CN105339591B - There is the nozzle gaseous film control of alternative expression compound angle - Google Patents
There is the nozzle gaseous film control of alternative expression compound angle Download PDFInfo
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- CN105339591B CN105339591B CN201480034210.0A CN201480034210A CN105339591B CN 105339591 B CN105339591 B CN 105339591B CN 201480034210 A CN201480034210 A CN 201480034210A CN 105339591 B CN105339591 B CN 105339591B
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- Prior art keywords
- end wall
- cooling holes
- nozzle
- wall
- pressure side
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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
- F01D5/186—Film cooling
-
- 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of nozzle segment for gas-turbine unit nozzle ring.The nozzle segment includes the first end wall, the second end wall, and the fin extended between the first end wall and the second end wall.The fin includes being spaced from each other and alternate multigroup Cooling Holes on direction, so that first group of Cooling Holes forms angle towards the first end wall, second group of Cooling Holes is formed angle towards the second end wall and is separated with first group of Cooling Holes, and the 3rd group of Cooling Holes are formed angle towards the first end wall and separated with second group of Cooling Holes.
Description
Technical field
The present invention relates generally to gas-turbine unit, more specifically, includes with alternative expression compound angle for one kind
Film cooling holes nozzle segment.
Background technology
Gas-turbine unit includes compressor, burner and turbine portion.Turbine portion bears high temperature.Especially,
The first order of turbine portion bears so high temperature so that the first order generally carried out by the air guided from compressor cold
But, and the air is directed into, among other things, in the nozzle segment and turbo blade.
The part for importing the air of the nozzle segment can be directed over the wall of nozzle segment fin and along the wall
Press side surface to carry out gaseous film control to the wall.United States Patent (USP) No.7,377,743 for authorizing D.Flodman discloses one kind
Turbine nozzle, its are included in the intermediate blade that install between a pair of end blade in externally-located band and internal band.The middle leaf
Piece includes that the film cooling holes of first mode, the film cooling holes of the first mode are configured to than each having second mode
Each more cooling air of discharge of described two end blades of film cooling holes.
It is contemplated that overcoming one or more problems that the present inventor had found or well known in the prior art.
Content of the invention
The invention discloses a kind of nozzle segment of the nozzle ring for gas-turbine unit.The nozzle segment includes first
End wall, the second end wall, and the fin extended between first end wall and second end wall.The fin includes leading
Edge, trailing edge, pressure side wall, and inhale side wall.The guide lug extends radially to second end wall from first end wall.The tail
Edge extends radially to second end wall from first end wall, axially away from the guide lug.Pressure side wall is led from described
Edge extends to the trailing edge.Suction side wall also extends to the trailing edge from the guide lug.The fin also includes multiple seedpod of the lotus
Hair style Cooling Holes, multiple front Cooling Holes, and multiple intercooling holes.The plurality of sprinkle nozzle Cooling Holes are along the guide lug
Across.The plurality of front Cooling Holes in groups together, close to the plurality of sprinkle nozzle Cooling Holes.The plurality of intercooling
Hole in the wall of the pressure side in groups together, between the trailing edge and the plurality of front Cooling Holes.The plurality of sprinkle nozzle
Cooling Holes, the plurality of front Cooling Holes, and the plurality of intercooling hole on direction alternately so that the plurality of shower nozzle
Formula Cooling Holes form angle towards first end wall, and the plurality of front Cooling Holes form angle towards second end wall, and
Multiple intercooling holes form angle towards first end wall.
Description of the drawings
Fig. 1 is the schematic diagram of exemplary gas turbogenerator.
Fig. 2 is the perspective view of the nozzle segment of the gas-turbine unit for Fig. 1.
Fig. 3 is the cross-sectional view of a part for the nozzle segment of Fig. 2, and which illustrates sprinkle nozzle Cooling Holes.
Fig. 4 is the detailed view of the front Cooling Holes of Fig. 2.
Fig. 5 is the detailed view in the intercooling hole of Fig. 2.
Fig. 6 is the detailed view of the rear Cooling Holes of Fig. 2.
Fig. 7 is the cross section of the fin of Fig. 2.
Specific embodiment
System and methods described herein includes the nozzle segment of the nozzle ring for gas-turbine unit.In embodiment
In, shown nozzle segment includes upper end wall, inner end wall, and positioned at one or more fins between the two.Each fin includes wearing
Cross the groups of Cooling Holes for separating of the pressure side wall of the fin.One group forms angle, and next group pair towards the lower end wall
Angle is formed towards the upper end wall with alternate mode in the Cooling Holes that subsequently organizes.The groups of Cooling Holes are towards the lower end
The direction of wall and the upper end wall replaces, and can reduce the temperature of the lower end wall and the upper end wall, and can reduce
Cooling air volume needed for the effect cooling nozzle segment.
Fig. 1 is the schematic diagram of exemplary gas turbogenerator 100.In order to understand and be easy to illustrate, some surfaces are saved
Omit or exaggerate (in Ben Tu or other figures).Additionally, the present invention is referred to direction forward or backward.Generally, to " front " or
" afterwards " institute with reference to the flow direction for being associated with major air (that is, in combustion process used air), unless otherwise stated.
For example, " front " is that and " afterwards " is relative to main air stream " downstream " relative to main air stream " upstream ".
In addition, the present invention can referring generally to the center of rotation axis 95 of gas-turbine unit, the axis substantially by it
The longitudinal axis of axle 120 (which passes through multiple bearing assemblies 150 and supports) are limited.Central axis 95 can be with various other electromotors
Concentric parts are shared or shared.To axially, radially, the institute of circumferencial direction with reference to measurement be with reference to central axis 95, unless
It is otherwise noted；And the term such as " interior " and " outward " substantially represents less or larger radial distance, wherein radially 96 can be with
It is from central axis 95 to extraradial and vertical any direction.
