KR102010660B1 - Gas turbine - Google Patents

Abstract

The present invention relates to a gas turbine, comprising: a housing; A rotor rotatably provided in the housing; A compressor compressing air by receiving rotational force from the rotor; A combustor that mixes and ignites fuel with compressed air in the compressor to produce combustion gas; And a turbine which rotates the rotor by obtaining a rotational force from the combustion gas generated by the combustor, wherein the turbine comprises: a turbine blade rotated together with the rotor; And a turbine vane fixedly installed in the housing to align the flow of the combustion gas flowing into the turbine blade, wherein the turbine vane is formed with a turbine vane cooling passage through which a cooling fluid for cooling the turbine vane passes. The turbine vane cooling passage may be formed with a guide vane for redirecting the flow direction of the cooling fluid. As a result, it is possible to prevent the temperature gradient and the thermal stress from occurring in the turbine vane cooled by the cooling fluid.

Description

Gas Turbine {GAS TURBINE}

The present invention relates to a gas turbine.

In general, a turbine is a machine that converts the energy of a fluid such as water, gas, steam, etc. into mechanical work, usually by planting several feathers or vanes on the circumference of a rotating body and exhaling steam or gas thereon to produce high-speed impulse or reaction force. A turbo-type machine that rotates is called a turbine.

Such turbine types include a hydro turbine using energy of high water, a steam turbine using energy of steam, an air turbine using energy of high pressure compressed air, and a gas using energy of high temperature and high pressure gas. Turbine and the like.

Among these, the gas turbine includes a compressor, a combustor, a turbine, and a rotor.

The compressor includes a plurality of compressor vanes and a plurality of compressor blades alternately arranged.

The combustor produces combustion gas of high temperature and high pressure by supplying fuel to the compressed air compressed in the compressor and igniting the burner.

The turbine includes a plurality of turbine vanes and a plurality of turbine blades alternately arranged.

The rotor is formed to penetrate the center of the compressor, the combustor and the turbine, both ends are rotatably supported by a bearing, one end is connected to the drive shaft of the generator.

The rotor includes a plurality of compressor rotor disks coupled to the compressor blades, a plurality of turbine rotor disks coupled to the turbine blades, and a torque tube for transmitting rotational force from the turbine rotor disks to the compressor rotor disks.

In the gas turbine according to this configuration, the air compressed in the compressor is mixed with fuel in the combustion chamber and combusted so as to be converted into a high temperature combustion gas, the combustion gas thus produced is injected to the turbine side, and the injected combustion gas is injected into the turbine blade. The rotating force is generated while passing through the rotor, and the rotor rotates.

Since the gas turbine does not have a reciprocating mechanism such as a piston in a four-stroke engine, there is no mutual friction portion such as a piston-cylinder, so the consumption of lubricating oil is extremely low, and the amplitude characteristic of the reciprocating machine is greatly reduced and high speed movement is possible. There is an advantage.

On the other hand, since the turbine is in contact with the combustion gas of high temperature and high pressure unlike the compressor, a cooling means for preventing damage such as deterioration is required, and for this purpose, the compressed air (cooling fluid) compressed at a part of the compressor is added to the Further comprising a cooling passage for supplying to the turbine, the cooling passage is in communication with the turbine vane cooling passage formed inside the turbine vane.

However, in such a conventional gas turbine, the turbine vanes are not cooled properly, and a temperature gradient occurs in the turbine vanes, thereby causing damage due to thermal stress. Specifically, referring to Korean Patent Laid-Open Publication No. 10-2006-0073428, in the conventional gas turbine, the turbine vane cooling flow path has air (cooling fluid) zigzag inside the turbine vane, and then the second turn 72. At the leading edge of the turbine vane through the third passage leg 76, the flow cross section of the third passage leg 76 of the second turn 72. It is formed to expand rapidly in relation to the flow cross-sectional area. As a result, most of the air (cooling fluid) that has passed through the second turn 72 is supplied only to one portion of the third passage leg 76 (a portion opposite to the second turn 72), and the third passage leg is provided. Other parts of 76 (parts not opposed to the second turn 72) are hardly supplied with air (cooling fluid). Accordingly, one portion of the second passage leg 76 is overcooled, the other portion of the second passage leg 76 is undercooled or not cooled, resulting in a temperature gradient at the trailing edge portion of the turbine vane, Thermal stresses are generated at the trailing edges of the turbine vanes and damage is generated at the trailing edges of the turbine vanes.

Republic of Korea Patent Application Publication No. 10-2006-0073428

Accordingly, an object of the present invention is to provide a gas turbine capable of preventing the temperature gradient and thermal stress from occurring in the turbine vane cooled by the cooling fluid.

The present invention, to achieve the object as described above, the housing; A rotor rotatably provided in the housing; A compressor compressing air by receiving rotational force from the rotor; A combustor that mixes and ignites fuel with compressed air in the compressor to produce combustion gas; And a turbine which rotates the rotor by obtaining a rotational force from the combustion gas generated by the combustor, wherein the turbine comprises: a turbine blade rotated together with the rotor; And a turbine vane fixedly installed in the housing to align the flow of the combustion gas flowing into the turbine blade, wherein the turbine vane is formed with a turbine vane cooling passage through which a cooling fluid for cooling the turbine vane passes. The turbine vane cooling passage provides a gas turbine in which guide vanes are formed to redirect the flow direction of the cooling fluid.

The turbine vane cooling passage may include an enlarged portion in which a flow cross section is enlarged, and the guide vane may be formed at an inlet side of the enlarged diameter portion.

The enlarged diameter portion, the inlet opposing portion facing the inlet of the enlarged diameter portion; And an inlet non-facing portion that does not face the inlet of the enlarged diameter portion, wherein the guide vane may be formed to guide a portion of the cooling fluid flowing into the inlet of the enlarged diameter portion toward the inlet non-facing portion side.

The guide vanes may be integrally formed.

The guide vanes may be formed to bisec the flow cross section at the position where the guide vanes are formed.

The guide vane is a distance from the guide vane to one side wall portion of the turbine vane cooling channel and the guide vane to the other wall portion of the turbine vane cooling channel in a direction crossing the inlet opposing portion and the non-inlet opposing portion. The distance of the same can be formed.

The guide vane may be formed to be inclined toward the inlet non-facing portion with respect to the flow direction of the cooling fluid flowing from the inlet of the enlarged diameter portion.

