WO2018038507A1 - Aube de turbine à gaz - Google Patents

Aube de turbine à gaz Download PDF

Info

Publication number
WO2018038507A1
WO2018038507A1 PCT/KR2017/009154 KR2017009154W WO2018038507A1 WO 2018038507 A1 WO2018038507 A1 WO 2018038507A1 KR 2017009154 W KR2017009154 W KR 2017009154W WO 2018038507 A1 WO2018038507 A1 WO 2018038507A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine blade
cooling
gas turbine
outlet portion
rib
Prior art date
Application number
PCT/KR2017/009154
Other languages
English (en)
Korean (ko)
Inventor
이기돈
Original Assignee
두산중공업 주식회사
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 두산중공업 주식회사 filed Critical 두산중공업 주식회사
Priority to CN201780029639.4A priority Critical patent/CN109154199B/zh
Priority to US16/084,968 priority patent/US10927681B2/en
Priority to EP17843927.9A priority patent/EP3502418B1/fr
Priority claimed from KR1020170106069A external-priority patent/KR101951115B1/ko
Publication of WO2018038507A1 publication Critical patent/WO2018038507A1/fr

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling

Definitions

  • the present invention relates to a turbine blade provided in a gas turbine, and more particularly, to a gas turbine blade for mixing the high temperature hot gas moved toward the turbine blade to perform membrane cooling of the turbine blade.
  • a gas turbine is a type of internal combustion engine that converts thermal energy into mechanical energy by rotating a high-temperature, high-pressure combustion gas generated by mixing fuel with air compressed at high pressure in a compressor unit and then rotating it by injecting and rotating the combustion gas of a high temperature and high pressure into the turbine.
  • positioned on the outer peripheral surface in multiple stages is used widely.
  • gas turbine blades used in this way are generally used by a film cooling method for cooling the surface, which will be described with reference to the accompanying drawings.
  • the turbine blade is formed with a plurality of membrane cooling units 7 on the turbine blade surface for cooling from the hot gas supplied to the surface.
  • the membrane cooling unit 7 includes an inlet 7a formed in a circular shape so that the cooling air supplied from the inside of the turbine blade is introduced, and an extension part extending outwardly in a symmetrical form at the extended end of the inlet 7a. (7b).
  • the inlet 7a is formed in a circular cross section when cut in cross section and viewed from the front, so that the expansion portion 7b extends at a specific diffusion angle ⁇ to supply a large amount of cooling air to the surface of the turbine blade. As the diffusion angle ⁇ is increased, a separation phenomenon occurs unevenly inside the extension part 2b.
  • the inlet 7a has a circular cross section, a hoop stress is generated, causing deformation or cracking due to stress concentration at a specific position.
  • Embodiments of the present invention can change the structure of the membrane cooling unit provided in the gas turbine blade to the ellipse shape to achieve a stable cooling for the turbine blade gas turbine that can improve the cooling efficiency for a plurality of turbine blades To provide a blade.
  • Gas turbine blades according to the first embodiment of the present invention includes a turbine blade (33) provided in the gas turbine; And a cooling unit 110 having a cooling channel 110 for cooling the turbine blade 33, an outlet portion 12 through which cooling air is discharged, and a cooling portion 110 having a plurality of ribs 130.
  • 120 extends from the longitudinally extending end of the cooling channel 110 to the outer surface of the turbine blade 33 and from one end of the cooling channel 110 toward the outer surface of the turbine blade 33. It is increased, the plurality of ribs 130, characterized in that facing each other on the inner wall of the outlet portion 120.
  • the cooling channel 110 extends toward the outlet portion 120 in the form of a circular cylinder, and the outlet portion 120 has a diffusion angle ⁇ from the rear end of the cooling channel 110 to the outside. It is characterized by extending in the form of an ellipse.
  • the diffusion angle ⁇ is characterized in that more than 15 degrees.
  • the diffusion angle ⁇ is characterized by being within 15 degrees to 40 degrees.
  • the membrane cooling unit 100 is characterized in that located on the pressure surface 33a and the suction surface 33b of the turbine blade 33, respectively.
  • the membrane cooling unit 100 may be disposed at different intervals between sections of the leading edge 34 constituting the turbine blade 330 to the trailing edge 35 to achieve membrane cooling.
  • the membrane cooling unit 100 is characterized in that each of the plurality of unit blades constituting the turbine blade 33 is provided in the first and second turbine blades.
  • the length of the cooling channel 110 extends four to eight times the diameter (D).
  • the diameter (D) is formed of 0.6mm ⁇ 1.0mm.
  • the outlet portion 120 is characterized in that the inclination angle ( ⁇ ) of the center line extending along the center in the longitudinal direction and the surface of the turbine blade 33 is 30 degrees to 40 degrees.
  • the outlet portion 120 is extended at an angle of 15 degrees to 20 degrees in both lateral directions with respect to the cooling channel 110.
  • the rib 130 has a protruding length e extending to the same length at the outlet 120.
  • the rib 130 is characterized in that the protruding length (e) gradually increases from one end of the cooling channel 110 toward the outer surface of the turbine blade (33).
  • the rib 130 has a total length from the leading end of the outlet 120 to the rear end extending from the outer surface of the turbine blade 33 to L, from the position 1/5 to L relative to the leading end. Characterized in that arranged to the rear end.
  • the rib 130 is characterized in that the polygonal pyramid shape.
  • the rib 130 has an opening hole 140 through which cooling air is introduced.
  • the opening hole 140 is characterized in that the opening toward the inner wall of the outlet portion 120.
  • the opening hole 140 is reduced in diameter from the front of the rib 130 to the rear.
  • the opening hole 140 may be opened in an ellipse shape in the width direction at the front of the rib 130 or in an ellipse shape in the vertical direction adjacent to the inner wall of the outlet part 120 at the front of the rib 130. It is formed in any one form of opening.
  • the membrane cooling unit 100 further includes a first membrane cooling unit 102 provided at the leading edge 34 of the turbine blade 33.
  • the first membrane cooling unit 102 may include a first cooling channel 102a through which cooling air passes; A first outlet portion (102b) extending from the end extending in the longitudinal direction of the first cooling channel (102a) to the outer surface of the turbine blade (33); A first rib 130a is disposed on an inner sidewall of the first outlet portion 102b and guides the cooling air to flow in a vortex form toward the first outlet portion 102b.
  • the first outlet portion 102b has a length that extends in the longitudinal direction longer than the first cooling channel 102a.
  • the first rib 130a is disposed to face each other and is formed of a C-shaped ring.
  • the first rib 130a defines a length protruding from the inside of the first outlet portion 102b as the protruding length e, and a distance between the centers of the ribs 130a spaced apart from each other. P / e is spaced within 5mm ⁇ 10mm.
  • the first ribs 130a facing each other along the longitudinal direction of the inner wall of the first outlet portion 102b are offset from each other.
  • the first rib 130a extends in the form of a spiral along the longitudinal direction of the inner wall of the first outlet portion 102b.
  • the first membrane cooling unit 102 defines an entire section of the first outlet section 102b as an extension section S, and is connected to the first cooling channel 102a to a position of 1/2 * S.
  • the section is called the first extension section S1 and the remaining section is defined as the second extension section S2
  • the separation interval between the first rib 130a positioned in the first extension section S1 and the first section are defined.
  • the separation interval of the first ribs 130a positioned in the two extension sections S2 is different from each other.
  • the first ribs 130a positioned in the first extension section S1 may have a length between the centers of the ribs 130a spaced apart from each other, compared to the first ribs 130a positioned in the second extension section S2.
  • the resulting separation pitch p is shortly spaced.
  • This embodiment provides a gas turbine in which the membrane cooling unit 100 is provided in the turbine blade 33.
  • Gas turbine blades according to a second embodiment of the present invention includes a turbine blade 330 provided in the gas turbine;
  • the first membrane cooling unit 1020 provided at the leading edge 340 for cooling the turbine blade 330, and the pressure surface 330a and the suction surface 330b of the turbine blade 330.
  • two membrane cooling units 1000 are provided.
  • the first membrane cooling unit 1020 may include a first cooling channel 1020a through which cooling air passes; Extends from the end extending in the longitudinal direction of the first cooling channel 1020a to the outer surface of the turbine blade 330 and from one end of the first cooling channel 1020a to the outer surface of the turbine blade 330.
  • a first outlet portion 1020b having an increased width;
  • a first rib 1300a disposed on an inner wall of the first outlet portion 1020b to face each other and guiding the cooling air to flow in a vortex form toward the first outlet portion 1020b.
  • the first cooling channel 1020a extends toward the first outlet portion 1020b in the form of a circular cylinder, and the first outlet portion 1020b extends outward from the rear end of the first cooling channel 1020a. Extending in an elliptical shape with a diffusion angle ⁇ .
  • the diffusion angle ⁇ is characterized in that 15 to 40 degrees.
  • the first outlet portion 1020b has a length longer than that of the first cooling channel 1020a.
  • the first rib 1300a is disposed to face each other and is formed of a C-shaped ring.
  • the first rib 1300a defines a length protruding from the inside of the first outlet portion 1020b as the protruding length e, and a distance between the centers of the ribs 1300a spaced apart from each other. P / e is spaced within 5mm ⁇ 10mm.
  • the first rib 1300a extends in the form of a spiral along the longitudinal direction of the inner wall of the first outlet portion 1020b.
  • the second membrane cooling unit 1000 may include a second cooling channel 1100 through which cooling air passes; Extending from the end extending in the longitudinal direction of the second cooling channel 1100 to the outer surface of the turbine blade 330 and toward the outer surface of the turbine blade 330 at one end of the second cooling channel 1100 A second outlet portion 1200 whose width is increased; And a plurality of second ribs 1300 facing each other on the inner wall of the second outlet portion 1200.
  • the second cooling channel 1100 extends toward the second outlet 1200 in the form of a circular cylinder, and the second outlet 1200 extends outward from the rear end of the second cooling channel 1100. It is characterized in that it extends in the form of an ellipse toward the diffusion angle ( ⁇ ).
  • the diffusion angle ⁇ is characterized by being within 15 degrees to 40 degrees.
  • the first and second membrane cooling units 1020 and 1000 may be provided in the first stage turbine blade and the second stage turbine blade, respectively, of the plurality of unit blades constituting the turbine blade 330.
  • the length of the second cooling channel 1100 extends 4 to 8 times the diameter (D).
  • the diameter (D) is formed of 0.6mm ⁇ 1.0mm.
  • the second outlet portion 1200 is characterized in that the inclination angle ( ⁇ ) of the center line extending along the center in the longitudinal direction and the surface of the turbine blade 330 is 30 degrees to 40 degrees.
  • the second outlet portion 1200 is extended at an angle of 15 degrees to 20 degrees in both lateral directions with respect to the second cooling channel 1100.