Gas-turbine unit 100 includes entrance 110, axle 120, compressor 200, burner 300, turbine 400, exhaustor
500, and power output bonder 600.Gas-turbine unit 100 can have uniaxially or biaxially configure.
Compressor 200 includes that compressor drum component 210, compressor fixes blade (stator) 250 and inlet guide vane
255.Compressor drum component 210 is mechanically coupled to axle 120.As illustrated, compressor drum component 210 is shaft flow rotor group
Part.Compressor drum component 210 includes one or more compressor disc components 220.Each compressor disc component 220 includes circumference
Be assembled with the compressor drum disk of compressor drum blade.Stator 250 axially follows each compressor disc component 220.Per
One compressor disc component 220, its in pairs, are considered compressor stage with the adjacent stator 250 for following the compressor disc component 220.
Compressor 200 includes multiple compressor stages.Before inlet guide vane 255 is axially located at compressor stage.
Burner 300 includes one or more fuel injectors 310, and including one or more combustor 390.
Turbine 400 includes turbine rotor component 410 and turbine nozzle 450.Turbine rotor component 410 is mechanically coupled to
Axle 120.As illustrated, turbine rotor component 410 is shaft flow rotor component.Turbine rotor component 410 includes one or more whirlpools
Wheel assemblies 420.Each turbine disc assemblies 420 include the turbine disk for being circumferentially assembled with turbine blade.Turbine nozzle 450 or spray
Before mouth ring is axially located at each turbine disc assemblies 420.Each turbine nozzle 450 includes forming the multiple of ring in groups together
Nozzle segment 451.Each turbine disc assemblies 420, which is paired with the neighbouring turbine nozzle 450 being located at before turbine disc assemblies 420, quilt
It is considered as stage of turbine.Turbine 400 includes multiple stage of turbines.
Turbine 400 can also include turbine shroud 430 and turbine baffle 440.Turbine shroud 430 can be from turbine rotor
Component 410 and turbine nozzle 450 are radially outwardly arranged.Turbine shroud 430 can include one or more cylindrical shapes.Each
Nozzle segment 451 is it is so structured that being attached, being coupled to or be suspended from turbine shroud 430.Each turbine baffle 440 can be axial
Before ground is located at each turbine disc assemblies 420, and can the neighbouring turbine disk.Each turbine baffle 440 can be spraying from turbine
Mouth 450 is radially inwardly arranged.Each nozzle segment 451 may be configured to be attached or coupled to turbine baffle 440.
Air vent 500 includes exhaust diffuser 520 and exhaust collector 550.Power output coupling 600 can be arranged on axle
120 one end.
Fig. 2 is the perspective view of the nozzle segment 451 of the gas-turbine unit 100 for Fig. 1.Nozzle segment 451 includes upper cover
Shell 452, lower encioser 456, fin 460 and the second fin 470.In other embodiments, nozzle segment 451 can include more or more
Few fin.When nozzle segment 451 is in the gas-turbine unit 100, upper encloser 452 can be neighbouring and from turbine shroud
430 are radially inwardly arranged.Upper encloser 452 includes upper end wall 453.Upper end wall 453 can be a part for annular shape or one
One section of section, a such as annular section or hollow cylinder.The annular shape can include convex shape by having
The cross section of inward flange is limiting.The arrangement of multiple upper end walls 453 is shaped as annular shape and limits by turbine nozzle 450
The radially-outer surface of flow path.When in gas-turbine unit 100, upper end wall 453 can be with central axis 95
Coaxially.
Upper encloser 452 can also include front upper rail 454 and rear upper rail 455.Front upper rail 454 is from 453 footpath of upper end wall
To outwardly extending.In the embodiment shown in Figure 2, front upper rail 454 from upper end wall 453 at the axial end of upper end wall 453
Extend.In other embodiments, front upper rail 454 prolongs at the axial end near or adjacent to upper end wall 453 from upper end wall 453
Stretch.Front upper rail 454 can include lip, protuberance or further feature, and which can be used for for nozzle segment 451 being fixed to turbine case
Body 430.
Upper rail 455 can also be extended radially out from upper end wall 453 afterwards.In the embodiment shown in Figure 2, rear upper rail
Road 455 is " L " shape, has：From upper end wall 453, axially opposite end extends radially outwardly with the position of front upper rail 454
Part I, and in the relative side upwardly extending second in the position of the front upper rail 454 for extending axially beyond upper end wall 453
Part.In other embodiments, upper rail 455 includes other shapes afterwards, and may be located near or adjacent to upper end wall 453 it
The axially opposite end with the position of front upper rail 454.Upper rail 455 can also include further feature afterwards, and which can be used for spraying
Mouth section 451 is fixed to turbine shroud 430.
Lower encioser 456 is radially inwardly arranged from upper encloser 452.When nozzle segment 451 is arranged on gas-turbine unit 100
When middle, lower encioser 456 can be with neighbouring and radially outwardly arrange from turbine baffle 440.Lower encioser 456 includes lower end wall 457.
Lower end wall 457 can be a part for annular shape (such as annular or hollow cylinder) or a section.The annular shape can be with
Limited by having the outer peripheral cross section for including convex shape.Multiple lower end walls 457 arrangement be shaped as annular shape and
It is defined through the inner radial surface of the flow path of turbine nozzle 450.When in gas-turbine unit 100, lower end
Wall 457 can be coaxial with upper end wall 453 and central axis 95.
Lower encioser 456 can also include front lower railway 458 and rear lower railway 459.Front lower railway 458 is from 457 footpath of lower end wall
To upcountry extending.In the embodiment shown in Figure 2, front lower railway 458 from lower end wall 457 at the axial end of lower end wall 457
Extend.In other embodiments, front lower railway 458 prolongs at the axial end near or adjacent to lower end wall 457 from lower end wall 457
Stretch.Front lower railway 458 can include lip, protuberance or further feature, its can be used for by nozzle segment 451 be fixed to turbine every
Plate 440.
