Turbulator Design for Combustor Liner Cooling

Abstract

The present invention relates to a turbulence generator with a rip turbulator for cooling a combustor liner, and more specifically, to a turbulence generator for cooling a gas turbine liner, comprising: a combustion gas flow path into which combustion gas is introduced; a cooling space provided at the rear end of the combustion gas flow path; a cooling channel for introducing a coolant into the cooling space; and an outlet cooling plate installed within the cooling channel, which forms film cooling through the coolant introduced into the cooling space through the cooling channel, and which is equipped with a rip turbulator on one side.

Description

Technology Field

[0001] The present invention relates to a turbulence generator with a rip turbulator applied for cooling a combustor liner. Background Technology

[0002] Research to increase the efficiency of gas turbines has been conducted for a long time, and generally, research has proceeded in the direction of raising the turbine inlet temperature. However, raising the turbine inlet temperature increased the risk of degradation and failure of gas turbine components, and to solve this, technologies and materials were developed. In this regard, the advancement of cooling technology has contributed to increasing gas turbine efficiency and extending the lifespan of gas turbine components. Figures 1a and 1b show the configuration diagram and image of a gas turbine.

[0003] Global demand for electricity is increasing, and gas turbines are playing a pivotal role in meeting this energy demand. Growing at an annual rate of 4.5% since 2019, the market is projected to reach $27.9 billion by 2033. Gas turbines are primarily applied in power generation and aviation sectors. When analyzing market share by type, capacity, and technology, large gas turbines are dominant in terms of type, capacity exceeding 300 MW, and combined cycle technology.

[0004] A gas turbine is a device that converts the chemical energy of fuel into thermal energy to generate rotational mechanical energy. As shown in Fig. 1a, it consists of a compressor, a combustor, and a turbine, and the compressor and turbine are composed of multiple stages. Gas turbines are used for propulsion of aircraft and ships, or for power generation to produce electricity.

[0005] To increase the efficiency of gas turbines, turbine inlet temperatures have steadily increased, and accordingly, cooling technologies are being developed to improve thermal fatigue and thermal durability. Cooling technologies include internal cooling utilizing fin-fin structures and rib turbators, external cooling including impingement cooling and film cooling, and thermal shielding coatings.

[0006] Different cooling techniques are applied to the leading edge part, serpentine part, and trailing edge part of the gas turbine for internal cooling. Since the thermal load is strongest in the leading edge part, impingement cooling is applied, and because the flow velocity is high, a lip turbulator is applied to only one side to minimize pressure loss.

[0007] Ripturbators improve heat transfer performance by promoting turbulence, and their variables include shape, pitch, height, and width. While heat transfer is enhanced by these various variables, pressure drop also increases simultaneously; therefore, the selection of optimal variables and numerical settings are crucial.

[0008] Currently, research on changes in the shape and arrangement of ripturbators is actively underway, and research on the optimization of ripturbators using AI is also being conducted, but there is a lack of validation experiments to support this, and there is a lack of research on internal cooling through experiments such as PIV. Prior art literature

[0009] Japanese Published Patent 2014-509712 Korean Published Patent 10-2019-0037492 Japanese Published Patent 2010-203440 The problem to be solved

[0010] Accordingly, the present invention has been devised to solve the aforementioned conventional problems. According to an embodiment of the present invention, the purpose is to propose a structure that improves the cooling efficiency of gas turbine components that must withstand high temperatures by attaching a lip turbulator to an existing cooling plate.

[0011] According to an embodiment of the present invention, the purpose is to provide a turbulence generator with a lip turbulator for cooling a combustor liner, which can improve the stability of gas turbine components at high temperatures by installing a lip turbulator on a cooling plate having a conventional simple angle cylinder shape to improve the cooling performance of the combustor and blades, thereby spreading the coolant better and increasing cooling efficiency compared to a cooling plate without a lip turbulator.

[0012] Meanwhile, the technical problems to be solved by the present invention are not limited to those mentioned above, and other technical problems not mentioned will be clearly understood by those skilled in the art to which the present invention belongs from the description below. means of solving the problem

[0013] The first objective of the present invention can be achieved as a turbulence generator for cooling a gas turbine liner, comprising: a combustion gas flow path into which combustion gas is introduced; a cooling space provided at the rear end of the combustion gas flow path; a cooling channel for introducing a coolant into the cooling space; and an outlet cooling plate installed within the cooling channel, which forms film cooling through the coolant introduced into the cooling space through the cooling channel, and which is equipped with a rip turbulator on one side.

