CN105229278A - For the exhaust diffuser of gas turbine engine exhaust system - Google Patents
For the exhaust diffuser of gas turbine engine exhaust system Download PDFInfo
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- CN105229278A CN105229278A CN201480029347.7A CN201480029347A CN105229278A CN 105229278 A CN105229278 A CN 105229278A CN 201480029347 A CN201480029347 A CN 201480029347A CN 105229278 A CN105229278 A CN 105229278A
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- diffuser
- wall
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- exit
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- 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
- F01D25/30—Exhaust heads, chambers, or the like
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- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
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- General Engineering & Computer Science (AREA)
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Abstract
A kind of exhaust diffuser for gas turbine engine comprises diffusor entry, diffuser exit, interior diffuser wall and external diffusion wall.Described interior diffuser wall can comprise first tubular member with enlarging downstream part.Described external diffusion wall can comprise the second tubular member, and the second tubular member has the second enlarging downstream part around described interior diffuser wall at least in part.Described external diffusion wall and described interior diffuser wall extend between described diffusor entry and described diffuser exit, and form diverging flow passage between.Described second enlarging downstream part can comprise hypomere and epimere, and relative to diffuser axis, described epimere extends to downstream in the axial direction further than hypomere.
Description
Technical field
The present invention relates generally to gas turbine engine, relates more specifically to a kind of vent systems, and this vent systems is for comprising the combustion gas turbine of exhaust diffuser.
Background technique
Gas turbine engine produces the exhaust of high temperature and high speed.Limit exhaust diffuser by increasing flow area, this causes the flow velocity of exhaust stream to reduce, and causes again conversely increasing along its flow channel static pressure.Due to the pressure recover in diffuser, the inlet and outlet pressure of turbo machine is than increasing, and this causes output power and the thermal efficiency to increase.In addition, vent systems is used for being redirected waste gas away from upstream device or towards particular station interface.
Authorize the U. S. Patent the 5th, 257 of the people such as Gray on November 5th, 1993, No. 906 show a kind of vent systems for steam turbine.Particularly, the invention of the people such as Gray relates to a kind of vent systems, and this system has diffuser, and working fluid stream is guided to exhaust casing from turbine outlet by this diffuser, and described exhaust casing has bottom opening, thus makes air-flow from axially changing 90 degree to radial direction.In exhaust casing, the air-flow left at diffuser top is from direction vertically upward to changing 180 degree in downward direction.Because this changes, moved the outlet of guide part, make the intensity of the eddy current be formed in exhaust casing reduce to minimum, thus make it be in a plane by the air stream efflux of directional diffuser, this plane forms angle with the plane perpendicular to turbine axis.Therefore, the minimum axial length of outer flow guide appears at the position away from exhaust casing outlet, and greatest axial length appears at the position near opening, thus is accumulated in by eddy current and extend baffle plate opposite position with the radial direction in exhaust casing.
The present invention is intended to the problem overcoming known problem and/or inventor's discovery.
Summary of the invention
A kind of exhaust diffuser for gas turbine engine comprises diffusor entry, diffuser exit, interior diffuser wall and external diffusion wall.Interior diffuser wall can comprise first tubular member with enlarging downstream part.External diffusion wall can comprise the second tubular member, and described second tubular member has the second enlarging downstream part around interior diffuser wall at least in part.External diffusion wall and interior diffuser wall extend between diffusor entry and diffuser exit, and define diverging flow passage between.Second enlarging downstream part can comprise hypomere and epimere, and relative to diffuser axis, epimere extends to downstream further than hypomere in the axial direction.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of exemplary gas turbogenerator.
Fig. 2 is the isometric view of the vent systems of the gas turbine engine of Fig. 1.
Fig. 3 is the sectional view of the vent systems of Fig. 2.
Embodiment
System and method disclosed by the invention comprises the vent systems for combustion gas turbine, and described combustion gas turbine comprises axis-radial exhaust diffuser and is positioned at the radial exhaust collector in diffuser downstream.Embodiment comprises axis-radial exhaust diffuser, and wherein, described diffuser exit is reduced.