The guide vane may include a first guide vane; And a second guide vane located on a downstream side of the first guide vane.

Downstream of the first guide vane may include: a first guide vane first downstream positioned on the inlet opposing side relative to the first guide vane; And a first guide vane second downstream positioned on the side of the inlet non-facing portion with respect to the first guide vane. The second guide vane may be positioned downstream of the first guide vane first.

The first guide vane may be formed to bisec the flow cross-sectional area at the position where the first guide vane is formed.

The first guide vane is a distance from the first guide vane to one side wall portion of the turbine vane cooling flow path and the first guide vane from the first guide vane in a direction crossing the inlet opposing portion and the non-inlet opposing portion. The distance to the other wall portion of the cooling flow path may be equally formed.

The second guide vane may be formed to bisec the flow cross-sectional area at the position where the second guide vane is formed.

The second guide vane is a distance from the second guide vane to one side wall portion of the turbine vane cooling flow path and the first guide vane from the second guide vane in a direction crossing the inlet opposing portion and the non-inlet opposing portion. The distance to the guide vanes can be formed equally.

The first guide vane is formed to be inclined toward the inlet non-facing portion with respect to the flow direction of the cooling fluid flowing from the inlet of the enlarged diameter portion, the second guide vane is a cooling fluid introduced to the first downstream side of the first guide vane It may be formed to be inclined toward the inlet non-facing portion with respect to the flow direction of.

The first guide vane may be formed to be more inclined toward the inlet non-facing portion side than the second guide vane.

The first guide vane is formed to be inclined at an angle of 45 degrees toward the inlet non-facing portion relative to the flow direction of the cooling fluid flowing from the inlet of the enlarged diameter portion, and the second guide vane is introduced from the inlet of the enlarged diameter portion. It may be formed to be inclined at an angle of 30 degrees toward the inlet non-facing portion relative to the flow direction of the cooling fluid.

The turbine vane cooling flow path may include: a first turbine vane cooling flow path guiding cooling fluid introduced into the turbine vane cooling flow path from the blade root side of the turbine vane to the tip side of the turbine vane; A second turbine vane cooling flow path for redirecting a flow direction of the cooling fluid passing through the first turbine vane cooling flow path to the blade root side; A third turbine vane cooling channel configured to guide the cooling fluid passing through the second turbine vane cooling channel from the tip side to the blade side; A fourth turbine vane cooling channel configured to redirect a flow direction of the cooling fluid passing through the third turbine vane cooling channel to a trailing edge side of the turbine vane; And a fifth turbine vane cooling channel for distributing the cooling fluid passing through the fourth turbine vane cooling channel to the entire region of the trailing edge from the blade root side, wherein the guide vane is the fourth turbine vane cooling channel. And a boundary portion between the fifth turbine vane cooling channel.

The fifth turbine vane cooling channel may include: a first portion of the fifth turbine vane cooling channel located at the blade root side; And a fifth turbine vane cooling flow passage second portion located at the tip side, wherein the guide vane is configured to transfer a portion of the cooling fluid passing through the fourth turbine vane cooling flow passage to the fifth turbine vane cooling flow passage second portion. It can be formed to guide to the side.

The guide vanes may be formed in two or less, and each guide vane may be formed to bisect the flow rate of the cooling fluid flowing into the guide vanes.

On the other hand, the present invention, the housing; A rotor rotatably provided in the housing; A blade that rotates with the rotor; And a vane for aligning a flow of the fluid flowing into the blade, wherein the vane is provided with a cooling passage through which cooling fluid passes, and a guide vane for dispersing the cooling fluid is provided in the cooling passage. do.

Gas turbine according to the present invention, the housing; A rotor rotatably provided in the housing; A compressor compressing air by receiving rotational force from the rotor; A combustor that mixes and ignites fuel with compressed air in the compressor to produce combustion gas; And a turbine which rotates the rotor by obtaining a rotational force from the combustion gas generated by the combustor, wherein the turbine comprises: a turbine blade rotated together with the rotor; And a turbine vane fixedly installed in the housing to align the flow of the combustion gas flowing into the turbine blade, wherein the turbine vane is formed with a turbine vane cooling passage through which a cooling fluid for cooling the turbine vane passes. The turbine vane cooling passage may be formed with a guide vane for redirecting the flow direction of the cooling fluid. As a result, it is possible to prevent the temperature gradient and the thermal stress from occurring in the turbine vane cooled by the cooling fluid.

1 is a cross-sectional view showing a gas turbine according to an embodiment of the present invention;
FIG. 2 is a sectional view of the turbine vane in the gas turbine of FIG. 1;
3 is a cross-sectional view showing a turbine vane in a gas turbine according to another embodiment of the present invention.

Hereinafter, a gas turbine according to the present invention will be described in detail with reference to the accompanying drawings.

1 is a cross-sectional view showing a gas turbine according to an embodiment of the present invention, Figure 2 is a cross-sectional view showing a turbine vane in the gas turbine of FIG.

1 and 2, a gas turbine according to an embodiment of the present invention includes a housing 100, a rotor 600 rotatably provided inside the housing 100, and the rotor 600. Compressor 200 for receiving the rotational force from the compressor to compress the air flowing into the housing 100, the combustor 400 for mixing the fuel compressed in the compressor 200 and ignited to generate combustion gas, the Turbine 500 for rotating the rotor 600 by obtaining a rotational force from the combustion gas generated in the combustor 400, a generator linked to the rotor 600 for power generation and the combustion gas passed through the turbine 500 It may include a diffuser.

The housing 100 includes a compressor housing 110 in which the compressor 200 is accommodated, a combustor housing 120 in which the combustor 400 is accommodated, and a turbine housing 130 in which the turbine 500 is accommodated. can do.

The compressor housing 110, the combustor housing 120, and the turbine housing 130 may be sequentially arranged from an upstream side to a downstream side in the fluid flow direction.

The rotor 600 is accommodated in the compressor rotor disk 610 accommodated in the compressor housing 110, the turbine rotor disk 630 accommodated in the turbine housing 130 and the combustor housing 120 and the compressor. Tie rods for fastening the torque tube 620 connecting the rotor disk 610 and the turbine rotor disk 630, the compressor rotor disk 610, the torque tube 620, and the turbine rotor disk 630. 640 and retaining nut 650.