[0014] In addition, the direction of inflow of the coolant may be a direction intersecting the direction of inflow of the combustion gas, and the planar direction of the outlet cooling plate may be a direction intersecting the direction of inflow of the coolant.

[0015] Additionally, it may include a collision plate installed within the cooling channel, with a planar direction intersecting the direction of the inflow of the coolant, and having a plurality of outflow cooling holes formed therein to uniformly inflow the coolant; wherein the outflow cooling plate is installed at a specific distance from the collision plate in the direction of the coolant.

[0016] In addition, the above-mentioned outflow cooling plate may be characterized by having a plurality of inclined cylinder-shaped impact cooling holes formed therein.

[0017] In addition, the planar cross-section of the impact outflow hole in the impact inflow hole of the above-mentioned impact cooling hole may be characterized as being elliptical.

[0018] And the inclination angle of the above inclined cylinder shape can be characterized as being 25 to 35 degrees.

[0019] In addition, the plurality of the above-mentioned rip turbulators may be characterized by having a specific pitch in the longitudinal direction of the outflow cooling plate, and the longitudinal direction of the rip turbulators may be the width direction of the outflow cooling plate.

[0020] And the longitudinal central axis of the above-mentioned ripturbulator may be characterized by coinciding with a virtual line connecting the center of the impact outflow hole of the above-mentioned impact cooling hole in the width direction.

[0021] In addition, the longitudinal central axis of the above-mentioned lipturbulator may be characterized by coinciding with a virtual line connecting the center of the outflow cooling hole in the width direction and a virtual line connecting the center of the collision outflow hole of the above-mentioned outflow cooling hole in the width direction.

[0022] And the above-mentioned ripturbulator may be characterized by having a width (e), a height (h), and a length, and the upper surface of the ripturbulator may form a curved surface that is convex upward.

[0023] In addition, with respect to the 700 length portion in the longitudinal direction of the above-mentioned outflow cooling plate, the pitch of the above-mentioned ripturbator may be characterized as being 60 to 70 length portions.

[0024] And with respect to the length of 700 in the longitudinal direction of the above-mentioned outflow cooling plate, the width of the above-mentioned ripturbulator may be characterized as being 1.8 to 3 lengths.

[0025] In addition, the height of the above-mentioned ripturbulator may be characterized as being 0.8 to 1.5 relative to the width.

[0026] And with respect to the 700 length portion in the longitudinal direction of the above-mentioned outflow cooling plate, the major axis length of the above-mentioned impact cooling hole may be characterized as being 14 to 18 length portions.

[0027] In addition, regarding the 300 length portion in the width direction of the above-mentioned outflow cooling plate, the pitch in the width direction of the above-mentioned impact cooling hole may be characterized as being 14 to 18 length portions.

[0028] And with respect to the 300 length portion in the width direction of the above-mentioned discharge cooling plate, the pitch in the width direction of the above-mentioned discharge cooling hole may be characterized as being 14 to 18 length portions. Effects of the invention

[0029] According to the turbulence generator with a lip turbulator for cooling a combustor liner according to an embodiment of the present invention, by attaching a lip turbulator to an existing cooling plate, it has the effect of improving the cooling efficiency of gas turbine components that must withstand high temperatures.

[0030] According to an embodiment of the present invention, the purpose is to provide a cooling plate having a conventional simple angle cylinder shape with a lip turbulator installed to improve the cooling performance of the combustor and blades, thereby spreading the coolant better and increasing the cooling efficiency compared to a cooling plate without a lip turbulator, and improving the stability of the gas turbine components at high temperatures.