  • the present embodiment provides a gas turbine in which the first and second membrane cooling units 1020 and 1000 are provided in the turbine blade 330.
  • Gas turbine blades includes a turbine blade 330 provided in the gas turbine; A membrane cooling unit (1000A) provided on the pressure surface (330a) and the suction surface (330b) of the turbine blade (330); And a leading edge having a protrusion 2200 formed in a spiral shape inside the plurality of openings 2100 opened in the leading edge 340 for cooling the turbine blade 330 and guiding cooling air in a vortex form.
  • the leading edge cooling unit 2000 is characterized in that the opened position and direction of the opening 2100 is differently opened according to the temperature distribution state of the leading edge 340 do.
  • the opening 2100 of the leading edge cooling unit 200 is formed in any one of a cylindrical shape, an elliptic shape, or a trapezoidal shape.
  • the membrane cooling unit 1000A includes a cooling channel 1100 through which cooling air passes; Extends from the end extending in the longitudinal direction of the cooling channel 1100 to the outer surface of the turbine blade 330 and increases in width from one end of the cooling channel 1100 to the outer surface of the turbine blade 330.
  • the cooling channel 1100 extends toward the outlet portion 1200 in the form of a circular cylinder, and the outlet portion 1200 has a diffusion angle ⁇ outward from the rear end of the cooling channel 1100. It extends in an elliptic form, the diffusion angle ( ⁇ ) is characterized in that 15 degrees.
  • Embodiments of the present invention can supply cooling air stabilized in the flow flow to the surface of the turbine blade through a plurality of ribs provided in the outlet portion to minimize the peeling phenomenon.
  • Embodiments of the present invention can improve the heat transfer performance by utilizing the limited area of the membrane cooling unit to the maximum, thereby improving the cooling efficiency of the surface of the turbine blades.
  • Embodiments of the present invention can minimize the peeling or flow unevenness inside the membrane cooling unit to improve the flow safety of the cooling air.
  • FIG. 1 is a view showing a membrane cooling unit formed in a conventional turbine blade.
  • FIG. 2 is a longitudinal sectional view of a gas turbine in which a turbine blade according to the present invention is installed;
  • FIG 3 is an enlarged perspective view of the gas turbine blade and the membrane cooling unit according to the first embodiment of the present invention.
  • FIG. 4 is a perspective view showing another embodiment of the rib provided in the membrane cooling unit according to the first embodiment of the present invention.
  • 5 to 6 are diagrams showing the flow of cooling air via a rib provided in the membrane cooling unit according to the first embodiment of the present invention.
  • FIGS. 9 to 10 are views showing various embodiments of the rib according to the first embodiment of the present invention.
  • 11 to 15 are views showing various forms of the opening hole provided in the rib according to the first embodiment of the present invention.
  • FIG. 19 is a view showing another embodiment of the first membrane cooling unit according to the second embodiment of the present invention.
  • 20 to 21 are side views of a first rib provided in the first membrane cooling unit of the present invention.
  • FIG. 22 is a view showing another embodiment of a first rib provided in the first membrane cooling unit of the present invention.
  • FIG. 23 is a view showing another embodiment of the first rib disposed in the first membrane cooling unit according to the second embodiment of the present invention.
  • FIG. 24 is a perspective view showing a gas turbine blade according to a third embodiment of the present invention.
  • FIG. 25 is a view showing a machining state using a tool to process the leading edge cooling unit according to the third embodiment of the present invention.
  • 26 is a perspective view of a membrane cooling unit according to a third embodiment of the present invention.
  • the gas turbine is provided with a casing 10 forming an outline, and a diffuser for discharging the combustion gas passing through the turbine is provided at the rear side (right side of FIG. 2) of the casing 10.
  • a combustor 11 for receiving the compressed air to the front of the diffuser is combusted.
  • the compressor section 12 is located in front of the casing 10, the turbine section 30 is provided at the rear.
  • a torque tube 14 is provided between the compressor section 12 and the turbine section 30 to transmit the rotational torque generated in the turbine section 30 to the compressor section 12.
  • the compressor section 12 is provided with a plurality (for example 14) of compressor rotor disks, each of which is fastened so as not to be spaced in the axial direction by the tie rods 15.
  • the centers of the respective compressor rotor disks are aligned in the axial direction with each other while the tie rods 15 penetrate.
  • a flange coupled to a neighboring rotor disk such that relative rotation is impossible is formed to protrude in the axial direction.
  • a plurality of blades are radially coupled to the outer circumferential surface of the compressor rotor disk.
  • Each blade has a dove tail portion and is fastened to the compressor rotor disk.
  • the dovetail part may be of a tangential type and an axial type. This may be selected according to the required structure of a commercially available gas turbine. In some cases, the blade may be fastened to the rotor disk using a fastening device other than the dovetail.
  • the tie rod 15 is disposed to penetrate through the center of the plurality of compressor rotor disks, one end of which is fastened in the compressor rotor disk located at the most upstream side, and the other end of which is fixed to the torque tube.
  • the shape of the tie rod may be formed in a variety of structures depending on the gas turbine, it is not necessarily limited to the form shown in the drawings.
  • One tie rod may have a form penetrating the center portion of the rotor disk, a plurality of tie rods may be arranged in a circumferential shape, and a mixture thereof may be used.
  • the compressor of the gas turbine may be provided with a vane serving as a guide vane at the next position of the diffuser to increase the pressure of the fluid and then adjust the flow angle of the fluid entering the combustor inlet to the design flow angle.
  • a desworler This is called a desworler.
  • the combustor 11 mixes and combusts the introduced compressed air with fuel to produce a high-temperature, high-pressure combustion gas of high energy, and increases the temperature of the combustion gas to a heat-resistant limit that the combustor and turbine parts can withstand during the isostatic combustion process. .
  • a plurality of combustors constituting the combustion system of the gas turbine may be arranged in a casing formed in a cell form, the combustor may include a burner including a fuel injection nozzle, a combuster liner forming a combustion chamber, And a transition piece that is a connection part of the combustor and the turbine.
  • the liner provides a combustion space in which fuel injected by the fuel nozzle is mixed with the compressed air of the compressor and combusted.
  • a liner may include a flame barrel providing a combustion space in which fuel mixed with air is combusted, and a flow sleeve surrounding the flame barrel to form an annular space.
  • the fuel nozzle is coupled to the front end of the liner, the spark plug is coupled to the side wall.
  • the transition piece is connected to the rear end of the liner so that combustion gas combusted by the spark plug can be sent to the turbine side.
  • the transition piece is cooled by the compressed air supplied from the compressor so that the outer wall is prevented from being damaged by the high temperature of the combustion gas.
  • the transition piece is provided with holes for cooling to inject air therein, and the compressed air flows to the liner side after cooling the body therein through the holes.
  • the mechanical energy from the turbine is supplied to the compressor to compress the air, and the rest is used to drive the generator to produce power.
  • a plurality of vanes and rotor blades are alternately arranged in the vehicle compartment, and the output shaft to which the generator is connected is rotationally driven by driving the rotor blades by combustion gas.
  • the turbine section 30 is equipped with a plurality of turbine rotor disks.
  • Each turbine rotor disk basically has a form similar to the compressor rotor disk.
  • the turbine rotor disk also includes a plurality of turbine blades 33 (see FIG. 3) arranged radially with a flange provided for engagement with a neighboring turbine rotor disk.
  • the turbine blade 33 may also be coupled to the turbine rotor disk in a dovetail manner.
  • the introduced air is compressed in the compressor section 12, combusted in the combustor 11, and then moved to the turbine section 30 to drive the turbine, and through the diffuser to the atmosphere. Discharged to the air.
  • Representative of the method for increasing the efficiency of the gas turbine is to increase the temperature of the gas flowing into the turbine section 30, in which case the phenomenon that the inlet temperature of the turbine section 30 is increased.
  • Cooling air is supplied to the inside of the turbine blade 33 to compensate for the problems caused by the above-described turbine blade 33.
  • the cooling air cools while flowing along the flow path formed inside the turbine blade 33.
  • the gas turbine blade according to the first embodiment of the present invention requires stable cooling of the outer circumferential surface when hot gas is supplied to the outer circumferential surface of the turbine blade 33. .
  • the cooling of the membrane to the surface of the turbine blade 33 through the membrane cooling unit 100 that can supply the cooling air supplied into the turbine blade 33 to the outer circumferential surface of the turbine blade 33. We want to do this.
  • a plurality of membrane cooling units 100 are provided in a section from the leading edge 34 to the trailing edge 35 of the turbine blade 33.
  • the membrane cooling unit 100 is provided for cooling the membrane while cooling air is injected from the inside of the turbine blade 33 and then sprayed onto the surface.
  • the membrane cooling unit 100 extends from the end extending in the longitudinal direction of the cooling channel 110 and the cooling channel 110 through the cooling air to the outer surface of the turbine blade 33 and the cooling channel ( At one end of the 110 includes an outlet portion 120 that increases in width toward the outer surface of the turbine blade 33 and a plurality of ribs 130 facing each other on the inner wall of the outlet portion 120.
  • the outlet portion 120 has inner walls 121 and 122 facing each other therein, and a plurality of ribs 130 are disposed on the inner walls 121 and 122 as shown in the drawing.
  • the membrane cooling unit 100 mixes with the hot hot gas moving along the outer circumferential surface of the turbine blade 33 to achieve membrane cooling of the surface of the turbine blade 33.
  • the membrane cooling unit 100 may exchange heat through the surface area and stably diffuse toward the surface of the turbine blade 33 to maintain the high temperature of the hot gas. The temperature is lowered to a predetermined temperature to achieve cooling.
  • the membrane cooling unit 100 may minimize flow unevenness due to separation in the inner region of the outlet 120 when the cooling air moves to the outer circumferential surface of the turbine blade 33 through the outlet 120. It is advantageous to maintain a constant cooling efficiency.
  • the present invention is provided with ribs 130 on the inner wall (121, 122) to maintain a constant flow flow of cooling air in the outlet portion 120 is to minimize the occurrence of unstable flow flow due to peeling
  • the flow stability of the cooling air can also be improved at the same time.
  • a plurality of ribs 130 are disposed along the inner walls 121 and 122 of the outlet 120 toward the outer circumferential surface of the turbine blade 33 at regular intervals.
  • the inner walls 121 and 122 are disposed in the number shown in the drawing in a state facing each other.