Fig. 1 is the schematic diagram of exemplary commercial gas turbine engine.In order to know and be convenient to explain, some surfaces have been omitted or have expanded (in this figure or other accompanying drawings).The present invention also will quote the central axis 95 of the rotation of gas turbine engine usually, and this central axis 95 can be limited by the longitudinal axis of its axle 120 (being supported by multiple bearing unit 150) usually.Other various motor concentric parts can have or Sharing Center's axis 95.To all references of radial, axis and circumferencial direction with measure and all refer to central axis 95, except as otherwise noted, the smaller or greater radial distance of term such as " interior " and " outward " ordinary representation institute distance, wherein, radial 96 can be arbitrarily perpendicular to central axis 95 and from central axis 95 to extraradial direction.
In addition, the present invention can quote " front " and " afterwards " direction.Usually, except as otherwise noted, all references of " front " and " afterwards " is all correlated with the flow direction of primary air (that is, the air used in combustion process).Such as, front relative to primary air stream " upstream " (that is, entering the position of this system towards air), after relative to primary air stream " downstream " (that is, leaving the position of this system towards air).
Usually, gas turbine engine 100 comprises entrance 110, compressor 200, firing chamber 300, turbine 400, vent systems 500 and power output connector 600.Compressor 200 comprises one or more compressor drum assembly 220.Firing chamber 300 comprises one or more sparger 350, and comprises one or more combustion chamber 390.Turbine 400 comprises one or more turbine rotor component 420.Vent systems 500 comprises exhaust diffuser 520 and exhaust collector 550.
In operation, air 10 enters entrance 110 as " working fluid ", and is compressed by compressor 200.In compressor 200, working fluid is compressed by a series of compressor drum assembly 220 in annular fluid passage.Once be compressed, pressurized air leaves compressor 200 and enters firing chamber 300, is diffused, and adds fuel in firing chamber 300.Fuel and pressurized air to be injected in combustion chamber 390 via sparger 350 and to be lighted.After the combustion reaction, a series of turbine rotor component 420 extracts energy via turbine 400 from the fuel/air mixture of burning.Exhaust 90 is diffused subsequently in exhaust diffuser 520.Exhaust collector 550 is collected the exhaust 90 carrying out system since then, is made it change direction and discharge.Exhaust 90 can also be further processed (such as, reduce noxious emission, and/or reclaim heat from exhaust 90).
One or more above-mentioned parts (or their subassembly) can by stainless steel and/or durable, the high temperature material that are called as " superalloy " make.Superalloy or high performance alloys are the alloys at high temperature showing good mechanical strength and creep resistance, good surface stability, corrosion resistance and oxidative stability.Superalloy can comprise following material, such as Hastelloy (HASTELLOY), inconel (INCONEL), Waspaloy (WASPALOY), RENE alloy, HAYNES alloy, incoloy (INCOLOY), MP98T, TMS alloy, CMSX single crystal alloy, alloy X, alloy 188/230 etc.
Fig. 2 is the isometric view of the vent systems of the gas turbine engine of Fig. 1.Particularly, this view normally forward with upstream finding, but independent of the remaining part of gas turbine engine 100.In order to object that is clear and that illustrate, some features/components is increased, removes and/or revises.Such as, in this view, the rear wall 554 of exhaust collector 550 is only partially illustrated.
Fig. 3 is the sectional view of the vent systems of Fig. 2.Particularly, this side view is consistent with flowing symmetry plane.Described symmetry plane is formed by central axis 95 and discharge direction 559.In order to object that is clear and that illustrate, some features/components is increased, removes and/or schematically shows.Such as, be schematically illustrated in the parts (such as, axle 120 and bearing 150) of interior diffuser wall 523 inside in this view, wherein optional feature is removed.