[0031] Meanwhile, the effects obtainable from the present invention are not limited to those mentioned above, and other unmentioned effects will be clearly understood by those skilled in the art to which the present invention belongs from the description below. Brief explanation of the drawing

[0032] The following drawings attached to this specification illustrate preferred embodiments of the present invention and serve to further enhance understanding of the technical concept of the present invention together with the detailed description of the invention; therefore, the present invention should not be interpreted as being limited only to the matters described in such drawings. Figures 1a and 1b are a schematic diagram and an image of a gas turbine, FIG. 2 is a configuration diagram of a turbulence generator with a rip turbulator applied for cooling a combustor liner according to an embodiment of the present invention. FIG. 3a is a side cross-sectional view of a collision cooling hole according to an embodiment of the present invention, FIG. 3b is a plan view of a collision cooling hole according to an embodiment of the present invention, FIG. 4 is a side view of a ripturbulator according to an embodiment of the present invention, FIG. 5 is a plan view of a cooling plate showing an outflow cooling hole and an impact inflow hole according to an embodiment of the present invention. FIG. 6a is a plan view of an outflow cooling plate without a ripturbulator applied, FIG. 6b is a plan view of an outflow cooling plate to which a rip turbulator is applied according to an embodiment of the present invention, FIG. 7 is a side cross-sectional view of an outflow cooling plate with a rip turbulator applied according to an embodiment of the present invention, FIG. 8 shows a thermal imaging camera image of an outflow cooling plate without a ripturbulator applied and an outflow cooling plate with a ripturbulator applied according to an experimental example of the present invention. FIG. 9 shows a graph comparing the efficiency of an outflow cooling plate without a rip turbulator and an outflow cooling plate with a rip turbulator according to an experimental example of the present invention. Specific details for implementing the invention

[0033] The above objects, other objects, features, and advantages of the present invention will be easily understood through the following preferred embodiments associated with the accompanying drawings. However, the present invention is not limited to the embodiments described herein and may be embodied in other forms. Rather, the embodiments introduced herein are provided to ensure that the disclosed content is thorough and complete and to ensure that the spirit of the invention is sufficiently conveyed to a person skilled in the art.

[0034] In this specification, when a component is described as being on another component, it means that it may be formed directly on the other component or that a third component may be interposed between them. Also, in the drawings, the thicknesses of the components are exaggerated for the effective description of the technical content.

[0035] The embodiments described herein will be explained with reference to cross-sectional and / or plan views, which are exemplary illustrations of the invention. In the drawings, the thicknesses of films and regions are exaggerated for effective explanation of the technical content. Accordingly, the shapes of the exemplary drawings may be modified by manufacturing techniques and / or tolerances, etc. Accordingly, the embodiments of the invention are not limited to the specific shapes depicted but include variations in shape produced according to the manufacturing process. For example, a region depicted as a right angle may be rounded or have a certain curvature. Accordingly, the regions illustrated in the drawings have properties, and the shapes of the regions illustrated in the drawings are intended to illustrate specific shapes of the regions of the device and are not intended to limit the scope of the invention. Although terms such as first, second, etc., have been used to describe various components in the various embodiments of this specification, these components should not be limited by such terms. These terms are used merely to distinguish one component from another. The embodiments described and illustrated herein also include their complementary embodiments.

[0036] The terms used herein are for describing the embodiments and are not intended to limit the invention. In this specification, the singular form includes the plural form unless specifically stated otherwise in the text. As used herein, 'comprises' and / or 'comprising' do not exclude the presence or addition of one or more other components to the mentioned components.

[0037] In describing the specific embodiments below, various specific details have been included to explain the invention more specifically and to aid understanding. However, a reader with sufficient knowledge in the art to understand the invention will recognize that it can be used without these various specific details. In some cases, it is noted in advance that commonly known aspects that are not significantly related to the invention have been omitted to prevent unnecessary confusion in describing the invention.

[0039] Below, the configuration of a turbulence generator with a rip turbulator applied for cooling a combustor liner according to an embodiment of the present invention will be described.

[0040] First, FIG. 2 illustrates a configuration diagram of a turbulence generator with a rip turbulator applied for cooling a combustor liner according to an embodiment of the present invention.

[0041] And FIG. 3a shows a side cross-sectional view of a collision cooling hole according to an embodiment of the present invention, and FIG. 3b shows a plan view of a collision cooling hole according to an embodiment of the present invention.

[0042] And Fig. 4 shows a side view of a lip turbulator according to an embodiment of the present invention.

[0043] FIG. 5 is a plan view of a cooling plate showing an outflow cooling hole and an impact inflow hole according to an embodiment of the present invention.

[0044] In addition, Fig. 6a shows a plan view of an outflow cooling plate to which a rip turbulator is not applied.

[0045] A turbulence generator according to an embodiment of the present invention is a cooling unit for cooling a gas turbine combustor liner, comprising: a combustion gas passage into which combustion gas is introduced; a cooling space provided at the rear end of the combustion gas passage; and a cooling channel for introducing a coolant into the cooling space.