  • the gaps spaced apart from each other may maintain a gap of 5e or more. Can be.
  • the spacing of the ribs 130 and the protruding length e cause heat transfer performance.
  • the spacing between the ribs 130 maintains more than 5e rather than less than 5e, thereby transferring more heat and cooling. As is advantageous, the above-described spacing intervals are maintained.
  • the protrusion length e of the rib 130 is varied according to the size of the outlet 120, it is set through a separate analysis or simulation.
  • the rib 130 When the rib 130 has the total length from the distal end portion 120a of the outlet portion 120 to the rear end portion 120b as L, the rear end portion 120b from the 1/5? L position based on the distal end portion 120a. A plurality is arranged until).
  • the flow of cooling air is kept constant compared to the rear 120b, and the peeling phenomenon is about 1/5? L spaced apart from the tip 120a toward the rear end. Since the rib 130 is disposed from the position, the flow instability due to peeling can be minimized.
  • the rib 130 has a protruding length e extending to the same length at the outlet portion 120 or at the front end portion 120a of the outlet portion 120.
  • Protruding length e may be increased toward the end portion 120b toward the center in the width direction of the outlet portion 120.
  • the outlet portion 120 has an increased area of the rear end portion 120b, and as a result, the flow flow at the center in the width direction may become unstable compared to the front end portion 120a, so that the protruding length of the rib 130 may be Increasing) may lead to a stable flow of cooling air.
  • One end of the cooling channel 110 is connected to the inside of the turbine blade 33 so that cooling air is introduced, and the other end extends toward the outside of the turbine blade 33 and is formed in a circular cross-sectional shape, but is formed in an ellipse shape. It may also be possible.
  • the outlet portion 120 has a diffusion angle ⁇ at the rear end of the cooling channel 110 and extends in an ellipse shape in the width direction.
  • the cooling channel 110 extends toward the outlet portion 120 in the form of a circular cylinder, and the diffusion angle ⁇ is maintained at an angle of 15 degrees or more.
  • the diffusion angle is maintained at the aforementioned angle in order to suppress the occurrence of unnecessary peeling phenomenon and induce a stable movement before the cooling air moving along the outlet 120 is moved to the surface of the turbine blade 33.
  • the cooling channel 110 may induce a membrane cooling effect by stably inducing the flow of cooling air in an optimal state in the diffusion angle ⁇ within a range of 15 degrees to 40 degrees.
  • the present embodiment reduces the peeling phenomenon generated by the movement of the cooling air through the plurality of ribs 130 along with the diffusion angle and constantly induces the flow of cooling air moving along the inner center of the outlet portion 120. can do.
  • the outlet portion 120 has ribs 130 positioned on the inner walls 121 and 122, respectively, and is symmetrically disposed with respect to the center in the width W direction.
  • the moving speed may be lowered at the inner walls 121 and 122, and thus peeling may occur. Is placed.
  • the cooling air is most preferably made of a uniform flow flow when moving in the inner region of the outlet 120, the outlet 120 has a moving speed of the cooling air in the inner wall (121, 122) Since it is kept close to zero, the movement speed and viscosity of the cooling air moved to the inner walls 121 and 122 and the movement speed and viscosity of the cooling air moving along the center of the width direction W are generated.
  • the cooling air moving along the center in the width direction does not move straight forward from the inside of the outlet part 120 but moves toward the relatively slow inner walls 121 and 122. While peeling phenomenon may occur.
  • the present invention is provided with a rib 130 to minimize this peeling phenomenon.
  • the present invention is to install a rib 130 on the inner wall (121, 122) in order to minimize the peeling occurring in the inner region of the outlet portion 120,
  • the rib 130 causes an eddy phenomenon in which a small vortex occurs when the cooling air passes through the rib 130.
  • the eddy phenomenon may prevent undesired peeling of the cooling air moving along the inner walls 121 and 122 of the outlet 120, thereby achieving stable movement of the cooling air.
  • the heat transfer performance is also improved to improve the overall cooling performance for the turbine blade (33).
  • the flow of cooling air is tested through a computational fluid simulation (also known as CFD) in which cooling air moves along the inner region of the outlet 120 to the surface of the turbine blade 33. As shown in the figure.
  • CFD computational fluid simulation
  • the eddy phenomenon causes a small vortex in the cooling air in the inner walls 121 and 122, unlike the peeling phenomenon which causes a considerably large vortex flow in the cooling air, which causes an influence on the overall flow flow of the cooling air.
  • the flow direction of the cooling air is guided to the width direction center of the outlet portion 120 in the form as shown in the figure on the inner walls 121 and 122 instead of the flow flow.
  • the cooling air is a small vortex is generated around the ribs 130, it can be seen that the degree of swirl is weakened between the spaced ribs 130.
  • a plurality of ribs 130 are provided on the inner walls 121 and 122 in order to use the eddy phenomenon, and the uniform cooling air flows in the width direction center at the inside of the outlet 120.
  • the heat transfer performance may also be improved at the same time while the cooling air moves.
  • the membrane cooling unit 100 is located at the pressure surface 33a and the suction surface 33b of the turbine blade 33, respectively, and the position is at a position where the hot gas is moved along the surface of the turbine blade 33. Yes.
  • the pressure surface 33a and the suction surface 33b are stably maintained as the cooling effect of the cooling air moves along the surface of the turbine blade 33 as shown by the arrows, thereby maintaining the film cooling of the turbine blade 33. Can be planned.
  • the membrane cooling unit 100 is disposed at different intervals between sections of the leading edge 34 constituting the turbine blade 33 to the trailing edge 35 to achieve membrane cooling. can do.
  • the membrane cooling unit 100 is a plurality of concentrated in the section that is maintained at a high temperature in the pressure surface (33a) and the suction surface (33b) of the turbine blade 33, the number is arranged in a section maintained at a relatively low temperature Can be reduced.
  • the membrane cooling unit 100 is provided in each of the first and second turbine blades of the plurality of unit blades constituting the turbine blade 33, the first and second turbine blades of the high temperature via the combustor Corresponds to the location where contact with the hot gas occurs either directly or indirectly.
  • the cooling state may be different according to the movement trajectory and the temperature distribution of the hot gas moving along the pressure surface 33a and the suction surface 33b.
  • the pressure surface 33a and the suction surface It is possible to improve the film cooling effect on the surface of the turbine blade 33 by making arrangement intervals or distribution different from 33b).
  • the turbine blade 33 can improve the film cooling effect on the surface in contact with the hot hot gas, it is possible to prevent deformation even in long-term use.
  • the membrane cooling unit 100 is largely composed of a cooling channel 110 and an outlet 120, and the cooling channel 110 has a length of 4D ⁇ depending on the diameter D. It can extend to a length within 8D.
  • the diameter (D) is formed as an example 0.6mm ⁇ 1.0mm, but is not necessarily limited to the above-described dimensions can be variously changed according to the specifications of the gas turbine.
  • the membrane cooling effect of the turbine blade 33 may be maximized.
  • the stable heat transfer performance effect can be maintained.
  • the cooling channel 110 may extend to a maximum of 4.8mm, but the cooling channel 110 is not necessarily limited to the above-mentioned value when maintaining the length ratio of 4 times to 8 times the length according to the diameter (D).
  • the outlet portion 120 maintains an inclination angle ⁇ between the center line extending along the center of the longitudinal direction and the surface of the turbine blade 33 is 30 degrees to 40 degrees.
  • the length of the cooling channel 110 may be unnecessarily longer.
  • the inclination angle is greater than the above-described angle, it may not be sprayed onto the surface of the turbine blade 33 or only a portion thereof may be moved toward the surface, which may cause a stable film cooling effect of the turbine blade 33 only when the aforementioned inclination angle is maintained. have.
  • the outlet portion 120 is inclined at an angle of 15 degrees to 20 degrees inclined angle ⁇ in both lateral directions with respect to the cooling channel 110.
  • the diffusion angle at which the cooling air is injected toward the surface of the turbine blade 33 may vary according to the angle of expansion of the outlet 120. The above-described angle optimally optimizes the membrane cooling effect on the surface of the turbine blade 33. It is an angle that can be maintained.
  • the outlet portion 120 may be configured at an angle of at least 15 degrees and up to 20 degrees to spray cooling air to the surface of the turbine blade 33 to maintain the membrane cooling effect to the maximum, thereby achieving efficient cooling.
  • the ribs 130 may be formed of a polyhedron as an example, and the vertices may be kept larger than zero degrees and smaller than right angles.
  • the polyhedron is not particularly limited to a specific polyhedron, but a polyhedron in which stable eddy phenomenon is induced through the above CFD analysis is used. That is, the rib 130 is configured in the shape of a polygonal pyramid.
  • the heat transfer performance can be improved by increasing the contact area with the cooling air.
  • the rib may be formed in a cuboid shape, in which case the vertex is maintained at an angle of 90 degrees.
  • the reason why the vertices are formed at this angle is that they are advantageous over circular or rounded shapes when intentionally inducing small swirls in the cooling air.
  • the turbine blade may include the ribs such that cooling air is supplied to the plurality of ribs 130 disposed spaced apart from the side walls 121 and 122 facing each other inside the outlet 120.
  • An opening hole 140 opened in front of the 130 is formed.
  • the opening holes 140 are formed in the ribs 130 to guide the moving direction of the cooling air, thereby simultaneously improving the stable flow flow and heat transfer performance of the cooling air.
  • the opening hole 140 is opened toward the sidewalls 121 and 122 of the outlet 120.
  • the opened area of the opening hole 140 may be opened to an optimized size through a separate simulation or flow analysis.
  • the opening hole 140 may be supplied with a predetermined amount of cooling air to the side walls 121 and 122 because the opened position is opened toward the side walls 121 and 122. In this case, the opening holes 140 may be supplied to the side walls 121 and 122. The heat transfer efficiency can be improved by the cooling air.
  • the cooling air when the cooling air is moved to the side walls 121 and 122, the cooling air circulates in the region between the spaced ribs 130 and moves toward the ribs 130 after heat transfer is performed, and a small vortex generated in the ribs 130 is generated. Mixed into the flow.
  • an eddy phenomenon occurs that causes a small eddy flow.
  • the eddy phenomenon causes a small vortex in the cooling air in the inner walls 121 and 122, unlike the peeling phenomenon which causes a considerably large vortex flow in the cooling air.
  • the vortex directs the flow direction of the cooling air in the width direction center of the outlet portion 120 in the inner wall (121, 122) rather than the flow flow that affects the overall flow flow of the cooling air.