As shown in Figures 2 and 3, exhaust diffuser 520 is axial-radial diffusers, it is configured to pneumatically connect with turbine 400 (Fig. 1) and exhaust collector 550, and forms flow channel between turbine 400 (Fig. 1) and exhaust collector 550.Usually, exhaust diffuser 520 can be contemplated to be two concentric structures (such as, pipe) with diffuser axis 535, and it is connected to each other by the multiple pillars 525 around diffuser axis 535 circle distribution.When exhaust diffuser 520 is arranged on gas turbine engine 100, diffuser axis 535 can be consistent with central axis 95.Therefore, during installation, flow channel can be the annular vent flow channel between turbine 400 and exhaust collector 550, is only cut off by pillar 525 itself.Conveniently, central axis 95 will mean to comprise diffuser axis 535 hereinafter.
Exhaust diffuser 520 comprises diffusor entry 521, diffuser exit 522, interior diffuser wall 523 and external diffusion wall 524.Exhaust diffuser 520 be configured on cardinal principle axial direction via diffusor entry 521 receive from turbine 400 exhaust 90.Exhaust diffuser 520 is further configured to and substantially via diffuser exit 522, exhaust 90 is being discharged to exhaust collector 550 in the radial direction.
Interior diffuser wall 523 and external diffusion wall 524 are the generic tubular component around central axis 95.Interior diffuser wall 523 comprises the first enlarging downstream part 541, and described first enlarging downstream part 541 is near the diffuser exit 522 extended radially outwardly.Similarly, external diffusion wall 524 comprises the second enlarging downstream part 543, and it is near the diffuser exit 522 extended radially outwardly.
At upstream extremity, it is inner that interior diffuser wall 523 is radially placed in external diffusion wall 524.In downstream, interior diffuser wall 523 extends axially beyond external diffusion wall 524.Interior diffuser wall 523 and external diffusion wall 524 can be linked together by the multiple pillars 525 extended betwixt.According to an embodiment, interior diffuser wall 523 and external diffusion wall 524 can be concentric at least in part.
Interior diffuser wall 523 and external diffusion wall 524 form diffusor entry 521 and diffuser exit 522 jointly.Particularly, diffusor entry 521 can be the annular opening formed by the concentric upstream extremity of interior diffuser wall 523 and external diffusion wall 524.Similarly, diffuser exit 522 can be the perimeter band opening formed by the axial displacement of the first enlarging downstream part 541 and the second enlarging downstream part 543.According to an embodiment, diffusor entry 521 and diffuser exit 522 can be cut off by the component extended between interior diffuser wall 523 and external diffusion wall 524 or traverse (such as, pillar, blade etc.).
Interior diffuser wall 523 and external diffusion wall 524 are also common forms flow channel between turbine 400 and exhaust collector 550.Particularly, the outer surface of interior diffuser wall 523 and the internal surface of external diffusion wall 524 form annular flow passage between turbine 400 and exhaust collector 550.When flow channel advanced downstream, it is transformed into is mainly radially outer perimeter band shape from being mainly annular shape.According to an embodiment, flow channel can be cut off by the component extended between interior diffuser wall 523 and external diffusion wall 524 or traverse (such as, pillar, blade etc.).
In addition, the shape of the internal surface of interior diffuser wall 523 and the outer surface of external diffusion wall 524 can be different from their opposite flank (as mentioned above).Such as, the internal surface of interior diffuser wall 523 and the outer surface of external diffusion wall 524 can have shape or the cascade cylinder form (there is different diameters on every rank) of general cylindrical.On the other hand, some part of the internal surface of interior diffuser wall 523 and the outer surface of external diffusion wall 524 can be cylindrical or cascade, and other partial shapes can be similar to their respective opposite flanks.It should be noted that unless otherwise expressly specified, internally the discussion of diffuser wall 523 and external diffusion wall 524 refers to flow channel surface (that is, the outer surface of interior diffuser wall 523 and the internal surface of external diffusion wall 524) hereinafter.