[0046] A turbulence generator with a rip turbulator for cooling a combustor liner according to an embodiment of the present invention is installed within a cooling channel and forms film cooling through a coolant flowing into a cooling space through the cooling channel, and is configured to include an outflow cooling plate having a rip turbulator on one side.

[0047] And the direction of inflow of the coolant is a direction intersecting the direction of inflow of the combustion gas, and the planar direction of the outlet cooling plate is a direction intersecting the direction of inflow of the coolant.

[0048] In addition, an impact plate is installed within the cooling channel, and this impact plate is installed in a planar direction that intersects the direction of coolant inflow, and is configured to have multiple outflow cooling holes formed to ensure uniform inflow of coolant.

[0049] The outflow cooling plate according to an embodiment of the present invention is installed at a specific distance from the collision plate in the direction of the coolant.

[0050] In addition, as shown in FIG. 3a and FIG. 3b, a plurality of impact cooling holes in the shape of an inclined cylinder are formed in this outflow cooling plate. It can be seen that the planar cross-section of the impact outflow hole from the impact inflow hole of the impact cooling hole is elliptical. The angle of inclination of the inclined cylinder shape according to the embodiment of the present invention is 25 to 35 degrees.

[0051] According to an embodiment of the present invention, a plurality of the above-mentioned rip turbulators have a specific pitch in the longitudinal direction of the outflow cooling plate, and the longitudinal direction of the rip turbulators is the width direction of the outflow cooling plate.

[0052] And the longitudinal central axis of the ripturbulator according to an embodiment of the present invention coincides with a virtual line connecting the center of the impact outflow hole of the impact cooling hole in the width direction.

[0053] More specifically, the longitudinal central axis of the ripturbator is configured to coincide with a virtual line connecting the center of the outflow cooling hole in the width direction and a virtual line connecting the center of the collision outflow hole of the outflow cooling hole in the width direction.

[0054] As shown in FIG. 4, the ripturbulator according to an embodiment of the present invention has a width (e), a height (h), and a length, and it can be seen that the upper surface of the ripturbulator forms a curved surface that is convex upward.

[0055] FIG. 6b shows a plan view of an outflow cooling plate with a rip turbulator applied according to an embodiment of the present invention. FIG. 7 shows a side cross-sectional view of an outflow cooling plate with a rip turbulator applied according to an embodiment of the present invention.

[0056] As shown in FIGS. 6b and FIGS. 7, for a length of 700 in the longitudinal direction of the outflow cooling plate, the pitch (P) of the rip turbulator is configured to have a length of about 60 to 70.

[0057] In addition, for a length of 700 in the longitudinal direction of the outflow cooling plate, the width (e) of the ripturbulator is characterized to be approximately 1.8 to 3 lengths.

[0058] And the height (h) of the ripturbator is configured to be approximately 0.8 to 1.5 relative to the width (e).

[0059] In addition, for a length of 700 in the longitudinal direction of the outflow cooling plate, the major axis length of the impact cooling hole is approximately 14 to 18 lengths.

[0060] And for the 300 length portion in the width direction of the outflow cooling plate, the pitch of the impact cooling hole in the width direction is about 14 to 18 length portion.

[0061] In addition, for a 300-meter length portion in the width direction of the outflow cooling plate, the pitch in the width direction of the outflow cooling hole is approximately 14 to 18 meters.

[0063] Below, we will describe experimental examples and result data regarding a turbulence generator with a rip turbulator applied for cooling a combustor liner according to the embodiment of the present invention mentioned above.

[0064] FIG. 8 shows thermal camera images of an outflow cooling plate without a rip turbulator and an outflow cooling plate with a rip turbulator applied according to an experimental example of the present invention.

[0065] FIG. 9 shows a graph comparing the efficiency of an outflow cooling plate without a rip turbulator and an outflow cooling plate with a rip turbulator according to an experimental example of the present invention.

[0066] In the experimental example of the present invention, to simulate the gas turbine membrane cooling effect, power was supplied to a mesh heater using a low-voltage, high-current power supply to generate a temperature difference, and an experiment was conducted using an IR camera.

[0067] Hot air passes through the main flow, and a coolant is supplied from the impact plate, forming a film of coolant on the surface of the outflow cooling plate. In the experimental example of the present invention, the experiment was conducted by applying a lip turbulator at the cross flow position.