  • the cooling air generates a small vortex around the ribs 130, and the degree of swirl is weakened between the spaced ribs 130.
  • a plurality of ribs 130 are disposed on the inner walls 121 and 122 in order to use the eddy phenomenon, and the uniform cooling air flows in the width direction center in the outlet 120. By inducing the flow to minimize the peeling phenomenon that can be generated unnecessarily due to the specific diffusion angle can guide the flow of the stable cooling air flow.
  • the small vortex generated in the rib 130 and the cooling air through the opening hole 140 are mixed with each other and then directed toward the turbine blade along a constant flow flow moving along the widthwise center of the outlet 120. Is moved.
  • the opening hole 140 maintains a constant diameter from the front of the rib 130 toward the rear. In this case, the amount of air moving toward the inner walls 121 and 122 is kept constant.
  • the opening hole 140 may have an opening area that increases toward the rear end portion 120b of the outlet portion 120.
  • the opening hole 140 arranges the position at which the cooling air is discharged toward the inner walls 121 and 122.
  • the cooling air is diffused toward the inner walls 121 and 122, a larger amount of cooling air is moved toward the inner walls 121 and 122 than the opening holes having a predetermined size. Therefore, the heat transfer efficiency at the inner walls 121 and 122 can be improved, thereby improving the cooling performance of the turbine blades.
  • the opening hole 140 may be opened in an elliptical shape in the width direction at the front of the rib 130.
  • a large amount of cooling air can be supplied to the inner walls 121 and 122 by utilizing the limited height of the membrane cooling unit 100 to the maximum, thereby improving heat transfer efficiency.
  • One or a plurality of opening holes 140 are opened, and the size of the opening holes 140 is not particularly limited.
  • the opening hole 140 is opened in an elliptical shape in a vertical direction adjacent to the side walls 121 and 122 of the outlet part 120 at the front of the rib 130. Can be.
  • the opening hole 140 may be configured in plural, and since the opened area is increased, cooling air may be stably supplied toward the inner walls 121 and 122.
  • the cooling air may be guided in a moving direction toward the inner walls 121 and 122, thereby improving heat transfer efficiency.
  • the diameter of the opening hole 140 according to the present embodiment may be reduced from the front side of the rib 130 toward the rear side.
  • the cooling air moves to the spaced space where the rib 130 is spaced while the flow velocity is increased while passing through the opening hole 140.
  • the cooling air is moved toward the rib 130 after being moved faster than the moving speed of the cooling air moving at the central position in the width direction of the outlet 120. After mixing with the small vortex flow generated in the rib 130, it is stably moved toward the rear end 120b of the outlet 120.
  • the membrane cooling unit 100 further includes a first membrane cooling unit 102 provided at the leading edge 34 of the turbine blade 33.
  • the first membrane cooling unit 102 is configured in a part similar to the membrane cooling unit 100 described above, but differently configured in detail.
  • the first membrane cooling unit 102 includes a first cooling channel 102a through which cooling air passes, and an end extending in the longitudinal direction of the first cooling channel 102a to an outer surface of the turbine blade 33.
  • the first outlet portion 102b has inner walls 102c and 102d facing each other therein, and a plurality of first ribs 130a are illustrated in the inner walls 102c and 102d. Are arranged together.
  • the first membrane cooling unit 102 is provided on the leading edge 34 of the outer circumferential surface of the turbine blade 33 to achieve film cooling of the surface of the leading edge 34 in contact with the hot hot gas.
  • the first membrane cooling unit 102 is stable toward the surface of the leading edge 34 of the turbine blade 33 and the heat exchange through the surface area when cooling air is supplied through the first outlet 102b. While spreading, the high temperature of the hot gas is lowered to a predetermined temperature to achieve cooling.
  • the first membrane cooling section 102 separates in the inner region of the first outlet section 10b when cooling air moves through the first outlet section 102b to the leading edge 34 of the turbine blade 33. Flow non-uniformity caused by) can be minimized, which is advantageous for maintaining a constant cooling efficiency.
  • the present invention is provided with the first rib (130a) on the inner wall (102c, 102d) so that the flow of cooling air is maintained in the interior of the first outlet (102b), unstable flow flow due to peeling occurs It can be minimized to improve the flow stability of the cooling air at the same time.
  • the first rib 130a extends in a spiral form along the inner walls 102c and 102d of the first outlet portion 102b.
  • the reason why the first rib 130a extends as described above is to guide the cooling air to move helically along the first outlet 102b toward the surface of the turbine blade 33.
  • the first rib 130a is disposed to face each other and is formed of a C-shaped ring.
  • a portion of the cooling air flows along the inner walls 102c and 102d, and the c-shaped shape of the first rib 130a A second flow is generated that moves along.
  • the cooling air is sprayed toward the surface of the turbine blade 33 after moving toward the turbine blade 33 in a spiral vortex form.
  • the cooling air maintains the flow flow in close contact with the inner walls 102c and 102d of the first outlet portion 102b and the unstable flow flow due to the peeling flow is suppressed in the inner walls 102c and 102d.
  • the flow of the cooling air may be induced in a spiral vortex through the first rib 130a, as shown in the drawing at the first outlet portion 102b in which the major movement of the cooling air is made.
  • the flow flow can be altered to allow efficient cooling at the leading edge 34 where hot temperature conditions are maintained.
  • leading edge 34 corresponds to a position where the hot hot gas makes initial contact, cooling through film cooling may become unstable, or the surface temperature of the leading edge 34 may increase rapidly due to the hot hot gas. Can be.
  • This embodiment improves the overall cooling performance of the turbine blade 33 through stable cooling of the leading edge 33 and the cooling air through the first membrane cooling unit 102 provided at the leading edge 34. It is possible to guide the flow in the form of a spiral to reduce the occurrence of peeling and to perform stable cooling of the turbine blade 33.
  • the first outlet portion 102b may extend longer than the first cooling channel 102a in the longitudinal direction. The reason why the length of the first outlet portion 102b is extended in this way is to increase the rotational force of the cooling air, which is advantageous for maintaining spiral spiral flow on the surface of the turbine blade 33.
  • the length of the first outlet 102b is shorter than the length of the first cooling channel 102a, it may be difficult for the cooling air to maintain spiral flow in the spiral form.
  • the length of the first outlet portion 102b extends longer than the first cooling channel 102a as shown in the drawing, so that the cooling air passes through the plurality of first ribs 130a. Spiral rotational force is generated stably.
  • the cooling air can be stably maintained even when spiral vortex flow is injected onto the surface of the turbine blade 33.
  • the first rib 130a is disposed to face each other and is formed of a C-shaped ring.
  • the reason why the first rib 130a is configured as described above is advantageous in that the first rib 130a is formed in a ring shape or a c-shape in order to maintain a spiral flow of cooling air.
  • the first rib 130a may be formed in a ring shape, but when the inner region of the first outlet portion 102b is narrow, it may be preferable that the first rib 130a is formed in a c shape shown in the drawing for easier processing. But it is not necessarily limited to the form shown in the drawings.
  • it may be configured by variously changing to another form that can easily change the moving flow of cooling air in the form of a spiral.
  • a plurality of first ribs 130a are disposed along the inner walls 102c and 102d of the first outlet portion 102b at regular intervals.
  • the inner walls 102c and 102d are disposed in the number shown in the figure in a state facing each other.
  • the first rib 130a protrudes from the inner walls 102c and 102d with a protruding length e toward a center (inner center of the first outlet portion), and each of the first ribs 130a has a separation pitch ( p) and spaced apart from each other.
  • the length of the first rib 130a protruding from the inside of the first outlet 102b is defined as the protruding length e, and the length between the centers of the ribs 130a spaced apart from each other.
  • the separation pitch p When defined as the separation pitch p, the p / e may be spaced within 5mm ⁇ 10mm.
  • the p / e spaced apart by at least 5 mm may induce a stable movement of the cooling air and a moving flow in the form of a bare shape. If the interval smaller than the aforementioned interval is maintained, the flow safety of the cooling air may be deteriorated.
  • the embodiment includes the above-described embodiment in which the p / e is spaced at intervals of up to 10 mm, and the protrusion length e or the separation pitch p is varied as described above. Spaced apart.
  • the first ribs 130a may be offset from each other along the longitudinal direction of the inner wall of the first outlet portion 102b.
  • the cooling air may be more advantageous for maintaining the helical flow of cooling air.
  • the first rib 130a may be disposed to be orthogonal to the first outlet portion 102b when viewed from the side.
  • the first rib 130a may have a c shape and may be inclined at a first inclination angle ⁇ 1 when viewed from the side.
  • the reason why the first rib 130a is inclined at the first inclination angle is that the cooling air and the first rib 130a are perpendicular to each other when the moving direction is guided after the cooling air is first contacted with the first rib 130a. Contact with.
  • the first rib 130a is disposed to be inclined at a first inclination angle ⁇ 1 to induce cooling air not to be in contact with the first rib 130a at a right angle.
  • ⁇ 1 first inclination angle
  • some of the cooling air is moved forward, and some of the cooling air is moved in a spiral moving flow, thereby reducing the impact loss, thereby improving rotational force.
  • the first membrane cooling unit 102 defines an entire section of the first outlet section 102b as an extension section S, and from the position connected to the first cooling channel 102a.
  • the first rib section 130a positioned in the first extension section S1 is defined as a section extending to 1/2? S as a first extension section S1 and the remaining section is defined as a second extension section S2.
  • the separation interval of) and the separation interval of the first rib 130a positioned in the second extension section S2 may be different from each other.
  • the first extension section S1 and the second extension section S2 have a first outlet portion 102b having a length limited to a section in which spiral rotational force is generated by the first rib 130a when cooling air is introduced.
  • the separation interval of the first rib 130a is configured differently.
  • first rib 130a disposed in the first extension section S1 may have a length between the centers of the ribs 130a spaced apart from each other than the first rib 130a disposed in the second extension section S2.
  • the spacing pitch p can thus be shortened.
  • the cooling air introduced into the first outlet 102b may have a rotational force generated through the plurality of first ribs 130a in the first extension section S1 in the second extension section S2. It is generated larger than the rotational force.
  • the membrane cooling unit 100 may be simultaneously formed by casting during the turbine blade 33 molding. In the case of casting processing, since the precise molding is possible, easy molding of the plurality of ribs 130 or the first ribs 130a is possible.