The compressor rotor disk 610 may be formed in plural, and the plurality of compressor rotor disks 610 may be arranged along the axial direction of the rotor 600. That is, the compressor rotor disk 610 may be formed in multiple stages.

In addition, each of the compressor rotor disks 610 may be formed in a substantially disc shape, and a compressor blade coupling slot may be formed at an outer circumference thereof to be coupled to the compressor blade 210 to be described later.

The compressor blade coupling slot may be formed in a fir-tree shape to prevent the compressor blade 210, which will be described later, from being separated from the compressor blade coupling slot in a rotational radial direction of the rotor 600.

Here, the compressor rotor disk 610 and the compressor blade 210 to be described later are typically combined in a tangential type or an axial type. In the present embodiment, the compressor rotor disk 610 and the compressor blade 210 are formed to be coupled in an axial type. Accordingly, the compressor blade coupling slot according to the present embodiment may be formed in plural, and the plurality of compressor blade coupling slots may be arranged radially along the circumferential direction of the compressor rotor disk 610.

The turbine rotor disk 630 may be formed similarly to the compressor rotor disk 610. That is, the turbine rotor disk 630 may be formed in plural, and the plurality of turbine rotor disks 630 may be arranged along the axial direction of the rotor 600. That is, the turbine rotor disk 630 may be formed in multiple stages.

In addition, each turbine rotor disk 630 is formed in a substantially disk shape, a turbine blade coupling slot may be formed in the outer peripheral portion is coupled to the turbine blade 510 to be described later.

The turbine blade coupling slot may be formed in a fir shape to prevent the turbine blade 510, which will be described later, from being separated from the turbine blade coupling slot in a rotational radial direction of the rotor 600.

Here, the turbine rotor disk 630 and the turbine blade 510 to be described later are typically combined in a tangential type or an axial type. In this embodiment, the turbine rotor disk 630 is formed to be coupled in an axial type. Accordingly, the turbine blade coupling slot according to the present embodiment may be formed in plural, and the plurality of turbine blade coupling slots may be arranged radially along the circumferential direction of the turbine rotor disk 630.

The torque tube 620 is a torque transmission member that transmits the rotational force of the turbine rotor disk 630 to the compressor rotor disk 610, one end of which is the most in the flow direction of air among the plurality of compressor rotor disks 610. Compressor rotor disk 610 is located at the downstream end, and the other end may be engaged with the turbine rotor disk 630 located at the most upstream end in the flow direction of the combustion gas of the plurality of turbine rotor disk 630. . Here, a protrusion is formed at one end and the other end of the torque tube 620, and a groove is formed in each of the compressor rotor disk 610 and the turbine rotor disk 630 to be engaged with the protrusion. 620 may be prevented from rotating relative to the compressor rotor disk 610 and the turbine rotor disk 630.

The torque tube 620 may be formed in a hollow cylinder shape such that air supplied from the compressor 200 may flow through the torque tube 620 to the turbine 500.

In addition, the torque tube 620 is strongly formed due to the deformation and distortion of the gas turbine continuously operated for a long time, and can be easily assembled and disassembled for easy maintenance.

The tie rod 640 is formed to penetrate through the plurality of compressor rotor disks 610, the torque tube 620, and the plurality of turbine rotor disks 630, and one end thereof includes a plurality of compressor rotor disks 610. A turbine rotor disk fastened in the compressor rotor disk 610 positioned at the most upstream end in the flow direction of the heavy air, and the other end of which is located at the downstreammost end in the flow direction of the combustion gas among the plurality of turbine rotor disks 630 ( 630 may protrude to the opposite side of the compressor 200 and may be fastened to the fixing nut 650.

Here, the fixing nut 650 pressurizes the turbine rotor disk 630 located at the downstream end to the compressor 200, and the compressor rotor disk 610 and the downstream end located at the most upstream end. As the spacing between the turbine rotor disks 630 being located decreases, a plurality of the compressor rotor disks 610, the torque tube 620, and the plurality of turbine rotor disks 630 are axially oriented in the rotor 600. Can be compressed. Accordingly, axial movement and relative rotation of the plurality of compressor rotor disks 610, the torque tube 620, and the plurality of turbine rotor disks 630 may be prevented.

Meanwhile, in the present exemplary embodiment, one tie rod 640 is formed to penetrate through the centers of the plurality of compressor rotor disks 610, the torque tubes 620, and the plurality of turbine rotor disks 630. It is not limited. That is, separate tie rods 640 may be provided on the compressor 200 side and the turbine 500 side, and a plurality of tie rods 640 may be disposed radially along the circumferential direction, and a mixture thereof may be used. It is also possible.

Both ends of the rotor 600 according to such a configuration may be rotatably supported by a bearing, and one end may be connected to the drive shaft of the generator.

The compressor 200 is a compressor vane 220 that is fixed to the housing 100 to align the flow of the air flowing into the compressor blade 210 and the compressor blade 210 and the rotor 600 is rotated together. ) May be included.

The compressor blades 210 are formed in plural, the plurality of compressor blades 210 are formed in plural stages along the axial direction of the rotor 600, and the plurality of compressor blades 210 are formed in each stage. It may be formed radially along the rotation direction of the rotor 600.

Each of the compressor blades 210 includes a plate-shaped compressor blade platform portion, a compressor blade root portion extending from the compressor blade platform portion to a centripetal side in the rotational radial direction of the rotor 600, and the rotor from the compressor blade platform portion. It may include a compressor blade air foil portion extending to the centrifugal side in the rotational radial direction of 600.

The compressor blade platform portion may contact a neighboring compressor blade platform portion and serve to maintain a gap between the compressor blade air foil portions.

As described above, the compressor blade root portion may be formed in a so-called axial type that is inserted into the compressor blade coupling slot along the axial direction of the rotor 600.

In addition, the compressor blade root portion may be formed in a fir shape so as to correspond to the compressor blade coupling slot.

Here, in the present embodiment, the compressor blade root portion and the compressor blade coupling slot are formed in a fir shape, but are not limited thereto and may be formed in a dove tail shape or the like. Alternatively, the compressor blade 210 may be fastened to the compressor rotor disk 610 by using a fastener such as a key or a bolt other than the above type.

In addition, the compressor blade root portion and the compressor blade coupling slot, the compressor blade coupling slot is formed larger than the compressor blade root portion, so that the compressor blade root portion and the compressor blade coupling slot can be easily coupled, the coupling In this state, a gap may be formed between the compressor blade root portion and the compressor blade coupling slot.