As shown in the figure, exhaust collector 550 is radial exhaust collectors, it is configured to pneumatically connect with exhaust diffuser 520, " collection " exhaust 90 and be redirected it with single, discharge direction 559 easily, radially away from gas turbine engine 100 (Fig. 1).In one embodiment, exhaust collector 550 is the housings round exhaust diffuser 520, and has the single opening in a substantially radial direction for being vented 90 discharges.Here, exhaust collector 550 be configured to radial receive exhaust 90 and change its direction be radial direction upwards, or along with the discharge direction 559 of top dead center (TDC) into about 0 degree or ± 5 degree, there is no axial component.
Exhaust collector 550 comprises exhaust collector outlet 551, antetheca 552, peripheral wall 553 and rear wall 554.Exhaust collector 550 is configured to substantially receiving exhausting air 90 via diffuser exit 522 from exhaust diffuser 520 in the radial direction.Exhaust collector 550 is configured to discharge exhausting air 90 via exhaust collector outlet 551 in the discharge direction 559 away from gas turbine engine 100 further.
Antetheca 552, peripheral wall 553 and rear wall 554 are common around diffuser exit 522, make the exhausting air 90 of discharging be directed to exhaust collector outlet 551.Particularly, peripheral wall 553 can surround the major part of diffuser exit 522 around central axis 95, and fully offsets with the air-flow received from diffuser exit 522.In addition, peripheral wall 553 is bonded to front side by antetheca 552, and is bonded to rear side by rear wall 554.
In addition, each in antetheca 552 and rear wall 554 can extend radially inwardly from peripheral wall 553, and closely cooperates respectively with external diffusion wall 524 and interior diffuser wall 523 and/or any intermediate member.According to an embodiment, antetheca 552 can be vertical wall, and this vertical wall is attached to the external diffusion wall 524 in diffuser exit 522 front, and described rear wall 554 can be vertical wall, and this vertical wall is attached to the interior diffuser wall 523 at diffuser exit 522 rear.
Antetheca 552, peripheral wall 553 and rear wall 554 form exhaust collector outlet 551 jointly.Particularly, exhaust collector outlet 551 can be the opening formed by the upstream extremity of antetheca 552, peripheral wall 553 and rear wall 554.Such as, the upstream extremity of antetheca 552, peripheral wall 553 and rear wall 554 can couple together, and forms the single-pathway leaving outer cover.Exhaust collector outlet 551 can be any suitable shape and the orientation towards discharge direction 559.Such as and as shown in the figure, exhaust collector outlet 551 can have rectangular shape, and this rectangular shape is perpendicular to discharge direction 559.
According to an embodiment, exhaust collector outlet 551 can comprise one or more transition member, and this transition member is configured to utilize additional exhaust pipeline adjoining exhaust trap 550.Particularly, one or more transition member can closely cooperate with both exhaust collector 550 (have the first shape and/or effectively flow region) and additional exhaust pipeline (have second, difformity and/or effective flow area), transition between.Such as, exhaust collector outlet 551 can comprise cover cap, and this cover cap is configured to connect the exhaust collector outlet 551 of most rectangular shape and first effective flow area, and transits to the circular gas exhausting pipe road with second effective flow area.Again such as, one or more transition member can angle of inclination, irregular or asymmetric shape or other suitable way, with exhaust collector export 551 and/or additional exhaust pipeline engage.
Although exhaust collector 550 is configured to upwards discharge exhaust 90 at this, exhaust collector 550 can be configured to discharge exhaust 90 along other discharge direction 559.Such as, exhaust collector 550 can be configured to the radial TDC laterally or along the about +/-90 degree never axial component of discharge direction 559 and discharge exhaust 90.Again such as, exhaust collector 550 can be configured to discharge exhaust 90 along any discharge direction 559 at the TDC that+90 spend never axial component between-90 degree.According to another embodiment, exhaust collector 550 can be configured to discharge exhaust 90 along any discharge direction 559 at the TDC that+135 spend never axial component between-135 degree.Selectively, exhaust collector 550 can be configured to the scope along any above-mentioned discharge direction 559 or discharge direction 559, but has the axial component being up to 45 degree backward, discharges exhaust 90.