  • the film cooling unit 100 may be processed by any one of an electric discharge machining method, a three-dimensional printer method, or laser processing.
  • the membrane cooling unit 100 may be installed in a gas turbine provided in the turbine blade 33, and in this case, the cooling efficiency of the turbine blade 33 by the hot gas may be stably maintained and the membrane cooling may be performed. The cooling effect by this can be improved.
  • a turbine blade 330 provided in a gas turbine, a first membrane cooling unit 1020 and a turbine blade provided at a leading edge 340 for cooling the turbine blade 330.
  • a second membrane cooling unit 1000 provided on the pressure surface 330a and the suction surface 330b of the 330.
  • the first and second membrane cooling units 1020 and 1000 mix with the hot hot gas moving along the outer circumferential surface of the turbine blade 330 to achieve membrane cooling of the surface of the turbine blade 330.
  • the first and second membrane cooling units 1020 and 1000 may heat exchange through a surface area when the cooling air is supplied, and stably diffuse the high temperature of the hot gas to the surface of the turbine blade 330 at a predetermined temperature. It is lowered to achieve cooling.
  • the first and second membrane cooling units 1020 and 1000 have the first outlet portion when the cooling air moves to the outer circumferential surface of the turbine blade 330 through the first outlet portion 1020b and the second outlet portion 1200 which will be described later. Flow unevenness due to separation in the inner region of the 1020b and the second outlet 1200 may be minimized, which is advantageous in maintaining a constant cooling efficiency.
  • first rib 1300a and the second rib 1200 are respectively provided to maintain a constant flow of cooling air inside the first outlet portion 1020b and the second outlet portion 1200. It is possible to minimize the occurrence of an unstable flow flow due to the separation and to improve the flow stability of the cooling air at the same time.
  • the first membrane cooling unit 1020 extends from the end extending in the longitudinal direction of the first cooling channel 1020a through which the cooling air passes and the first cooling channel 1020a to the outer surface of the turbine blade 330.
  • a first outlet portion 1020b is formed which extends and increases in width from one end of the first cooling channel 1020a to the outer surface of the turbine blade 330.
  • first rib (1300a) facing each other on the inner wall of the first outlet (1020b) and guides the cooling air flow in a vortex form toward the first outlet (1020b). do.
  • the first cooling channel 1020a extends toward the first outlet portion 1020b in the form of a cylinder in a circle or an ellipse, and the first outlet portion 1020b is formed in the first cooling channel 1020a. It extends in the shape of an ellipse with a diffusion angle ⁇ from the rear end toward the outside.
  • a plurality of the first ribs 1300a are disposed along the inner walls 1021c and 1022d of the first outlet portion 1020b toward the outer circumferential surface of the turbine blade 330 at regular intervals.
  • the inner walls 1021c and 1022d are disposed in the number shown in the figure in a state facing each other.
  • the spaced apart from each other is 5e. The above interval can be maintained.
  • the spacing of the first rib 1300a and the protruding length e cause heat transfer performance, and the heat between the first ribs 1300a is maintained more than 5e than if the spaced distance between the first ribs 1300a is within 5e. It is advantageous for cooling by transmitting the above-mentioned separation interval is maintained.
  • the p / e is spaced at least 5 mm apart.
  • the p / e spaced apart by at least 5 mm may induce a stable movement of the cooling air and a moving flow in the form of a bare shape. If the interval smaller than the aforementioned interval is maintained, the flow safety of the cooling air may be deteriorated.
  • the length of the first rib 1300a protruding from the inside of the first outlet portion 1020b is defined as the protruding length e, and the length between the centers of the ribs 130a spaced apart from each other.
  • the separation pitch p When defined as the separation pitch p, the p / e may be spaced within 5mm ⁇ 10mm.
  • the embodiment includes the above-described embodiment in which the p / e is spaced at intervals of up to 10 mm, and the protrusion length e or the separation pitch p is varied as described above. Spaced apart.
  • the total length from the distal end portion 1020aa to the rear end portion 1020bb of the first outlet portion 1020b is 1/5 to L from the position of the distal end portion 1020aa.
  • a plurality of rear ends 1020bb are arranged.
  • the first outlet portion 1020b maintains a constant flow of cooling air compared to the rear end portion 1020bb, and the peeling phenomenon is separated from the front end portion 1020aa toward the rear end portion 1020bb. Since it starts around the 5L position, when the first rib 1300a is disposed from the position, flow instability due to peeling can be minimized.
  • the protruding length e extends from the first outlet portion 1020b to the same length, or the rear end portion 120a of the front end portion 120a of the first outlet portion 1020b.
  • the protrusion length e may increase toward the center in the width direction of the first outlet portion 1020b toward 120b).
  • One end of the first cooling channel 1020a is connected to the inside of the turbine blade 330 to allow cooling air to flow in, and the other end of the first cooling channel 1020a extends toward the outside of the turbine blade 330 and has a circular cross-sectional shape. It may also be possible to form.
  • the first outlet portion 1020b has a diffusion angle ⁇ at the rear end portion of the first cooling channel 1020a and extends in an ellipse shape in the width direction.
  • the first cooling channel 1020a extends toward the first outlet portion 1020b in the form of a circular cylinder, and the diffusion angle ⁇ is maintained at an angle of 15 degrees or more.
  • the diffusion angle is maintained as described above to suppress the occurrence of unnecessary peeling phenomenon and induce stable movement before the cooling air moving along the first outlet portion 1020b is moved to the surface of the turbine blade 330. .
  • the diffusion angle ⁇ may stably induce a moving flow of cooling air in an optimal state within a range of 15 degrees to 40 degrees, thereby inducing a membrane cooling effect.
  • the first ribs 1300a are positioned on the inner walls 1021c and 1022d, respectively, and are symmetrically disposed with respect to the center of the width W direction. As the cooling air moves along the inner region of the first outlet portion 1020b, the moving speed may decrease in the inner walls 1021c and 1022d, and this may cause a peeling phenomenon. 1300a is disposed.
  • Cooling air is moved along a constant diameter of the first cooling channel 1020a when moving in the inner region of the first outlet portion 1020b and then moved to the first outlet portion 1020b to the inner walls 1021c and 1022d. Peeling may occur.
  • a uniform flow flow occurs when the cooling air moves in the inner region of the first outlet portion 1020b, but the first outlet portion 1020b is cooled air in the inner walls 1021c and 1022d. Since the moving speed of is maintained near zero, the moving speed and viscosity of the cooling air moved to the inner walls 1021c and 1022d and the moving speed and viscosity of the cooling air moving along the center of the width direction W are different. May occur.
  • the present invention is provided with a first rib 1300a in order to minimize such peeling phenomenon.
  • the present invention provides a first rib (1300a) to the inner wall (1021c, 1022d) in order to minimize the peeling occurring in the inner region of the first outlet portion (1020b), by the first rib (1300a)
  • a eddy phenomenon occurs in which a small vortex is generated.
  • the eddy phenomenon can prevent undesired peeling of the cooling air moving along the inner walls 1021c and 1022d of the first outlet portion 1020b, thereby achieving stable movement of the cooling air.
  • heat transfer performance may be improved to improve overall cooling performance of the turbine blade 330.
  • the first membrane cooling unit 1020 is provided on the leading edge 340 of the outer circumferential surface of the turbine blade 330 to cool the surface of the leading edge 340 in contact with the hot gas.
  • the first membrane cooling unit 1020 is stable toward the surface of the leading edge 340 of the turbine blade 330 and the heat exchange through the surface area when the cooling air is supplied through the first outlet 1020b. While spreading, the high temperature of the hot gas is lowered to a predetermined temperature to achieve cooling.
  • the first membrane cooling unit 1020 is separated in an inner region of the first outlet portion 1020b when the cooling air moves through the first outlet portion 1020b to the leading edge 340 of the turbine blade 330. Flow non-uniformity caused by) can be minimized, which is advantageous for maintaining a constant cooling efficiency.
  • the present invention is provided with a first rib (1300a) in the inner wall (1021c, 1022d) to maintain a constant flow flow of cooling air in the first outlet (1020b) is generated unstable flow flow due to peeling It can be minimized to improve the flow stability of the cooling air at the same time.
  • the first rib 1300a extends in a spiral form along the inner walls 1021c and 1022d of the first outlet portion 1020b.
  • the reason why the first rib 1300a extends as described above is to guide the cooling air to move helically along the first outlet portion 1020b toward the surface of the turbine blade 330.
  • the first rib 1300a may be disposed to face each other and have a C-shaped ring.
  • the first flow in which some cooling air moves along the inner walls 1021c and 1022d, and the c-shaped shape of the first rib 1300a A second flow is generated that moves along.
  • the cooling air is sprayed toward the surface of the turbine blade 330 after being moved toward the turbine blade 330 in a spiral vortex form.
  • the cooling air maintains the flow flow in close contact with the inner walls 1021c and 1022d of the first outlet portion 1020b and the unstable flow flow due to the peeling flow is suppressed in the inner walls 1021c and 1022d.
  • the flow of cooling air may be induced in a spiral vortex through the first rib 1300a, as shown in the drawing at the first outlet portion 1020b in which the main movement of the cooling air is made.
  • the flow flow can be altered to allow efficient cooling at the leading edge 340 where high temperature conditions are maintained.
  • leading edge 340 corresponds to a position where the hot hot gas makes initial contact, cooling through film cooling becomes unstable, or the surface temperature of the leading edge 340 is rapidly increased due to the hot hot gas. Can be.
  • the present embodiment improves the overall cooling performance of the turbine blade 330 through stable cooling of the leading edge 33 and provides cooling air through the first membrane cooling unit 1020 provided at the leading edge 340. By guiding the flow in the form of a spiral to reduce the occurrence of peeling can be carried out a stable cooling of the turbine blade 330.
  • the first outlet portion 1020b may extend longer in the longitudinal direction than the first cooling channel 102a. The reason why the length of the first outlet portion 1020b is extended in this way is to increase the rotational force of the cooling air, which is advantageous in maintaining spiral spiral flow on the surface of the turbine blade 330.
  • the length of the first outlet portion 1020b is shorter than the length of the first cooling channel 102a, it may be difficult for the cooling air to maintain spiral flow in the spiral form.
  • the cooling air passes through the plurality of first ribs 1300a, the spiral-shaped rotational force is stably generated. Therefore, the cooling air may be stably maintained even when spiral spiral flow is injected onto the surface of the turbine blade 330.
  • the first rib 1300a may be disposed to face each other and have a C-shaped ring.