Although not shown separately, the compressor blade root portion and the compressor blade coupling slot are fixed by separate pins so that the compressor blade root portion is separated from the compressor blade coupling slot in the axial direction of the rotor 600. Can be prevented.

The compressor blade air foil part is formed to have an airfoil optimized according to the gas turbine specification, and is positioned upstream in the air flow direction, and the leading edge and the air flow direction of the compressor blade air foil part at which air is incident It may comprise a compressor blade air foil portion trailing edge located on the upstream and downstream side where air is emitted.

The compressor vanes 220 may be formed in plural, and the plurality of compressor vanes 220 may be formed in plural stages along the axial direction of the rotor 600. Here, the compressor vanes 220 and the compressor blades 210 may be alternately arranged along the air flow direction.

In addition, the plurality of compressor vanes 220 may be radially formed along the rotation direction of the rotor 600 at each stage.

In addition, each compressor vane 220 includes a compressor vane platform formed in an annular shape along the rotational direction of the rotor 600 and compressor vane air extending from the compressor vane platform in the rotational radial direction of the rotor 600. It may include a foil portion.

The compressor vane platform portion is formed on the tip of the compressor vane air foil portion and is formed at the tip of the root side compressor vane platform portion and the compressor vane air foil portion fastened to the compressor housing 110 and the rotor 600. And a tip side compressor vane platform portion opposing).

Here, the compressor vane platform unit according to the present embodiment to support the compressor vane air foil portion more stably by supporting the tip of the compressor vane air foil portion as well as the tip of the compressor vane air foil portion and the root-side compressor vane platform portion and the It includes, but is not limited to, a tip side compressor vane platform portion. That is, the compressor vane platform unit may be formed to support only the root portion of the compressor vane air foil unit including the root-side compressor vane platform unit.

On the other hand, each compressor vane 220 may further include a compressor vane root portion for coupling the compressor-side compressor vane platform portion and the compressor housing 110.

The compressor vane air foil part is formed to have an airfoil optimized according to the gas turbine specifications, and is located on the upstream side in the flow direction of the air, and the compressor vane air foil part leading edge on which the air is incident and on the downstream side in the flow direction of the air downstream. It may include a compressor vane air foil portion trailing edge that is positioned and out of the air.

The combustor 400 mixes and combusts the air flowing from the compressor 200 with fuel to produce high energy, high temperature, high pressure combustion gas, and withstands the combustor 400 and the turbine 500 in an isostatic combustion process. It can be configured to raise the combustion gas temperature to a limit of heat resistance.

Specifically, the combustor 400 may be formed in plural, and the plurality of combustors 400 may be arranged along the rotational direction of the rotor 600 in the combustor housing 120.

Each of the combustors 400 includes a liner into which the air compressed by the compressor 200 flows, a burner that injects and burns fuel into the air flowing into the liner, and a combustion gas generated by the burner. It may include a transition piece leading to).

The liner may include a flame barrel forming a combustion chamber and a flow sleeve forming an annular space surrounding the flame barrel.

The burner may include a fuel injection nozzle formed at a front side of the liner to inject fuel into the air flowing into the combustion chamber, and a spark plug formed at a wall of the liner to ignite the air and fuel mixed in the combustion chamber. Can be.

The transition piece may be formed so that the outer wall portion of the transition piece is cooled by the air supplied from the compressor 200 so as not to be damaged by the high temperature of the combustion gas.

That is, the transition piece may be provided with a cooling hole for injecting air therein, and the air may cool the main body therein through the cooling hole.

Meanwhile, air that cools the transition piece flows into the annular space of the liner, and air is supplied to cooling air through a cooling hole provided in the flow sleeve on the outer wall of the liner to collide with the outer wall of the liner. have.

Here, although not separately shown, a dispenser serving as a guide vane is provided between the compressor 200 and the combustor 400 to adjust a flow angle of air introduced into the combustor 400 to a design flow angle. Can be formed.

The turbine 500 may be formed similarly to the compressor 200.

That is, the turbine 500 is fixed to the turbine blade 510 rotated together with the rotor 600 and the turbine vane fixed to the housing 100 to align the flow of air flowing into the turbine blade 510. 520 may include.

The turbine blades 510 may be formed in plural, the plurality of turbine blades 510 may be formed in plural stages along the axial direction of the rotor 600, and the plurality of turbine blades 510 may be formed in each stage. It may be formed radially along the rotation direction of the rotor 600.

And each turbine blade 510 is a plate-shaped turbine blade platform part, the turbine blade root part which extends from the turbine blade platform part to the centroid side on the rotation radial direction of the rotor 600, and the rotor from the turbine blade platform part. It may include a turbine blade air foil portion extending to the centrifugal side in the rotational radial direction of 600.

The turbine blade platform portion may contact a neighboring turbine blade platform portion and may serve to maintain a gap between the turbine blade air foil portions.

As described above, the turbine blade root portion may be formed in a so-called axial type that is inserted into the turbine blade coupling slot along the axial direction of the rotor 600.

The turbine blade root portion may be formed in a fir shape so as to correspond to the turbine blade coupling slot.

Here, in the present embodiment, the turbine blade root portion and the turbine blade coupling slot are formed in a fir shape, but are not limited thereto, and may be formed in a dove tail shape or the like. Alternatively, the turbine blade 510 may be fastened to the turbine rotor disk 630 by using a fastener such as a key or bolt other than the above-described configuration.

The turbine blade coupling slot and the turbine blade coupling slot may have the turbine blade coupling slot larger than the turbine blade root so that the turbine blade root and the turbine blade coupling slot can be easily coupled. In this state, a gap may be formed between the turbine blade root portion and the turbine blade coupling slot.

Although not shown separately, the turbine blade root portion and the turbine blade coupling slot are fixed by separate pins so that the turbine blade root portion is separated from the turbine blade coupling slot in the axial direction of the rotor 600. Can be prevented.

The turbine blade air foil part is formed to have an airfoil optimized according to the gas turbine specifications, and is located on the upstream side in the flow direction of the combustion gas, the turbine blade air foil part leading edge and the combustion gas on the flow direction of the combustion gas is incident It may comprise a turbine blade airfoil trailing edge located downstream and from which combustion gas is emitted.