Lower railway 459 can be radially inwardly extending from lower end wall 457 afterwards.In the embodiment shown in Figure 2, rear lower rail
Road 459 is being extended at axially opposite end with the position of front lower railway 458 from lower end wall 457 near or adjacent to lower end wall 457.
In other embodiments, from lower end wall 457, axially opposite end extends rear lower railway 459 with the position of front lower railway 458.Afterwards
Lower railway 459 can include lip, protuberance or further feature, and which can be used for for nozzle segment 451 being fixed to turbine baffle
440.
Fin 460 extends between upper end wall 453 and lower end wall 457.Fin 460 includes guide lug 461, trailing edge 462, pressure side
Wall 463 and suction side wall 464.It is adjacent that guide lug 461 extends to lower end wall 457 at the axial end of upper end wall 453 from upper end wall 453
At the axial end of nearly lower end wall 457.Guide lug 461 may be located at upper rail 454 and front lower railway 458 before being close to.Trailing edge 462 is from upper
End wall 453 is extended at axially opposite end away from guide lug 461 and adjacent to upper end wall 453 with the position of guide lug 461, and under
End wall 457 adjacent to the relative with the position of trailing edge 461 of upper end wall 453 or axially away from axial end at extend.When nozzle segment 451
When in gas-turbine unit 100, guide lug 461, front upper rail 454 and front lower railway 458 can be axially disposed at
The anterior and upstream of trailing edge 462, rear upper rail 455 and rear lower railway 459.Guide lug 461 can be at the upstream end of fin 460
There is the position of maximum curvature, and trailing edge 462 can be, in the downstream end of fin 460, there is the position of maximum curvature.?
In embodiment shown in Fig. 1, nozzle segment 451 is first order turbine nozzle adjacent to the part of combustor 390.In other embodiment
In, nozzle segment 451 is arranged in another grade of turbine nozzle 450.
Pressure side wall 463 can span to trailing edge 462 from guide lug 461 between upper end wall 453 and lower end wall 457.Pressure side wall
463 can include recessed shape.Pressure side wall 463 can also include the pressure side surface 469 with concave shape, that is, press side wall
463 outer surface.Inhale side wall 464 trailing edge 462 can also be spanned to from guide lug 461 between upper end wall 453 and lower end wall 457.
Inhaling side wall 464 can include raised shape.Guide lug 461, trailing edge 462, pressure side wall 463 and suction side wall 464 can form cooling
Chamber 485 (shown in Fig. 3 and Fig. 6) or the multiple cooling chambers between which.Upper end wall 453, lower end wall 457 or the two can include for
Cooling air (not shown) enters a hole, multiple holes or the path of cooling chamber 485.
Fin can also include multigroup gaseous film control hole or hole.Each cooling hole or hole can extend through fin
The passage of wall (such as pressing side wall 463).In the embodiment shown in Figure 2, fin 460 includes sprinkle nozzle Cooling Holes 465, front cold
But hole 466, rear Cooling Holes 467 and intercooling hole 468.Sprinkle nozzle Cooling Holes 465 are located at guide lug 461, and can be connected
It is grouped into together with guide lug 461.Sprinkle nozzle Cooling Holes 465 can be arranged in column.In the embodiment shown in Figure 2, shower nozzle
Formula Cooling Holes 465 are arranged to 6 row, and each being listed between upper end wall 453 and lower end wall 457 extends in radial directions.At other
In embodiment, sprinkle nozzle Cooling Holes 465 can be arranged to 4 to 7 row, or can be arranged to other constructions.Pressure 463 He of side wall
The part for inhaling the neighbouring guide lug 461 of side wall 464 can include sprinkle nozzle Cooling Holes 465.
Front Cooling Holes 466 can in groups together, and in 1/3rd of the neighbouring guide lug 461 of pressure side wall 463.
Front Cooling Holes 466 can be close to sprinkle nozzle Cooling Holes 465.In an embodiment, front Cooling Holes 466 are located at apart from sprinkle nozzle
1/8 to 1/4 place of the length of the pressure side wall 463 of Cooling Holes 465.In other embodiments, front Cooling Holes 466 are located at apart from the seedpod of the lotus
At the 1/6 of the length of the pressure side wall 463 of hair style Cooling Holes 465.In other embodiment, front Cooling Holes 466 are located at apart from lotus
At the 1/8 of the length of the pressure side wall 463 of fluffy hair style Cooling Holes 465.Front Cooling Holes 466 can be in upper end wall 453 and lower end wall 457
Between in groups together.In the embodiment shown in Figure 2, front Cooling Holes 466 are arranged to single radial alignment, and with 3.5 section
Be radially spaced from away from diameter ratio (pitch over diameter), the pitch diameters than be adjacent holes center between away from
From the diameter ratio with hole.In other embodiments, front Cooling Holes 466 are radially spaced from 3 to 4 pitch diameters ratio.Front cold
But hole 466 can be overlap with neighbouring front Cooling Holes 466, rather than is alignd along the surface of pressure side wall 463 in radial directions.
Cooling Holes 467 in groups together, and can be arranged on 1/3rd of the neighbouring trailing edge 462 for pressing side wall 463 afterwards
Interior.Cooling Holes 467 can be close to trailing edge 462 afterwards.In an embodiment, rear Cooling Holes are located at the pressure side wall 463 apart from trailing edge 462
Length 1/8 to 1/4 place.In other embodiments, rear Cooling Holes 467 are located at the length of the pressure side wall 463 apart from trailing edge 462
1/6 at.In other embodiment, rear Cooling Holes 467 are located at the 1/8 of the length of the pressure side wall 463 apart from trailing edge 462.