[0068] As shown in Figures 6b and 7, the experiment was conducted by aligning the center of the outflow cooling hole and the center of the collision outflow hole to the same position.

[0069] In the experimental examples of the present invention, experiments were conducted on cases where a simple cylindrical impact cooling hole with an angle of 30˚ was applied to the outflow cooling plate and a plate with a straight lip turbulator applied to the simple 30˚ impact cooling hole. The experiment was conducted by attaching the lip turbulator at the same position as the center of the outflow cooling hole and the impact outflow hole.

[0070] As shown in Fig. 8, it can be seen that the data was captured by a thermal imaging camera of the outflow cooling plate for each injection ratio by applying a temperature difference. It can be confirmed that the shape with a straight lip turbulator applied at a simple angle of 30˚ is better at cooling than the simple cylinder shape at a simple angle of 30˚, thereby improving cooling performance, and that cooling performance increases from upstream to downstream at all injection ratios due to the coolant superposition effect.

[0071] In addition, the efficiency of a simple cylinder shape with a 30˚ angle and a shape with a lip turbulator applied was compared and analyzed in Fig. 9. It can be confirmed that the shape with a straight lip turbulator applied to a simple cylinder shape with a 30˚ angle is better cooled than the simple cylinder shape with a 30˚ angle, thereby improving cooling performance, and that cooling performance increases from upstream to downstream at all injection ratios due to the coolant overlapping effect.

[0073] In addition, the apparatus and method described above are not limited to the configurations and methods of the embodiments described above; rather, all or part of each embodiment may be selectively combined to allow for various modifications to be made.

Claims

Claim 1 A turbulence generator for cooling a gas turbine combustor liner, comprising: a combustion gas passage into which combustion gas is introduced; a cooling space provided downstream of the combustion gas passage; and a cooling channel for introducing a coolant into the cooling space. A turbulence generator with a rip turbulator for cooling a gas turbine combustor liner, comprising: an outlet cooling plate installed within the cooling channel and having a plurality of rip turbulators on one side to form film cooling through a coolant flowing in through the cooling channel; wherein the outlet cooling plate is provided with a plurality of impact cooling holes having an elliptical structure in which the flat cross-section forms the major axis and has an inclination angle of 25° to 35° in the direction of the cooling channel; wherein the plurality of rip turbulators are formed extending along the width direction of the outlet cooling plate, and the upper surface of the rip turbulators has a curved shape that is convex upward; and the longitudinal central axis of the rip turbulators is spatially coaxially aligned parallel to a virtual line connecting the center of the outlet cooling hole of the outlet cooling plate in the width direction and a virtual line connecting the center of the impact outlet hole of the impact cooling hole in the width direction. Claim 2 A turbulence generator with a rip turbulator for cooling a gas turbine combustor liner, characterized in that, in claim 1, the inflow direction of the coolant is a direction intersecting the inflow direction of the combustion gas, and the planar direction of the outflow cooling plate is a direction intersecting the inflow direction of the coolant. Claim 3 A turbulence generator with a rip turbulator for cooling a gas turbine combustor liner, characterized in that, in claim 2, it includes an impact plate installed within the cooling channel, arranged such that its planar direction intersects the direction of inflow of the coolant, and having a plurality of impact cooling holes formed therein to introduce the coolant, wherein the outflow cooling plate is installed spaced apart from the impact plate and the cooling channel on the downstream side of the direction of inflow of the coolant, with a spaced-apart space forming the cooling channel. Claim 4 A turbulence generator with rip turbulators for cooling a gas turbine combustor liner, characterized in that, in claim 1, the plurality of rip turbulators are spaced apart from each other with a constant pitch along the longitudinal direction of the outflow cooling plate. Claim 5 A turbulence generator with a ripturbulator applied for cooling a gas turbine combustor liner, characterized in that, in claim 4, when the total longitudinal unit of the discharge cooling plate is defined as 700 length sections, the pitch of the ripturbulator is in the range of 60 to 70 length sections, the width of the ripturbulator is in the range of 1.8 to 3 length sections, and the height of the ripturbulator is in the ratio of 0.8 to 1.5 to the width. Claim 6 delete Claim 7 delete Claim 8 delete Claim 9 delete Claim 10 delete Claim 11 delete Claim 12 delete Claim 13 delete Claim 14 delete Claim 15 delete Claim 16 delete

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