The turbine vanes 520 may be formed in plural, and the plurality of turbine vanes 520 may be formed in plural stages along the axial direction of the rotor 600. Here, the turbine vanes 520 and the turbine blades 510 may be alternately arranged along the air flow direction.

The turbine vanes 520 may be radially formed along the rotation direction of the rotor 600 at each stage.

And each turbine vane 520, the turbine vane platform portion 522 formed in an annular shape along the rotational direction of the rotor 600 and the radial direction of rotation of the rotor 600 from the turbine vane platform portion 522. It may include a turbine vane air foil portion 526 extending to.

The turbine vane platform portion 522 is a root side turbine vane platform portion 522a and the turbine vane air foil portion which are formed at the root portion of the turbine vane air foil portion 526 and fastened to the turbine housing 130. It may include a tip side turbine vane platform portion 522b formed at the tip of 526 and opposite the rotor 600.

Here, the turbine vane platform portion 522 according to the present embodiment to support the turbine vane air foil portion 526 more stably by supporting the tip portion as well as the tip portion of the turbine vane air foil portion 526. For example, the root-side turbine vane platform 522a and the tip-side turbine vane platform 522b are not limited thereto. That is, the turbine vane platform unit 522 may be formed to support only the root portion of the turbine vane air foil unit 526 including the root side turbine vane platform unit 522a.

On the other hand, each turbine vane 520 may further include a turbine vane root portion for fastening the root-side turbine vane platform portion 522a and the turbine housing 130.

The turbine vane air foil part 526 is formed to have an airfoil optimized according to gas turbine specifications, and is positioned on the upstream side in the flow direction of the combustion gas, and the turbine vane air foil part leading edge 526a to which the combustion gas is incident. It may include a turbine vane air foil portion trailing edge 526b located downstream of the flow direction of the combustion gas to exit the combustion gas.

Here, since the turbine 500 contacts the combustion gas of high temperature and high pressure unlike the compressor 200, the turbine 500 requires cooling means to prevent damage such as deterioration.

Accordingly, the gas turbine according to the present embodiment may further include a cooling flow path for supplying the compressed air compressed at a portion of the compressor 200 to the turbine 500.

The cooling passage may extend from the outside of the housing 100 (outside passage), may extend through the inside of the rotor 600 (inside passage), and both the outer passage and the inner passage may be used.

In addition, the cooling passage may communicate with a turbine blade cooling passage formed in the turbine blade 510 so that the turbine blade 510 may be cooled by air (cooling fluid).

In addition, the turbine blade cooling passage is in communication with the turbine blade film cooling hole formed on the surface of the turbine blade 510, by supplying air (cooling fluid) to the surface of the turbine blade 510, the turbine blade ( 510 may be so-called membrane cooled by air (cooling fluid).

In addition, the turbine vane 520 may also be formed to be cooled by receiving air (cooling fluid) from the cooling passage, similar to the turbine blade 510. That is, a turbine vane cooling flow path 528 through which air (cooling fluid) supplied from the cooling flow path passes may be formed in the turbine vane 520.

On the other hand, the turbine 500 requires a gap between the tip of the turbine blade 510 and the inner circumferential surface of the turbine housing 130 so that the turbine blade 510 can be rotated smoothly.

However, the wider the gap, the more advantageous in terms of interference prevention between the turbine blade 510 and the turbine housing 130, but disadvantageous in terms of combustion gas leakage, and the narrower the opposite. That is, the flow of combustion gas injected from the combustor 400 may be divided into a main flow flowing through the turbine blade 510 and a leakage flow passing through a gap between the turbine blade 510 and the turbine housing 130. As the gap is wider, the leakage flow is increased to decrease the gas turbine efficiency, but interference between the turbine blade 510 and the turbine housing 130 due to thermal deformation and the like may be prevented. . On the other hand, as the gap is narrower, the leakage flow is reduced to improve gas turbine efficiency, but interference between the turbine blade 510 and the turbine housing 130 due to thermal deformation and the like may occur.

Accordingly, the gas turbine according to the present embodiment, the sealing to ensure an appropriate gap that can minimize the reduction in gas turbine efficiency while preventing interference between the turbine blade 510 and the turbine housing 130 and the resulting damage, Means may further comprise.

The sealing means is installed on the shroud located at the tip of the turbine blade 510, the labyrinth seal protruding from the shroud to the centrifugal side in the rotational radial direction of the rotor 600 and the inner peripheral surface of the turbine housing 130. Honeycomb thread.

The sealing means according to this configuration is fixed to the shroud rotated at high speed while forming a proper gap between the labyrinth seal and the honeycomb seal, thereby minimizing a decrease in gas turbine efficiency due to combustion gas leakage. Direct contact between the honeycomb yarns and the resulting damage can be prevented.

In addition, the turbine 500 may further include sealing means for blocking leakage between the turbine vane 520 and the rotor 600. In addition to the labyrinth seal described above, a brush seal may be provided. Can be utilized.

In the gas turbine according to this configuration, the air flowing into the housing 100 is compressed by the compressor 200, and the air compressed by the compressor 200 is mixed with fuel by the combustor 400. After combustion, the combustion gas is generated, the combustion gas generated by the combustor 400 flows into the turbine 500, and the combustion gas introduced into the turbine 500 passes through the turbine blade 510. The rotor 600, which is discharged to the atmosphere through the diffuser and rotates by combustion gas, may drive the compressor 200 and the generator after rotating the 600. That is, some of the mechanical energy obtained from the turbine 500 may be supplied as energy required to compress air in the compressor 200, and the rest may be used to generate power by the generator.

On the other hand, the gas turbine according to the present embodiment, the turbine vane cooling flow path 528 is provided with a guide vane 529 for deflecting and evenly dispersing the flow direction of air (cooling fluid) to the turbine vane 520, It can be formed to prevent temperature gradients and thermal stress from occurring.

Specifically, as described above, the turbine vane cooling passage 528 through which air (cooling fluid) for cooling the turbine vane 520 passes is formed in the turbine vane 520, and the turbine vane cooling is performed. The flow path 528 may be formed in a zigzag shape in the turbine vane 520 to increase the heat exchange area to improve cooling performance.