  • the reason why the first rib 1300a is configured as described above is advantageous in that the first rib 1300a is formed in a ring shape or a c-shape to maintain a spiral flow of cooling air.
  • the first rib 1300a may be configured in a ring shape, but when the inner region of the first outlet portion 1020b is narrow, it may be preferable that the first rib 1300a is configured in a c shape as shown in the figure for easier processing. But it is not necessarily limited to the form shown in the drawings.
  • it may be configured by variously changing to another form that can easily change the moving flow of cooling air in the form of a spiral.
  • the second membrane cooling unit 1000 includes a second cooling channel 1100 through which cooling air passes, and an end of the turbine blade 330 at an end extending in the longitudinal direction of the second cooling channel 1100.
  • a second outlet portion 1200 and an inner wall of the second outlet portion 1200 extending to an outer surface and increasing in width from one end of the second cooling channel 1100 to the outer surface of the turbine blade 330. It includes a plurality of second ribs 1300 facing each other in the.
  • the second membrane cooling unit 1000 is provided for cooling the pressure surface 330a and the suction surface 330b of the turbine blade 330 to minimize peeling occurring in the inner region of the second outlet 1200.
  • Eddy phenomenon in which a second rib 1300 is installed on the inner walls 1210 and 1220 and a small vortex is generated when the cooling air passes through the second rib 1300 by the second rib 1300. (eddy phenomenon)
  • the eddy phenomenon may prevent undesired peeling of the cooling air moving along the inner walls 1210 and 1220 of the second outlet 1200, thereby achieving stable movement of the cooling air.
  • heat transfer performance may be improved to improve overall cooling performance of the turbine blade 330.
  • the eddy phenomenon may cause a small vortex in the cooling air in the inner walls 1210 and 1220, unlike the peeling phenomenon which causes a considerably large vortex flow in the cooling air.
  • the vortex directs the flow direction of the cooling air in the width direction center of the second outlet portion 1200 in the inner walls 1210 and 1220 rather than the flow flow that affects the overall flow flow of the cooling air.
  • a plurality of second ribs 1300 are provided on the inner walls 1210 and 1220 to use the eddy phenomenon described with reference to FIGS. It is possible to guide the stable flow of cooling air by minimizing the peeling phenomenon that can be unnecessarily caused by the specific diffusion angle by inducing the flow of the uniform cooling air at
  • the heat transfer performance may be simultaneously improved while the cooling air moves.
  • the second membrane cooling unit 1000 is located at the pressure surface 330a and the suction surface 330b of the turbine blade 330, respectively, where the hot gas is moved along the surface of the turbine blade 330. Corresponds to the location.
  • the pressure surface 330a and the suction surface 330b may maintain the membrane cooling effect stably as the cooling air moves along the surface of the turbine blade 330, thereby achieving cooling of the turbine blade 330.
  • the second membrane cooling unit 1000 is disposed at different intervals between sections of the leading edge 340 constituting the turbine blade 330 to the trailing edge 350 to cool the membrane. Can be planned.
  • the second membrane cooling unit 1000 is disposed in a plurality of sections concentrated at a high temperature on the pressure surface 330a and the suction surface 330b of the turbine blade 330, and disposed in a section maintained at a relatively low temperature. The number is reduced.
  • the second membrane cooling unit 1000 is provided in each of the first stage turbine blades and the second stage turbine blades of the plurality of unit blades constituting the turbine blade 330, wherein the first and second stage turbine blades pass through a combustor. Corresponds to the point where contact with the hot hot gas occurs, directly or indirectly.
  • the cooling state may be different according to the movement trajectory and the temperature distribution of the hot gas moving along the pressure surface 330a and the suction surface 330b.
  • the pressure surface 330a and the suction surface It is possible to improve the membrane cooling effect on the surface of the turbine blade 330 by different arrangement intervals or distribution in the 330b.
  • the turbine blade 330 can prevent deformation even when used for a long time because the membrane cooling effect on the surface in contact with the hot gas is improved.
  • the second membrane cooling unit 1000 may be largely composed of a second cooling channel 1100 and an outlet 1200, and the second cooling channel 1100 may extend 4 to 8 times the diameter in length.
  • the diameter (D) is formed as an example 0.6mm ⁇ 1.0mm, but is not necessarily limited to the above-described dimensions can be variously changed according to the specifications of the gas turbine.
  • the second outlet portion 1200 maintains an inclination angle ⁇ between the center line extending along the center in the longitudinal direction and the surface of the turbine blade 330 within 30 degrees to 40 degrees.
  • the length of the cooling channel 110 may be unnecessarily long.
  • the inclination angle is greater than the above-described angle, it may not be sprayed to the surface of the turbine blade 330 or only a portion thereof may be moved toward the surface, which may cause the film cooling effect of the stable turbine blade 330 only when the inclination angle is maintained. have.
  • the second outlet portion 1200 is extended at an angle of 15 degrees to 20 degrees in both lateral directions with respect to the second cooling channel 1100.
  • the diffusion angle at which the cooling air is injected toward the surface of the turbine blade 330 may vary according to the angle of expansion of the second outlet portion 1200. The above-described angle may affect the cooling effect on the surface of the turbine blade 330. It corresponds to the angle that can be optimally maintained.
  • the second outlet portion 1200 may be configured at an angle of at least 15 degrees and up to 20 degrees, thereby spraying cooling air to the surface of the turbine blade 330 to maintain the maximum membrane cooling effect, thereby achieving efficient cooling.
  • the first and second membrane cooling units 1020 and 1000 are provided in the turbine blade 330 to improve the efficiency of the gas turbine through stable cooling by high temperature hot gas.
  • the present embodiment includes a turbine blade 330 provided in a gas turbine, and a membrane cooling provided in the pressure surface 330a and the suction surface 330b of the turbine blade 330.
  • a protrusion 2200 is formed in a spiral shape inside the plurality of openings 2100 opened at the leading edge 340 to cool the part 1000A and the turbine blade 330 to guide cooling air in a vortex form. It includes a leading edge cooling unit 2000 provided.
  • leading edge cooling unit 2000 is characterized in that the opened position and the direction of the opening 2100 is opened differently according to the temperature distribution state of the leading edge 340.
  • the configuration of the membrane cooling unit 1000A is similar and stable cooling of the leading edge 340 of the turbine blade 330 through the leading edge cooling unit 2000 is different from the first and second embodiments described above. Through this to improve the cooling efficiency of the gas turbine.
  • cooling air is injected to the surface to achieve cooling, or the opening edge and the opening position of the opening 2100 are different from each other so that the leading edge is different.
  • the opening 2100 of the leading edge cooling unit 2000 may have any one of a cylindrical shape, an elliptic shape, and a trapezoidal shape.
  • the cooling air may perform film cooling on the surface of the leading edge 340 at a flow rate proportional to the diameter thereof.
  • the leading edge cooling unit 2000 is maintained at a predetermined diameter in the longitudinal direction toward the opening 2100 in the turbine blade 330, the projection 2200 is maintained at a predetermined interval.
  • the protrusion 2200 may be simultaneously formed at the time of processing the opening 2100 by tapping, in which case the opening direction of the opening 2100 may be inclined at a specific angle.
  • Tapping is a machining method used to process female screws such as nuts, and the processing method is easy and the machining operation for the leading edge cooling unit 200 directly with respect to the leading edge 340 by machining or a manual operation by an operator. Can be carried out.
  • leading edge cooling unit 2000 such as the leading edge 340 of the turbine blade 330 can be easily processed to improve the work efficiency and mass production.
  • the leading edge cooling unit 2000 is a projection 2200 is formed along the inner longitudinal direction, the projection 2200 is formed at the same time through the tapping process can be easily formed unlike the casting method or laser processing method.
  • the protrusions 2200 may be spaced apart according to a tool 6 mounted at the time of tapping, and may be changed by cooling air sprayed onto the surface of the leading edge 340 through the protrusions 2200. It is configured to be spaced at specific intervals in consideration of membrane cooling.
  • the operator can easily perform the machining of the leading edge cooling unit 200 by one machining or one or more machining using the tool 6.
  • the protrusion 2200 may be formed in a spiral shape, and in this case, may be formed along the inner side of the opening 2100.
  • the protrusions 2200 may be arranged to face each other in a semi-circular ring shape in the inner length direction of the opening 2100, or may be disposed to be limited to only some sections.
  • the shape of the tool may be variously prepared in advance, and thus different projections 2200 may be processed according to the positions of the leading edges 340 to improve the film cooling effect. have.
  • the operator may selectively change the opened position and direction of the opening 2100 so that the cooling air is injected toward the position where the high temperature temperature condition is maintained according to the temperature distribution data on the front surface of the leading edge 340. Processing can be performed.
  • the operator can easily implement the tapping process so that the opened position and the direction of the opening 2100 are differently opened according to the temperature distribution state according to the front upper, lower and center positions of the leading edge 340.
  • the leading edge 340 is displayed in different colors at positions where the opening 2100 is to be tapped so that the operator can visually recognize the intervals according to the temperature distribution prior to the tapping operation on the opening 2100. It is preferable to display through a separate marker (not shown).
  • the tapping process may be performed using different tools for respective positions, so that the operator may perform the tapping operation accurately without confusion.
  • the operator After the tapping process is performed on the leading edge cooling unit 2000 of the turbine blade 330, the operator removes all the chips so as not to remain inside the opening 2100 so that partial blockage does not occur.
  • the protrusion 2200 may have an increased length protruding outward toward the opening 2100. In this case, the safety of the cooling air may be improved, and the spirally shaped stones may be stably implemented to achieve more efficient cooling of the membrane. have.
  • the membrane cooling unit 1000A extends from a cooling channel 1100 through which cooling air passes, and an outer surface of the turbine blade 330 at an end extending in the longitudinal direction of the cooling channel 1100 to the outer surface of the turbine blade 330. It includes an outlet portion 1200 and a plurality of ribs 1300 facing each other on the inner wall of the outlet portion 1200 is increased in width toward the outer surface of the turbine blade 330 at one end of the 1100.
  • the outlet portion 1200 has inner walls 1210 and 1220 facing each other therein, and a plurality of ribs 1300 are disposed on the inner walls 1210 and 1220 as shown in the drawing.