Cooling Holes 467 can be arranged radially between upper end wall 453 and lower end wall 457 afterwards.In the embodiment shown in Figure 2, cool down afterwards
Hole 467 is arranged to single radial alignment, and is radially spaced from 3.5 pitch diameters ratio.In other embodiments, rear Cooling Holes
467 are radially spaced from 3 to 4 pitch diameters ratio.Cooling Holes 467 can be overlap with neighbouring rear Cooling Holes 467 afterwards, rather than
Align in radial directions on surface along pressure side wall 463.
Intercooling hole 468 can in groups together, and positioned at pressure side wall 463 centre 1/3rd in.Middle cold
But hole 468 is can be located between front Cooling Holes 466 and trailing edge 462.Intercooling hole 468 may be alternatively located at front Cooling Holes 466 and rear cold
But between hole 467.In certain embodiments, intercooling hole 468 is located at the length of the pressure side wall 463 away from front Cooling Holes 466
In the 1/4 to 3/8 of the length of the pressure side wall 463 in 1/4 to 3/8 and away from rear Cooling Holes 467.In other embodiments, middle cold
But hole 468 is located at the pressure side wall 463 at the 1/3 of the length of the pressure side wall 463 away from front Cooling Holes 466 and away from rear Cooling Holes 467
At the 1/3 of length.In other embodiment, intercooling hole 468 is located at the length of the pressure side wall 463 away from front Cooling Holes 466
At least 1/8 at and away from rear Cooling Holes 467 pressure side wall 463 length at least 1/8 at.The intercooling hole 468 can be radially
Be arranged between upper end wall 453 and lower end wall 457.In the embodiment shown in Figure 2, intercooling hole 468 is arranged on single
It is radially spaced from radial alignment and with 3.5 pitch diameters ratio.In other embodiments, intercooling hole 468 is with 3 to 4
Pitch diameters ratio is radially spaced from.These intercooling holes 468 can be overlapped with adjacent intercooling hole 468, rather than along
Align in radial directions on the surface of pressure side wall 463.
Although embodiment shown in figure 2 includes front Cooling Holes 466, rear Cooling Holes 467 and intercooling hole 468,
But some embodiments do not include rear Cooling Holes 467, and other embodiment is included positioned at intercooling hole 468 and rear Cooling Holes
The second intercooling hole between 467.Second intercooling hole may be disposed to similar to front Cooling Holes 466, rear Cooling Holes 467 with
And the arrangement in intercooling hole 468.May also include the Cooling Holes of other groups or row.Interval between the group of Cooling Holes or row can use
Certainly in group or the number of row of the Cooling Holes along the pressure positioning of side wall 463.
Fin 460 may further include groove 483.Groove 483 can be located at pressure side wall 463 on and can be adjacent with trailing edge 462.
Groove 483 can be rectangle and can be alignd between upper end wall 453 and lower end wall 457 in radial directions.Groove 483 can be from cold
But chamber 485 extends to trailing edge 462.
In the embodiment shown in Figure 2, nozzle segment 451 includes the second fin 470.Second fin 470 may include and fin
460 same or similar features, including the second guide lug 471, the second trailing edge (not shown), the second pressure side wall 473, and second inhales
Side wall 474.Second fin 470 may also include
Hole 477, the second intercooling hole 478, and the second groove (not shown).Second guide lug 471, the second trailing edge, the second pressure side wall
473rd, second inhale side wall 474, Cooling Holes 477, second after Cooling Holes 476, second before the second sprinkle nozzle Cooling Holes 475, second
Intercooling hole 478, and the description of the second groove can by respectively with guide lug 461, trailing edge 462, pressure side wall 463, inhale side wall
464th, sprinkle nozzle Cooling Holes 465, front Cooling Holes 466, rear Cooling Holes 467, intercooling hole 468, and groove 483 be identical or class
As mode orient.In other embodiments, nozzle segment 451 only includes fin 460 and does not include the second fin 470.
The various parts of nozzle segment 451, including upper encloser 452, lower encioser 456, fin 460, and the second fin 470,
Can integratedly cast or metallurgically bond to form their monomer or single type component.
Embodiments in accordance with the present invention, the groups of Cooling Holes for separating, sprinkle nozzle Cooling Holes 465, front Cooling Holes 466,
Intercooling hole 468, and rear Cooling Holes 467 on direction alternately, formed at lower end wall 457 or upper end wall 453 angle or
It is partly formed angle.The directivity or angle of this some holes guides cooling air along preferential direction.Illustrate in Fig. 2 to Fig. 6
In embodiment, sprinkle nozzle Cooling Holes 465 form angle towards lower end wall 457, and front Cooling Holes 466, i.e., along pressure side wall 463
Next group of Cooling Holes, form angle towards upper end wall 453；Intercooling hole 468, i.e., along the cold of pressure follow-up group of side wall 463
But hole, also forms angle at lower end wall 457；And rear Cooling Holes 467, i.e., last group Cooling Holes, also shape at the upper end wall
Angled.In other embodiments, sprinkle nozzle Cooling Holes 465 form angle, 466 direction of front Cooling Holes towards upper end wall 453
Lower end wall 457 forms angle, and intercooling hole 468 also forms angle at upper end wall 453, and rear Cooling Holes 467 are also in lower end
Angle is formed at wall 457.
Include the second intercooling hole and sprinkle nozzle Cooling Holes 465 that angle is formed towards lower end wall 457 at some
In embodiment, the second intercooling hole in groups and can form angle towards upper end wall 453 after intercooling hole 468,
And rear Cooling Holes 467 in groups and can form angle towards lower end wall 457 after the second intercooling hole.