That is, the turbine vane cooling flow path 528 is configured to transfer air (cooling fluid) introduced into the turbine vane cooling flow path 528 from the blade side of the turbine vane air foil part 526 to the turbine vane air foil part 526. To direct the flow direction of the cooling fluid passing through the first turbine vane cooling channel 528a and the first turbine vane cooling channel 528a toward the tip side of the turbine vane air foil part 526. The blade root of the turbine vane air foil part 526 is transferred from the tip side of the turbine vane air foil part 526 to the cooling fluid passing through the second turbine vane cooling flow path 528b and the second turbine vane cooling flow path 528b. A fourth turbine which directs the flow direction of the cooling fluid passing through the third turbine vane cooling flow path 528c and the third turbine vane cooling flow path 528c toward the turbine vane airfoil trailing edge 526b. Vane cooling Cooling fluid having passed through the flow path 528d and the fourth turbine vane cooling flow path 528d from the root side of the turbine vane air foil portion 526 to the entire region of the turbine vane air foil portion trailing edge 526b. Distributing fifth turbine vane cooling passages 528e and 528f.

Here, the fifth turbine vane cooling passages 528e and 528f allow air (cooling fluid) to be smoothly discharged to the outside of the turbine vane 520, and to maximize the cooling performance, the fifth turbine vane cooling passage ( The flow cross sections of 528e and 528f may be formed to be larger than the flow cross sections of the fourth turbine vane cooling passage 528d. That is, the fifth turbine vane cooling passages 528e and 528f are located at the blade root side of the turbine vane air foil part 526 and are opposed to the outlets of the fourth turbine vane cooling passage 528d. The fourth turbine vane is located at the tip end side of the turbine vane air foil part 526 based on a cooling channel first part (inlet opposing part) 528e and the fifth turbine vane cooling channel first part 528e. Over the entire area of the turbine vane air foil portion trailing edge 526b, including a fifth turbine vane cooling channel second portion (inlet non-facing portion) 528f, which is not opposed to the outlet of the cooling passage 528d. Can be formed.

At this time, the air (cooling fluid) flowing along the turbine vane cooling channel 528 flows in a zigzag form inside the turbine vane 520 and is converted from the fourth turbine vane cooling channel 528d to be the fifth. It is discharged to the outside of the turbine vane 520 through the turbine vane cooling flow path (528e, 528f) to cool the turbine vane 520, since the fifth turbine vane cooling flow path (528e, 528f) is formed as a diameter portion. Accordingly, most of the air (cooling fluid) passing through the fourth turbine vane cooling channel 528d is supplied only to the fifth turbine vane cooling channel first part 528e, and the fifth turbine vane cooling channel second part is provided. Almost no air (cooling fluid) may be supplied to 528f. In this case, the fifth turbine vane cooling channel first portion 528e side is overcooled, and the fifth turbine vane cooling channel second portion 528f side is undercooled or not cooled, and thus the turbine vane airfoil trailing. Temperature gradients and thermal stresses may be generated at the edge 526b and damage may occur at the turbine vane airfoil trailing edge 526b.

In consideration of this, the air (cooling fluid) of the air passing through the fourth turbine vane cooling flow path 528d at the boundary between the fourth turbine vane cooling flow path 528d and the fifth turbine vane cooling flow paths 528e and 528f. The guide vane 529 may be formed to guide a part of the fifth turbine vane cooling flow path to the second portion 528f. That is, the guide vane 529 may be formed at the inlet side of the enlarged diameter part to guide a part of air (cooling fluid) flowing into the inlet of the enlarged diameter part toward the inlet non-facing part side.

The guide vane 529 is formed in, for example, a blade shape so as to redirect a flow direction of air (cooling fluid) incident to the guide vane 529, and is discharged from the fourth turbine vane cooling channel 528d as a whole. To the fifth turbine vane cooling flow path second portion (inlet non-facing portion) 528f with respect to the flow direction of air (cooling fluid) (inflowed from the inlet of the enlarged portion) (injected into the guide vane 529). It may be formed in an inclined plate shape.

Here, the guide vanes 529 are integrally formed so as to minimize adverse influences caused by the guide vanes 529, and the front of the fifth turbine vane cooling passages 528e and 528f may also be formed as an integral guide vane 529. It may be inclined at an approximately 45 degree angle so that air (cooling fluid) is evenly distributed in the region.

That is, the guide vane 529 may generate a local stiffness change of the turbine vane 520 at the portion where the guide vane 529 is formed, thereby causing non-uniform thermal deformation and thereby damage. The guide vane 529 according to an example may be integrally formed, thereby minimizing such a problem.

When the guide vanes 529 are integrally formed, air (cooling fluid) guided to the guide vanes 529 may be difficult to reach the tip side of the turbine vane air foil part 526. The integrated guide vane 529 according to the embodiment is air (cooling fluid) discharged from the fourth turbine vane cooling flow path 528d (inflowed from the inlet of the enlarged portion) (injected into the guide vane 529). This problem can be prevented by being inclined at an angle of approximately 45 degrees toward the second portion of the fifth turbine vane cooling channel 528f based on the flow direction of the 528f.

In addition, the guide vane 529 has a flow cross-sectional area at a position where the guide vane 529 is formed so as to distribute air (cooling fluid) evenly to all regions of the fifth turbine vane cooling flow paths 528e and 528f. It can be formed to bisect.

That is, the guide vane 529 crosses the fifth turbine vane cooling channel first part (inlet opposing part) 528e and the fifth turbine vane cooling channel second part (inlet non-facing part) 528f. The distance from the guide vane 529 to the fifth wall of the turbine vane cooling flow path first part (inlet opposing part) 528e side and the guide vane 529 from the guide vane 529 in the squeezing direction (rotational radial direction of the rotor). The distance to the side wall part of the 5th turbine vane cooling flow path 2nd site | part (inlet non-opposing site | part) 528f can be formed equal.

In the gas turbine according to the present embodiment including the guide vane 529 according to the above configuration, a part of the air (cooling fluid) that has passed through the fourth turbine vane cooling channel 528d is the fifth turbine vane cooling channel. The remainder of the air (cooling fluid) supplied to the first portion 528e and passing through the fourth turbine vane cooling channel 528d is diverted by the guide vanes 529 to provide the fifth turbine vane cooling channel second. By being supplied to the portion 528f, air (cooling fluid) can be evenly supplied to all the regions of the fifth turbine vane cooling passages 528e and 528f. As a result, the turbine vane air foil portion trailing edge 526b is uniformly cooled, and a temperature gradient is prevented from occurring in the turbine vane air foil portion trailing edge 526b, and the turbine vane air foil portion trailing is prevented. The occurrence of thermal stress at the edge 526b is prevented, and damage to the turbine vane air foil portion trailing edge 526b can be prevented.