  • the membrane cooling unit 1000A mixes with the hot hot gas moving along the outer circumferential surface of the turbine blade 330 to achieve membrane cooling of the surface of the turbine blade 330.
  • the membrane cooling unit 1000A may exchange heat through the surface area when the cooling air is supplied through the outlet unit 1200, and stably diffuse toward the surface of the turbine blade 330 while maintaining the high temperature of the hot gas. The temperature is lowered to a predetermined temperature to achieve cooling.
  • the membrane cooling unit 1000A may minimize flow unevenness due to separation in the inner region of the outlet 1200 when the cooling air moves to the outer circumferential surface of the turbine blade 330 through the outlet 1200. It is advantageous to maintain a constant cooling efficiency.
  • the present invention is provided with ribs 1300 in the inner wall (1210, 1220) to maintain a constant flow flow of cooling air in the outlet portion 1200 to minimize the occurrence of unstable flow flow due to peeling It can also improve the flow stability of the cooling air at the same time.
  • a plurality of ribs 1300 are disposed along the inner walls 1210 and 1220 of the outlet 1200 toward the outer circumferential surface of the turbine blade 330 at regular intervals.
  • the inner walls 1210 and 1220 are disposed in the number shown in the figure in a state facing each other.
  • the gaps spaced apart from each other may maintain a gap of 5e or more. Can be.
  • the spacing of the ribs 1300 and the protruding length e cause heat transfer performance.
  • the spacing between the ribs 1300 is more than 5e to maintain more than 5e of heat transfer to cool the heat transfer. As is advantageous, the above-described spacing interval is maintained.
  • the protrusion length e of the rib 1300 is varied according to the size of the outlet 1200, it is set through a separate analysis or simulation.
  • the rib 1300 has a total length from the tip portion 1200a of the outlet portion 1200 to the trailing portion 1200b as L, and is referred to as the rear end portion 1200b from the 1/5? L position based on the tip portion 1200a. A plurality is arranged until).
  • the outlet portion 1200 has a constant flow rate of cooling air at the front end portion 1200a compared to the rear end portion 1200b, and the peeling phenomenon is around a 1/5 * L position spaced apart from the front end portion 1200a toward the rear end portion. Since the rib 1300 is disposed from the position, the flow instability due to peeling can be minimized.
  • the rib 1300 may have a protruding length e extending from the outlet portion 1200 to the same length, or from the front end portion 1200a of the outlet portion 1200.
  • Protruding length e may increase toward the end portion 1200b toward the center in the width direction of the outlet portion 1200.
  • the outlet portion 1200 has an increased area of the rear end portion 1200b, and as a result, the flow flow in the center in the width direction may be unstable compared to the front end portion 1200a. Increasing) may lead to a stable flow of cooling air.
  • One end of the cooling channel 1100 is connected to the inside of the turbine blade 330 to allow cooling air to flow in, and the other end of the cooling channel 1100 extends toward the outside of the turbine blade 330 and has a circular cross-sectional shape. It may also be possible.
  • the outlet portion 1200 has a diffusion angle ⁇ at the rear end of the cooling channel 1100 and extends in an ellipse shape in the width direction.
  • the cooling channel 1100 extends toward the outlet portion 1200 in the form of a circular cylinder, and the diffusion angle ⁇ is maintained at an angle of 15 degrees or more.
  • the diffusion angle is maintained as described above to suppress the occurrence of unnecessary peeling phenomenon and induce a stable movement before the cooling air moving along the outlet portion 1200 is moved to the surface of the turbine blade 330.
  • the diffusion angle ⁇ may stably induce a moving flow of cooling air in an optimal state within a range of 15 degrees to 40 degrees, thereby causing a membrane cooling effect.
  • the present embodiment reduces the peeling phenomenon generated by the movement of the cooling air through the plurality of ribs 1300 together with the diffusion angle and constantly induces the flow of cooling air moving along the inner center of the outlet 1200. can do.
  • the outlet portion 1200 has ribs 1300 positioned on the inner walls 1210 and 1220, respectively, on the basis of the drawing, and symmetrically disposed with respect to the center in the width (W) direction.
  • the moving speeds may be reduced in the inner walls 1210 and 1220, and thus peeling may occur. Is placed.
  • the cooling air is most preferably made of a uniform flow flow when moving in the inner region of the outlet portion 1200, but the moving speed and viscosity of the cooling air moved to the inner walls 1210 and 1220, and the width direction ( W) A peeling phenomenon may occur in the inner walls 1210 and 1220 due to a difference in the speed and viscosity of the cooling air moving along the center.
  • outlet portion 1200 maintains the moving speed of the cooling air in the inner walls 1210 and 1220 close to zero, the moving speed of the cooling air in the center of the width direction and the inner walls 1210 and 1220. The difference in the moving speed occurs.
  • the cooling air moving along the center in the width direction does not move straight forward from the inside of the outlet portion 1200 but moves toward the relatively slow inner walls 1210 and 1220. While peeling phenomenon may occur.
  • the present invention is provided with a rib 1300 to minimize such peeling phenomenon.
  • ribs 1300 are installed on the inner walls 1210 and 1220 in order to minimize peeling occurring in the inner region of the outlet portion 1200. 1300 causes an eddy phenomenon in which a small vortex occurs.
  • the eddy phenomenon may prevent undesired peeling of the cooling air moving along the inner walls 1210 and 1220 of the outlet portion 1200, thereby achieving stable movement of the cooling air.
  • heat transfer performance may also be improved to improve overall cooling performance of the turbine blade 330.
  • the eddy phenomenon causes a small vortex in the cooling air in the inner walls 1210 and 1220, unlike the delamination which causes a considerably large vortex flow in the cooling air, which causes an influence on the overall flow flow of the cooling air.
  • the flow direction of the cooling air is led to the width direction center of the outlet portion 1200 in the inner walls 1210 and 1220 instead of the flow flow.
  • a small vortex is generated around the ribs 1300, and cooling air is weakened between the spaced ribs 1300.
  • a plurality of ribs 1300 are provided on the inner walls 1210 and 1220 in order to use the eddy phenomenon, and the flow of uniform cooling air in the width direction center in the outlet portion 1200.
  • the heat transfer performance may also be improved at the same time while the cooling air moves.
  • the membrane cooling unit 1000A is positioned at the pressure surface 330a and the suction surface 330b of the turbine blade 330, respectively, and the position is at a position where the hot gas is moved along the surface of the turbine blade 330. Yes.
  • the pressure surface 330a and the suction surface 330b may maintain the membrane cooling effect stably as the cooling air moves along the surface of the turbine blade 330, thereby achieving cooling of the turbine blade 330.
  • the membrane cooling unit 1000A is disposed at different intervals between sections of the leading edge 340 constituting the turbine blade 330 to the trailing edge 350 to achieve membrane cooling. can do.
  • the membrane cooling unit (1000A) is concentrated in a plurality of sections that are maintained at a high temperature on the pressure surface (330a) and the suction surface (330b) of the turbine blade 330, the number is arranged in a section maintained at a relatively low temperature Is reduced.
  • the membrane cooling unit 1000A is provided in the first stage turbine blades and the second stage turbine blades of the plurality of unit blades constituting the turbine blade 330, respectively. Corresponds to the location where contact with the hot gas occurs either directly or indirectly.
  • the cooling state may be different according to the movement trajectory and the temperature distribution of the hot gas moving along the pressure surface 330a and the suction surface 330b. It is possible to improve the membrane cooling effect on the surface of the turbine blade 330 by different arrangement intervals or distribution in the 330b.
  • the turbine blade 330 can prevent deformation even when used for a long time because the membrane cooling effect on the surface in contact with the hot gas is improved.
  • the membrane cooling unit 1000A may be composed of a cooling channel 1100 and an outlet 120, and the cooling channel 1100 may extend 4 to 8 times the diameter (D).
  • the diameter (D) is formed as an example 0.6mm ⁇ 1.0mm, but is not necessarily limited to the above-described dimensions can be variously changed according to the specifications of the gas turbine.
  • the membrane cooling effect of the turbine blade 330 may be maximized.
  • the stable heat transfer performance effect can be maintained.
  • the cooling channel 1100 may extend up to 4.8 mm but may extend 4 to 8 times depending on the diameter (D).
  • the outlet portion 1200 maintains an inclination angle ⁇ formed between the center line extending along the center of the longitudinal direction and the surface of the turbine blade 330 within 30 degrees to 40 degrees.
  • the length of the cooling channel 1100 may be unnecessarily long.
  • the inclination angle is greater than the above-described angle, it may not be sprayed to the surface of the turbine blade 330 or only a portion thereof may be moved toward the surface, which may cause the film cooling effect of the stable turbine blade 330 only when the inclination angle is maintained. have.
  • the outlet portion 1200 is extended at an angle of 15 degrees to 20 degrees in both lateral directions with respect to the cooling channel 1100. According to the angle of expansion, the diffusion angle at which cooling air is injected toward the surface of the turbine blade 330 may vary according to the angle of expansion. The above-described angle optimally optimizes the membrane cooling effect on the surface of the turbine blade 330. It is an angle that can be maintained.
  • the outlet portion 1200 may be configured at an angle of at least 15 degrees and up to 20 degrees, thereby spraying cooling air to the surface of the turbine blade 330 to maintain the maximum membrane cooling effect to achieve efficient cooling.
  • the gas turbine blade according to an embodiment of the present invention is intended to efficiently cool the membrane cooling unit by arranging a plurality of ribs for stable cooling of the membrane cooling unit due to high temperature hot gas.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une aube de turbine à gaz. L'aube de turbine à gaz selon un mode de réalisation de la présente invention comprend : une aube de turbine (33) disposée dans une turbine à gaz; et des unités de refroidissement (110). Ces unités de refroidissement ont chacune un canal de refroidissement (110) pour refroidir l'aube de turbine (33), une partie de sortie (120) à travers laquelle l'air refroidi s'échappe, et une pluralité de feuilles (130). La partie de sortie (120) s'étend à partir de la partie d'extrémité du canal de refroidissement (110), qui s'étend dans le sens de la longueur, jusqu'à la surface extérieure de l'aube de turbine (33), la largeur de la partie de sortie (120) augmente progressivement à partir d'une extrémité du canal de refroidissement (110) à la surface extérieure de l'aube de turbine (33), et la pluralité de feuilles (130) se font face à partir des parois internes de la partie de sortie (120).
PCT/KR2017/009154 2016-08-22 2017-08-22 Aube de turbine à gaz WO2018038507A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN201780029639.4A CN109154199B (zh) 2016-08-22 2017-08-22 燃气涡轮机叶片
US16/084,968 US10927681B2 (en) 2016-08-22 2017-08-22 Gas turbine blade
EP17843927.9A EP3502418B1 (fr) 2016-08-22 2017-08-22 Aube de turbine à gaz