Fig. 3 is the cross-sectional view of a part for the nozzle segment 451 of Fig. 2, and which illustrates sprinkle nozzle Cooling Holes 465.Show in Fig. 3
In the embodiment for going out, the wall 444 that sprinkle nozzle Cooling Holes 465 can extend through fin 460 towards lower end wall 457 enters cooling chamber
485.Wall 444 can be guide lug 461, pressure side wall 463 or the part for inhaling side wall 464.Sprinkle nozzle Cooling Holes 465 can be relative to
Reference plane 480 forms angle.Reference plane 480 can be defined to following planes, and the plane is perpendicular to from nozzle-axis, upper cover
The axis of shell 452 and lower encioser 456 and radially extending along guide lug 461.In one embodiment, shower nozzle angle 481, i.e.,
Angle of the sprinkle nozzle Cooling Holes 465 relative to reference plane 480, is directed towards 20 degree to 45 degree of lower end wall 457.At another
In embodiment, sprinkle nozzle angle 481 is 30 degree or in 30 degree of predetermined tolerance.The predetermined tolerance can be machining tolerance
Or manufacturing tolerance.Although shower nozzle angle 481 in the embodiment illustrated direction towards lower end wall 457, shower nozzle angle
481 in other embodiments can direction towards upper end wall 453.
Each sprinkle nozzle Cooling Holes 465 also can be at the position positioned by the sprinkle nozzle Cooling Holes 465, relative to just
Meet at the direction of guide lug 461, angle is formed towards lower end wall 457 or upper end wall 453.
As shown in figure 3, each sprinkle nozzle Cooling Holes 465 may include the shower nozzle arrival end 491 neighbouring with cooling chamber 485
With the shower nozzle port of export 492 being located at the surface of guide lug 461.Shower nozzle arrival end 491 can exist than the shower nozzle port of export 492
Radially closer to upper end wall 453, and the shower nozzle port of export 492 can than shower nozzle arrival end 491 diametrically closer to
Lower end wall 457.
Fig. 4 is the detailed view of the front Cooling Holes 466 of Fig. 2.Fig. 5 is the detailed view in the intercooling hole 468 of Fig. 2.Fig. 6
It is the detailed view of the rear Cooling Holes 467 of Fig. 2.With reference to Fig. 4, Fig. 5 and Fig. 6, front Cooling Holes 466, rear Cooling Holes 467 and centre are cold
But hole 468 can be advanced through turbine nozzle 450 relative to during gas-turbine unit 100 is operated along pressure side surface 469
Air flow direction formed angle.Line of reference 482 illustrates the flow direction.Line of reference 482 can also be defined to press side table
Intersection between face 469 and following planes, the plane is perpendicular to from turbine nozzle axis, upper encloser 452 and lower encioser 456
Axis, radially extending along pressure side surface 469.
With reference to Fig. 2 and Fig. 4, front Cooling Holes 466 can form angle at front compound angle 486.Front compound angle 486 can be
The component of the angle of Cooling Holes 466 before in the plane of pressure side surface 469.As indicated, front compound angle 486 can be relative to line of reference
482 or described flow directions form angle towards upper end wall.In one embodiment, front compound angle 486 is 15 degree to 40
Five degree.In another embodiment, front compound angle 486 is 30 degree or in 30 degree of predetermined tolerance.The predetermined tolerance
Can be machining tolerance or manufacturing tolerance.Zero degree can be the direction for marching to trailing edge 462 along line of reference 482 from guide lug 461
Flow direction.Although front compound angle 486 in illustrated embodiment direction towards upper end wall 453, in some wherein shower nozzles
Towards in the embodiment of upper end wall 453,486 direction of front compound angle is towards lower end wall 457 in formula angle 481 direction.
With reference to Fig. 2 and Fig. 5, intercooling hole 468 can form angle with middle compound angle 488.Middle compound angle 488 can be with
It is the component of the angle in intercooling hole 468 in the plane of pressure side surface 469.As indicated, middle compound angle 488 is relative to institute
State flow direction or line of reference 482 angle is formed towards lower end wall 457.In one embodiment, middle compound angle 488 is 15
Spend to 45 degree.In another embodiment, middle compound angle 488 is 30 degree or in 30 degree of predetermined tolerance.Institute
It can be machining tolerance or manufacturing tolerance to state predetermined tolerance.Although middle compound angle 488 is in the embodiment shown under the direction of direction
End wall 457, but in some wherein front 486 directions of compound angle towards in the embodiment of lower end wall 457,488 direction of middle compound angle
Towards upper end wall 453.
With reference to Fig. 2 and Fig. 6, rear Cooling Holes 467 can form angle at rear compound angle 487.Afterwards compound angle 487 can be
The component of the angle of Cooling Holes 467 after in the plane of pressure side surface 469.As indicated, rear compound angle 487 is relative to the flowing side
To or line of reference 482 form angle towards upper end wall 453, and can be similar with front compound angle 486 or equal.Implement at one
In example, rear compound angle 487 is 15 degree to 45 degree.In another embodiment, rear compound angle 487 is 30 degree or three
In ten degree of predetermined tolerance.The predetermined tolerance can be machining tolerance or manufacturing tolerance.Although rear compound angle 487 is in shown reality
Direction is applied in example towards upper end wall 453, but some wherein in the middle of 488 directions of compound angle towards in the embodiment of upper end wall 453,
487 direction of compound angle is towards lower end wall 457 afterwards.
Some embodiments for not including intercooling hole 468 or including the second intercooling hole some embodiments it
In, rear compound angle 487 can form angle relative to the flow direction or line of reference 482 towards lower end wall.In these embodiments
One of in, rear compound angle 487 is 15 degree to 45 degree.These embodiments another in, rear compound angle 487 be approximate three
Ten degree.