On the other hand, in the above-described embodiment, the guide vanes 529 are formed as one to minimize the adverse effect of the local stiffness change, but as shown in FIG. Two guide vanes 529 may be formed for even distribution.

That is, referring to the accompanying FIG. 3, the guide vanes 529 of the gas turbine according to another embodiment of the present invention are located on the downstream side of the first guide vane 529a and the first guide vane 529a. It may include a second guide vane (529b).

Here, the downstream of the first guide vane 529a is a first guide positioned on the first part of the fifth turbine vane cooling flow path (inlet opposing part) 528e based on the first guide vane 529a. The first guide vane second downstream positioned on the second turbine vane cooling flow path second part (inlet non-facing part) 528f side with respect to the vane first downstream D1 and the first guide vane 529a. D2), and the second guide vane 529b may include a fifth portion in which air (cooling fluid) has a larger flow cross-sectional area than a first portion of the fifth turbine vane cooling channel (inlet opposing portion) 528e. The first guide vane first to be supplied more to the turbine vane cooling flow path second portion (inlet non-facing portion) 528f to distribute more evenly over the entire area of the fifth turbine vane cooling flow passages 528e and 528f. It may be formed downstream (D1).

In addition, the first guide vane 529a includes the fifth turbine vane cooling flow path (expansion part) such that air (cooling fluid) is distributed evenly over the entire area of the fifth turbine vane cooling flow paths 528e and 528f. 528e and 528f are inclined toward the second portion of the fifth turbine vane cooling flow path (inlet non-facing portion) 528f with respect to the flow direction of air (cooling fluid) flowing from the inlet, and the second guide vane ( 529b) is formed to be inclined toward the second turbine vane cooling flow path second part (inlet non-facing part) 528f with respect to the flow direction of air (cooling fluid) flowing into the first guide vane first downstream D1. The first guide vane 529a may be formed to be more inclined toward the second portion of the fifth turbine vane cooling channel 528f than the second guide vane 529b. Preferably, the first guide vane 529a is the fifth turbine vane based on a flow direction of air (cooling fluid) flowing from an inlet of the fifth turbine vane cooling flow path (expansion part) 528e and 528f. It is formed to be inclined at an angle of approximately 45 degrees toward the cooling channel second portion (inlet non-opposite portion) 528f, and the second guide vane 529b is formed of the fifth turbine vane cooling passages (diameters) 528e and 528f. The second turbine vane cooling channel may be inclined at an angle of about 30 degrees to the second portion of the fifth turbine vane cooling channel (528 inward non-facing portion) 528f based on the flow direction of the air (cooling fluid) flowing from the inlet.

In addition, the first guide vanes 529a are formed with the first guide vanes 529a so that air (cooling fluid) is evenly distributed over the entire area of the fifth turbine vane cooling passages 528e and 528f. It is formed to bisec the flow cross-sectional area at the position, and the second guide vane 529b may be formed to bisect the flow cross-sectional area at the position where the second guide vane 529b is formed.

That is, the first guide vane 529a includes the fifth turbine vane cooling channel first part (inlet opposing part) 528e and the fifth turbine vane cooling channel second part (inlet non-opposing part) 528f. The distance from the first guide vane 529a to the wall portion on the side of the first portion (inlet opposing portion) 528e on the fifth turbine vane cooling flow path in the direction traversed by the rotor (rotational radial direction of the rotor) and the first guide. The distance from the vane 529a to the wall part of the 5th turbine vane cooling flow path 2nd site | part (inlet non-facing part) 528f side may be formed equally.

The second guide vane 529b includes the fifth turbine vane cooling channel first part (inlet opposing part) 528e and the fifth turbine vane cooling channel second part (inlet non-opposing part) 528f. Distance from the second guide vane 529b to the wall portion on the side of the first portion (inlet opposing portion) 528e of the fifth turbine vane cooling flow path in the direction traversed by the rotor (rotational radial direction of the rotor) and the second guide. The distance from the vanes 529b to the first guide vanes 529a may be the same.

Meanwhile, in the above-described embodiment, the turbine vane cooling passage 528 may include the first turbine vane cooling passage 528a, the second turbine vane cooling passage 528b, the third turbine vane cooling passage 528c, and the The fourth turbine vane cooling channel 528d and the fifth turbine vane cooling channel 528e and 528f are not limited thereto. That is, although not separately illustrated, the shape of the turbine vane cooling flow path 528, such as a flow direction of the turbine vane cooling flow path 528 and the number of turnovers, may be appropriately modified.

Meanwhile, in the above-described embodiment, the guide vane 529 is formed in the turbine vane cooling channel 528, but is not limited thereto. That is, although not separately illustrated, for example, a cooling passage and a guide vane may be formed in the compressor vane 220.

100: housing
200: compressor
210: compressor blade
220: compressor vane
400: burner
500: turbine
510 turbine blade
520 turbine vanes
526b: turbine vane airfoil trailing edge
528: turbine vane cooling euro
528a: first turbine vane cooling path
528b: second turbine vane cooling path
528c: third turbine vane cooling path
528d: fourth turbine vane cooling euro
528e: fifth turbine vane cooling flow path first portion
528f: 5th turbine vane cooling flow path 2nd part
529: guide vanes
529a: first guide vane
529b: 2nd guide vane
600: rotor
D1: first guide vane first downstream
D2: first guide vane second downstream located on the side

Claims (20)