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
KR20160106339 2016-08-22
KR10-2016-0106339 2016-08-22
KR1020170106069A KR101951115B1 (ko) 2016-08-22 2017-08-22 가스 터빈 블레이드
KR10-2017-0106069 2017-08-22

Publications (1)

Publication Number Publication Date
WO2018038507A1 true WO2018038507A1 (fr) 2018-03-01

Family

ID=61245066

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/KR2017/009154 WO2018038507A1 (fr) 2016-08-22 2017-08-22 Aube de turbine à gaz

Country Status (1)

Country Link
WO (1) WO2018038507A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080031738A1 (en) * 2005-03-01 2008-02-07 General Electric Company Bell-shaped fan cooling holes for turbine airfoil
US20090304499A1 (en) * 2008-06-06 2009-12-10 United Technologies Corporation Counter-Vortex film cooling hole design
US20090304494A1 (en) * 2008-06-06 2009-12-10 United Technologies Corporation Counter-vortex paired film cooling hole design
US20160153283A1 (en) * 2012-02-15 2016-06-02 United Technologies Corporation Gas turbine engine component with converging/diverging cooling passage
US20160201474A1 (en) * 2014-10-17 2016-07-14 United Technologies Corporation Gas turbine engine component with film cooling hole feature

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080031738A1 (en) * 2005-03-01 2008-02-07 General Electric Company Bell-shaped fan cooling holes for turbine airfoil
US20090304499A1 (en) * 2008-06-06 2009-12-10 United Technologies Corporation Counter-Vortex film cooling hole design
US20090304494A1 (en) * 2008-06-06 2009-12-10 United Technologies Corporation Counter-vortex paired film cooling hole design
US20160153283A1 (en) * 2012-02-15 2016-06-02 United Technologies Corporation Gas turbine engine component with converging/diverging cooling passage
US20160201474A1 (en) * 2014-10-17 2016-07-14 United Technologies Corporation Gas turbine engine component with film cooling hole feature

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP3502418A4 *

Similar Documents

Publication Publication Date Title
WO2021206232A1 (fr) Sèche-cheveux
WO2021071063A1 (fr) Sèche-cheveux
WO2020145718A1 (fr) Substrat d'affichage
WO2016178521A1 (fr) Climatiseur et son procédé de commande
WO2021071065A1 (fr) Sèche-cheveux
WO2021107696A1 (fr) Climatiseur
WO2021118208A1 (fr) Soufflante
WO2021206230A1 (fr) Diffuseur et sèche-cheveux comprenant celui-ci
WO2021071061A2 (fr) Sèche-cheveux
WO2019240521A1 (fr) Moteur électrique
WO2021235646A1 (fr) Sèche-cheveux
WO2022158939A1 (fr) Sèche-cheveux
WO2019013506A1 (fr) Efem et système d'efem
WO2022025363A1 (fr) Moteur de ventilateur et sèche-cheveux comprenant ledit moteur de ventilateur
WO2021071064A2 (fr) Procédé de commande pour commander un sèche-cheveux
WO2019045222A1 (fr) Dispositif de génération d'écoulement
WO2021071062A1 (fr) Sèche-cheveux
WO2021182733A1 (fr) Module de ventilateur, et purificateur d'air portable doté de celui-ci
WO2018038507A1 (fr) Aube de turbine à gaz
WO2019221491A1 (fr) Dispositif de production d'écoulement
WO2022139569A1 (fr) Moteur
WO2019194326A1 (fr) Récipient de stockage de plaquettes
WO2022019421A1 (fr) Ensemble moteur et sèche-cheveux doté de celui-ci
WO2021157779A1 (fr) Purificateur d'air portable
WO2020180110A1 (fr) Distributeur, unité d'échangeur de chaleur et climatiseur

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 17843927

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 2017843927

Country of ref document: EP