Fig. 7 is the cross section of the fin 460 of Fig. 2.With reference to Fig. 7, front Cooling Holes 466 can also include front jet angle 441.Before
Jet angle 441 can be the component of the angle of Cooling Holes 466 before in the plane for pressing side surface 469.Front jet angle 441
Relative to the line measurement extended towards trailing edge 462, and pressure side surface can be tangential at the position of each front Cooling Holes 466
469.In one embodiment, front jet angle 441 is 15 degree to 50 degree.In another embodiment, front jet angle 441 is near
Like 30 degree.
Cooling Holes 467 may also include rear jet angle 442 afterwards.Jet angle 442 can be perpendicular to pressure side surface 469 afterwards
The component of the angle of Cooling Holes 467 after in plane.Jet angle 442 can be measured relative to the line extended towards trailing edge 462 afterwards, and
And pressure side surface 469 is tangential at the position of each rear Cooling Holes 467.In one embodiment, rear jet angle 442 is 15 degree
To 50 degree.In another embodiment, rear jet angle 442 is approximate 30 degree.
Intercooling hole 468 may also include intermediate injection angle 443.Intermediate injection angle 443 can be perpendicular to pressure side table
The component of the angle in intercooling hole 468 in the plane in face 469.Intermediate injection angle 443 can be relative to extending towards trailing edge 462
Line measurement, and be tangential at the position in each intercooling hole 468 pressure side surface 469.In one embodiment, middle spray
Firing angle 443 is 15 degree to 50 degree.In another embodiment, intermediate injection angle 443 is approximate 30 degree.
Cooling chamber 485 can be single-chamber, or can be separated into multiple chambeies.In the embodiment shown in fig. 7, cooling chamber
485 can be separated into two cooling chambers.
Before each, Cooling Holes 466 can include the front entrance end 493 of neighbouring cooling chamber 485 and neighbouring or be located at pressure side table
The front port of export 494 at face 469.Each intercooling hole 468 can include the medial inlet end 497 of neighbouring cooling chamber 485 with
And neighbouring or at pressure side surface 469 central exit end 498.Each rear Cooling Holes 467 can include neighbouring cooling chamber 485
Rear entrance end 495 and neighbouring or at pressure side surface 469 the rear port of export 496.
The compound angle can be by the arrival end in the hole and the port of export relative to lower end wall 457 and upper end wall 453
Position is determining, and the jet angle can pass through the arrival end and the port of export relative to guide lug 461 and the position of trailing edge 462
To determine.
In the embodiment shown in fig. 4, front entrance end 493 than the front port of export 494 radially closer to lower end wall 457 and axle
To ground closer to guide lug 461, and the front port of export 494 is than front entrance end 493 radially closer to upper end wall 453 and axially more
Near trailing edge 462.In other embodiments, front entrance end 493 than the front port of export 494 radially closer to upper end wall 453 and axle
To ground closer to guide lug 461, and the front port of export 494 is than front entrance end 493 radially closer to lower end wall 457 and axially more
Near trailing edge 462.
In the embodiment shown in fig. 5, medial inlet end 497 than central exit end 498 radially closer to upper end wall 453
And axially closer to guide lug 461, and central exit end 498 than medial inlet end 497 radially closer to lower end wall 457 and
Axially closer to trailing edge 462.In other embodiments, medial inlet end 497 than central exit end 498 radially closer under
End wall 457 and axially closer to guide lug 461, and central exit end 498 than medial inlet end 497 radially closer to upper end
Wall 453 and axially closer to trailing edge 462.
In the embodiment shown in fig. 6, rear entrance end 495 than the rear port of export 496 radially closer to lower end wall 457 and axle
To ground closer to guide lug 461, and the rear port of export 496 is than rear entrance end 495 radially closer to upper end wall 453 and axially more
Near trailing edge 462.In other embodiments, rear entrance end 495 than the rear port of export 496 radially closer to upper end wall 453 and axle
To ground closer to guide lug 461, and the rear port of export 496 is than rear entrance end 495 radially closer to lower end wall 457 and axially more
Near trailing edge 462.
The one or more of above-mentioned part (or its subassembly) can be by rustless steel and/or resistant to elevated temperatures material (also referred to as
" superalloy ") make.Superalloy or high performance alloys be a kind of with excellent mechanical strength under high temperature and creep resistant,
Good surface stability, and the alloy of corrosion resistance and non-oxidizability.Superalloy can include such as HASTELLOY,
Alloy X, INCONEL, WASPALOY, RENE alloy, HAYNES alloys, alloy 188, alloy 230, INCOLOY, MP98T, TMS
Alloy, and the material such as CMSX single crystal alloys.
Industrial applicibility
Gas-turbine unit is applicable to multiple commercial Applications, and the various aspects of such as industrial gas oil (include
The transmission of petroleum gas, collection, storage, reclaim and lifted), power generation industries, cogeneration, aviation, and other transport
Industry.
With reference to Fig. 1, gas (usually air 10) enters entrance 110 as " working fluid " and is compressed by compressor 200.
In compressor 200, the working fluid is compressed by a series of compressor disc components 220 in annular flow path 115.Especially
Ground, air 10 are compressed in " multistage " of numbering, and the level is associated with each compressor disc component 220.For example, " the 4th grade
Air " can be related in the 4th compressor disc component 220 in " backward " direction or downstream for going to steam vent 500 from entrance 110
Connection,.Similarly, each turbine disc component 420 can be associated with " level " of a numbering.
Once compressed air 10 leaves compressor 200, it will enter burner 300, in this place air diffusion and
Add fuel.Air 10 and fuel are sprayed in combustor 390 via fuel injector 310 and are burnt.Energy passes through a series of whirlpools
Every one-level of wheel disc assembly 420 is extracted from the combustion reaction via turbine 400.Aerofluxuss 90 can be then in exhaust diffuser
Spread in 520, and be collected and guide again.Aerofluxuss 90 leave the system via exhaust collector 550, it is possible to further
Processed (such as in order to reduce noxious emission, and/or reclaim heat from aerofluxuss 90).