A housing 100;
A rotor (600) rotatably provided in the housing (100);
Compressor 200 for receiving the rotational force from the rotor 600 to compress the air;
Combustor 400 for mixing the fuel compressed in the compressor 200 and ignited to produce a combustion gas; And
And a turbine 500 that rotates the rotor 600 by obtaining a rotational force from the combustion gas generated by the combustor 400.
The turbine 500,
A turbine blade 510 rotated together with the rotor 600; And
And a turbine vane 520 fixed to the housing 100 to align the flow of the combustion gas flowing into the turbine blade 510.
The turbine vane 520 is provided with a turbine vane cooling passage 528 through which a cooling fluid for cooling the turbine vane 520 passes.
The turbine vane cooling passage 528 is formed with a guide vane 529 for redirecting the flow direction of the cooling fluid,
The turbine vane cooling passage 528 includes enlarged diameter portions 528e and 528f in which a flow cross section is enlarged.
The enlarged diameter portions 528e and 528f may include an inlet opposing portion 528e opposed to an inlet of the enlarged diameter portions 528e and 528f; And an inlet non-facing portion 528f that does not face the inlets of the enlarged diameter portions 528e and 528f.
The guide vane 529 is formed to guide a portion of the cooling fluid flowing from the inlet side of the enlarged diameter portions 528e and 528f to the inlet of the enlarged diameter portions 528e and 528f toward the inlet non-facing portion 528f. ,
The guide vane 529 may include a first guide vane 529a; And a second guide vane 529b positioned downstream of the first guide vane 529a.
The first guide vane 529a crosses the inlet opposing portion 528e and the inlet non-opposing portion 528f so as to bisect the flow cross-sectional area at the position where the first guide vane 529a is formed. The distance from the first guide vane 529a to one wall of the turbine vane cooling channel 528 and the distance from the first guide vane 529a to the other wall of the turbine vane cooling channel 528 are the same. Formed,
The second guide vane 529b crosses the inlet opposing portion 528e and the inlet non-opposing portion 528f so as to bisect the flow cross section at the position where the second guide vane 529b is formed. The distance from the second guide vane 529b to one wall of the turbine vane cooling passage 528 and the distance from the second guide vane 529b to the first guide vane 529a are equally formed. Gas turbine. delete delete The method of claim 1,
The guide vane (529) is a gas turbine formed integrally. delete delete The method of claim 4, wherein
The guide vane (529) is formed to be inclined toward the inlet non-facing portion (528f) with respect to the flow direction of the cooling fluid flowing from the inlet of the enlarged portion (528e, 528f). The method of claim 1,
The gas turbine is formed of two guide vanes (529). The method of claim 8,
Downstream of the first guide vane 529a,
A first guide vane first downstream (D1) positioned on the inlet opposing portion (528e) side with respect to the first guide vane (529a); And
A first guide vane second downstream D2 positioned on the inlet non-facing part 528f side with respect to the first guide vane 529a;
And the second guide vane (529b) is located first downstream of the first guide vane (D1). delete delete delete delete The method of claim 9,
The first guide vane 529a is formed to be inclined toward the inlet non-facing portion 528f with respect to the flow direction of the cooling fluid flowing from the inlets of the enlarged diameter portions 528e and 528f,
And the second guide vane (529b) is inclined toward the inlet non-facing portion (528f) with respect to the flow direction of the cooling fluid flowing into the first guide vane first downstream (D1) side. The method of claim 14,
And the first guide vane (529a) is formed to be inclined more toward the inlet non-facing portion (528f) than the second guide vane (529b). The method of claim 15,
The first guide vane 529a is formed to be inclined at an angle of 45 degrees toward the inlet non-facing portion 528f with respect to the flow direction of the cooling fluid flowing from the inlets of the enlarged diameter portions 528e and 528f,
The second guide vane (529b) is formed to be inclined at an angle of 30 degrees toward the inlet non-facing portion (528f) relative to the flow direction of the cooling fluid flowing from the inlet of the enlarged portion (528e, 528f). The method of claim 1,
The turbine vane cooling passage 528 is,
A first turbine vane cooling channel 528a for guiding the cooling fluid introduced into the turbine vane cooling channel 528 from the blade side of the turbine vane 520 to the tip side of the turbine vane 520;
A second turbine vane cooling channel 528b for redirecting the flow direction of the cooling fluid passing through the first turbine vane cooling channel 528a to the blade root side;
A third turbine vane cooling channel 528c for guiding the cooling fluid that has passed through the second turbine vane cooling channel 528b from the tip side to the blade side;
A fourth turbine vane cooling channel 528d for redirecting the flow direction of the cooling fluid passing through the third turbine vane cooling channel 528c to the trailing edge side of the turbine vane 520; And
And fifth turbine vane cooling passages (528e, 528f) for distributing the cooling fluid passing through the fourth turbine vane cooling passage (528d) from the blade root side to the entire region of the trailing edge.
And the guide vane (529) is formed at a boundary between the fourth turbine vane cooling channel (528d) and the fifth turbine vane cooling channel (528e, 528f). The method of claim 17,
The fifth turbine vane cooling passages (528e, 528f),
A fifth turbine vane cooling flow path first portion 528e positioned on the blade root side; And
And a fifth turbine vane cooling channel second portion 528f positioned on the tip side.
The guide vane (529) is formed to guide a portion of the cooling fluid passing through the fourth turbine vane cooling flow path (528d) toward the fifth turbine vane cooling flow path second portion (528f) side. The method of claim 18,
The guide vane 529 is formed of two or less,
Each guide vane (529) is formed to bisect the flow rate of the cooling fluid flowing into the guide vanes (529). A housing 100;
A rotor (600) rotatably provided in the housing (100);
Blades (210, 510) rotated together with the rotor (600); And
And vanes (220, 520) for aligning the flow of fluid flowing into the blades (210, 510),
Cooling flow paths through which cooling fluid passes are formed in the vanes 220 and 520,
Guide vanes for dispersing cooling fluid are formed in the cooling passage,
The cooling flow path includes an enlarged portion in which the flow cross section is enlarged,
The enlarged diameter portion, the inlet opposing portion facing the inlet of the enlarged diameter portion; And an inlet non-facing portion that is not opposed to the inlet of the enlarged diameter portion.
The guide vane is formed to guide a part of the cooling fluid flowing into the inlet of the enlarged diameter part from the inlet side of the enlarged diameter part toward the inlet non-facing part side,
The guide vane may include a first guide vane; And a second guide vane positioned downstream of the first guide vane;
The first guide vane is one side of the cooling passage from the first guide vane in a direction crossing the inlet opposing portion and the non-inlet opposing portion so as to bisec the flow cross-sectional area at the position where the first guide vane is formed. The distance to the wall portion and the distance from the first guide vane to the other wall portion of the cooling flow path is formed equally,
The second guide vane is one side of the cooling flow path from the second guide vane in a direction crossing the inlet opposing portion and the non-inlet opposing portion so as to bisec the flow cross-sectional area at the position where the second guide vane is formed. And a distance from the second guide vane to the first guide vane is equally formed.

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