second airfoil body adjacent to each other along a flow direction of the fluid; a second inner frame coupled to a radially inner end of the second airfoil body and arranged adjacent to the first inner frame; a second inner wing protruding from the second inner frame along the axial direction of the housing and arranged adjacent to the first inner wing; as well as A plurality of protruding pins are arranged between the first inner wing and the second inner wing and are arranged to be separated from each other along the circumferential direction of the housing, so that cooling air existing on the radial inner side of the first inner wing and the second inner wing can flow in through the inlet and pass through the outlet to be discharged to the radial outer side. A downstream area of ​​the first airfoil body based on a flow direction of the fluid flowing inside the casing is divided into a first area and a second area, and a pressure in the second area is lower than that in the first area. A first flow path and a second flow path are formed between the first inner wing and the second inner wing, the first flow path is connected to the first region, and the second flow path is arranged adjacent to the first flow path along the circumferential direction of the shell and connected to the second region. The plurality of protruding pins are respectively arranged on the plurality of second flow paths, and are arranged to face the second region, and block the second flow path to prevent the cooling air flowing into the inlet from flowing into the second region. The plurality of protruding pins are arranged so as to be inclined along the rotation direction of the wheel arranged inside the housing with reference to the axial direction of the housing as they go from the inlet toward the outlet. in, The first region corresponds to a downstream region of the trailing edge of the first airfoil body, The second region corresponds to a downstream region of a flow path between the pressure side and the suction side of the first airfoil body.

Images