The work efficiency of gas-turbine unit increases generally as ignition temperature increases.Thus, there is one kind and carry
The trend of temperature in high gas-turbine unit.From combustor 390 reach turbine before what gas can be 1000 °F or
Higher.In order to operate a part for the compressed air from compressor 200 at such high temperatures, cooling air can be via inside
Passage or chamber turn to cool down all parts (including turbine nozzle segment such as nozzle segment 451) of turbine.However, using cold
But air may reduce the work efficiency of gas-turbine unit.
The groups of Cooling Holes of alternating (such as sprinkle nozzle Cooling Holes 465, front Cooling Holes 466, intercooling hole 468 and
Cooling Holes direction 467) is with the upper end wall 453 by cooling air towards upper encloser 452 and the lower end wall 457 of lower encioser 456 afterwards
Guiding, can reduce the temperature of upper end wall 453 and lower end wall 457, and this can improve the working life of nozzle segment 451.
From the cooling that sprinkle nozzle Cooling Holes 465, front Cooling Holes 466, intercooling hole 468 and rear Cooling Holes 467 leave
The first order cooling or first use of air, can be used for gaseous film control pressure side wall 463.The second level cooling of cooling air or second
Secondary use, can be used for the temperature for reducing upper end wall 453 and lower end wall 457.
Cooling air can be directed over turbine shroud 430, turbine diaphragm 440 or while pass through the two and enter
Cooling chamber 485.Then cooling air can be directed over Cooling Holes, and the Cooling Holes include sprinkle nozzle Cooling Holes 465, front cold
But hole 466, intercooling hole 468 and rear Cooling Holes 467.Cooling air can be used for before the Cooling Holes
Internally cooling fins 460.Being used for multiple times for cooling air may include first order gaseous film control, the cooling of second level end wall, and
The internal cooling, it is possible to reduce effective 451 required air quantity of cooling nozzles section.Cooling nozzles section 451 required air quantity subtracts
Can improve or improve the efficiency of gas-turbine unit 100 less.
The Cooling Holes of the second fin 470 can be used by the same or similar mode with the Cooling Holes of fin 460, so as to lead
The further reduction of the temperature of upper end wall 453 and lower end wall 457 is caused, and it is empty effectively to cool down cooling needed for each nozzle segment 451
The minimizing of tolerance.
Above-mentioned detailed description is only substantially example, and is not intended to limit the application and use of the present invention or the present invention.
Described embodiment is not limited to be used in conjunction with certain types of gas-turbine unit.Therefore, although of the invention
Describe and describe specific nozzle segment for ease of explaining, but it should be appreciated that can be implemented according to the nozzle segment of the present invention various
In other configurations, can be used together with the gas-turbine unit of various other types, and can be used in other kinds of
In machine.Additionally, being not intended to be limited by any theory that is offered in aforementioned background art or detailed description.It should also be understood that
Diagram potentially include the size exaggerated with preferably diagrammatically shown go out REFER object, and be not intended as restricted, unless bright
Really explanation.
Claims (7)
1. a kind of nozzle segment for gas-turbine unit nozzle ring, the nozzle segment include：
First end wall；
Second end wall；And
The fin extended between first end wall and second end wall, the fin include：
Guide lug, its extend radially to second end wall from first end wall,
Trailing edge, which extends radially to second end wall from first end wall, axially away from the guide lug,
Pressure side wall, which extends to the trailing edge from the guide lug,
Side wall is inhaled, which extends to the trailing edge from the guide lug,
Multiple sprinkle nozzle Cooling Holes, its along the guide lug across,
Multiple front Cooling Holes, its in the wall of the pressure side in groups together, close to the plurality of sprinkle nozzle Cooling Holes, and
Multiple intercooling holes, its in the wall of the pressure side in groups together, the trailing edge and the plurality of front Cooling Holes it
Between,
The plurality of sprinkle nozzle Cooling Holes, the plurality of front Cooling Holes, and the plurality of intercooling hole submitted in direction
Replace so that the plurality of sprinkle nozzle Cooling Holes form angle towards first end wall, and the plurality of front Cooling Holes are towards institute
State the second end wall and form angle, and the plurality of intercooling hole forms angle towards first end wall；
Characterized in that, the fin is included between the guide lug, the trailing edge, pressure side wall and suction side wall
Cooling chamber, each sprinkle nozzle Cooling Holes include the shower nozzle arrival end for being adjacent to the cooling chamber and are located at the guide lug appearance
The shower nozzle port of export in face, the shower nozzle arrival end than the shower nozzle port of export radially closer to second end wall,
The shower nozzle port of export is than the shower nozzle arrival end radially closer to first end wall；Described in the wall of the pressure side
At least the 1/8 of multiple front Cooling Holes pressure side wall length spaced-apart with the plurality of sprinkle nozzle Cooling Holes, before each
Cooling Holes include the front entrance end adjacent with the cooling chamber and the front port of export adjacent with the pressure side surface, the front entrance
Hold than the front port of export radially closer to first end wall and axially closer to the guide lug, and the front outlet
End is than the front entrance end radially closer to second end wall and axially closer to the trailing edge；Also, it is the plurality of
At least the 1/8 of the intercooling hole pressure side wall length spaced-apart with the plurality of front Cooling Holes, each intercooling hole
Including the medial inlet end adjacent with the cooling chamber and the central exit end adjacent with the pressure side surface, the medial inlet
Hold than the central exit end radially closer to second end wall and axially closer to the guide lug, and the centre
The port of export is than the medial inlet end radially closer to first end wall and axially closer to the trailing edge.
2. nozzle segment as claimed in claim 1, wherein, when each sprinkle nozzle Cooling Holes extends through the wall of the fin
When, each sprinkle nozzle Cooling Holes forms angle towards first end wall；Before each, Cooling Holes are included relative in the operation phase
Between by the flow direction of the air of the nozzle segment, compound into before 15 degree to 45 degree towards second end wall
Angle, and each intercooling hole includes relative to during operation by the flow direction of the air of the nozzle segment, direction
First end wall is into 15 degree to 45 degree of middle compound angle.
3. nozzle segment as claimed in claim 2, wherein, the fin also includes multiple rear Cooling Holes, the plurality of after cool down
Hole in the wall of the pressure side in groups together, close to the trailing edge, each rear Cooling Holes is included relative to leading to during operation
The flow direction of air of the nozzle segment is crossed towards second end wall into 15 degree to 45 degree of rear compound angle.
4. nozzle segment as claimed in claim 1, wherein, the plurality of front Cooling Holes with single-row setting, and the plurality of in
Between Cooling Holes with single-row setting.
5. nozzle segment as claimed in claim 1, wherein, first end wall is lower end wall, and second end wall is position
In from the radially outer upper end wall of the lower end wall.
6. nozzle segment as claimed in claim 1, wherein, before each Cooling Holes with adjacent front Cooling Holes with 3 to 4 diameter pitches
Separate, and each intercooling hole is separated with 3 to 4 diameter pitches with adjacent intercooling hole.
7. nozzle segment as claimed in claim 1, wherein, the plurality of sprinkle nozzle Cooling Holes are configured to guide air with air film
The guide lug and cooling first end wall is cooled down, the plurality of front Cooling Holes are configured to guide air to press described in gaseous film control
The pressure side surface of side wall and cooling second end wall, and the plurality of intercooling hole is configured to guide air cold with air film
The pressure side surface and cooling first end wall.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/924,178 US20140377054A1 (en) | 2013-06-21 | 2013-06-21 | Nozzle film cooling with alternating compound angles |
| US13/924,178 | 2013-06-21 | ||
| PCT/US2014/043235 WO2014205249A1 (en) | 2013-06-21 | 2014-06-19 | Nozzle film cooling with alternating compound angles |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105339591A CN105339591A (en) | 2016-02-17 |
| CN105339591B true CN105339591B (en) | 2017-03-15 |
Family
ID=52105298
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201480034210.0A Expired - Fee Related CN105339591B (en) | 2013-06-21 | 2014-06-19 | There is the nozzle gaseous film control of alternative expression compound angle |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20140377054A1 (en) |
| CN (1) | CN105339591B (en) |
| RU (1) | RU2016100014A (en) |
| WO (1) | WO2014205249A1 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015163949A2 (en) * | 2014-01-16 | 2015-10-29 | United Technologies Corporation | Fan cooling hole array |
| US10641103B2 (en) * | 2017-01-19 | 2020-05-05 | United Technologies Corporation | Trailing edge configuration with cast slots and drilled filmholes |
| CN107120192A (en) * | 2017-04-27 | 2017-09-01 | 上海泛智能源装备有限公司 | A kind of scroll casing type collection chamber and gas turbine |
| US11002138B2 (en) * | 2017-12-13 | 2021-05-11 | Solar Turbines Incorporated | Turbine blade cooling system with lower turning vane bank |
| US10808572B2 (en) * | 2018-04-02 | 2020-10-20 | General Electric Company | Cooling structure for a turbomachinery component |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8281604B2 (en) * | 2007-12-17 | 2012-10-09 | General Electric Company | Divergent turbine nozzle |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5326224A (en) * | 1991-03-01 | 1994-07-05 | General Electric Company | Cooling hole arrangements in jet engine components exposed to hot gas flow |
| US6749396B2 (en) * | 2002-06-17 | 2004-06-15 | General Electric Company | Failsafe film cooled wall |
| US7121787B2 (en) * | 2004-04-29 | 2006-10-17 | General Electric Company | Turbine nozzle trailing edge cooling configuration |
| US7114923B2 (en) * | 2004-06-17 | 2006-10-03 | Siemens Power Generation, Inc. | Cooling system for a showerhead of a turbine blade |
| US20060032233A1 (en) * | 2004-08-10 | 2006-02-16 | Zhang Luzeng J | Inlet film cooling of turbine end wall of a gas turbine engine |
| US7806650B2 (en) * | 2006-08-29 | 2010-10-05 | General Electric Company | Method and apparatus for fabricating a nozzle segment for use with turbine engines |
| US8328517B2 (en) * | 2008-09-16 | 2012-12-11 | Siemens Energy, Inc. | Turbine airfoil cooling system with diffusion film cooling hole |
| US9109453B2 (en) * | 2012-07-02 | 2015-08-18 | United Technologies Corporation | Airfoil cooling arrangement |
| US9464528B2 (en) * | 2013-06-14 | 2016-10-11 | Solar Turbines Incorporated | Cooled turbine blade with double compound angled holes and slots |
-
2013
- 2013-06-21 US US13/924,178 patent/US20140377054A1/en not_active Abandoned
-
2014
- 2014-06-19 CN CN201480034210.0A patent/CN105339591B/en not_active Expired - Fee Related
- 2014-06-19 WO PCT/US2014/043235 patent/WO2014205249A1/en active Application Filing
- 2014-06-19 RU RU2016100014A patent/RU2016100014A/en not_active Application Discontinuation
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8281604B2 (en) * | 2007-12-17 | 2012-10-09 | General Electric Company | Divergent turbine nozzle |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2016100014A (en) | 2017-07-26 |
| CN105339591A (en) | 2016-02-17 |
| WO2014205249A1 (en) | 2014-12-24 |
| US20140377054A1 (en) | 2014-12-25 |
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