Exhaust diffuser 520 can be installed on turbo machine 400, and is configured to axially receive the exhausting air 90 leaving turbo machine 400 with main axial flow 531.As shown in the figure, main axial flow 531 can have relative to the velocity vector of central axis 95 between +/-15 degree, but is not more than +/-45 degree relative to central axis 95.Exhaust diffuser 520 can be configured to spread exhausting air 90 further, provides radial component, and radially discharge exhaust 90 as the main Radial Flow 532 around central axis 95 and enter exhaust collector 550 to its flowing.As shown in the figure, main Radial Flow 532 can have relative to the velocity vector of central axis 95 between 75 degree and 105 degree, but is not less than 45 degree relative to central axis 95 and is not more than 135 degree.
Exhaust collector 550 can be installed in exhaust diffuser 520 and/or any other supporting structure.Exhaust collector 550 can be configured to receive the exhaust 90 of discharging from diffuser exit 522, and reboot its around and towards exhaust collector outlet 551, and discharge exhaust 90 along discharge direction 559.
Exhaust diffuser 520 can comprise linear diffusion zone 526, follows by turn-around zone 527.Linear diffusion zone 526 shape can be annular frustum of a cone, or like this, and it is configured to the effective flow area between interior diffuser wall 523 and external diffusion wall 524 is increased from diffusor entry 521 to turn-around zone 527.Particularly, effective flow area can increase relative to the operational condition of exhaust 90, reclaims and control separation to increase.Such as, by increasing relative to the distance between the diffusor entry 521 of flow channel and diffuser exit 522, effective flow area can be made to increase along flow channel.Again such as, by increasing the average perimeter of flow channel, effective flow area can be made to increase along flow channel.
According to an embodiment, linear diffusion zone 526 can comprise angled flow passages.Especially, interior diffuser wall 523 can form truncated cones around central axis 95.Such as, interior diffuser wall 523 can on downstream direction with the angle of central axis 95 one-tenth 0 degree to 15 degree.In addition, again such as, interior diffuser wall 523 can on downstream direction with the angle of central axis 95 one-tenth 3 degree to 10 degree.In addition, again such as, interior diffuser wall 523 can on downstream direction the angle of about with central axis 95 one-tenth 5 degree.
Turn-around zone 527 is for starting from linear diffusion zone 526 and ending at the bending area in diffuser exit 522 downstream.Turn-around zone 527 is configured to add radial component to the velocity vector of exhaust 90, and the velocity vector of exhaust 90 is turned to into main Radial Flow 532 from main axial flow 531.
Linear diffusion zone 526 and turn-around zone 527 can comprise the separable axial part of interior diffuser wall 523 and external diffusion wall 524.Especially, in part, diffuser wall 523 or part external diffusion wall 524 can in conjunction with to form linear diffusion zone 526.Similarly, in part, diffuser wall 523 or part external diffusion wall 524 can in conjunction with to form turn-around zone 527.
In addition, each axial part forming linear diffusion zone 526 and turn-around zone 527 can combine smoothly, makes linear diffusion zone 526 overlapping at their junction point with the tangent line of turn-around zone 527.Such as, interior diffuser wall 523 can comprise the first surface of revolution around diffuser axis 535, and wherein, this first surface of revolution comprises the first conical area and the first enlarging downstream part 541.Similarly, external diffusion wall 524 can comprise the second surface of revolution around diffuser axis 535, wherein, this second surface of revolution comprises the second conical area and the second enlarging downstream part 543 (the second enlarging downstream part 543 further described) of level and smooth combination herein.
In addition, interior diffuser wall 523 and external diffusion wall 524 can the one or more parts of each freedom or its combination in any be made.Particularly, interior diffuser wall 523 and/or external diffusion wall 524 can be made up of multiple department of assembly.In addition, each parts or assembly can differently and manufacture according to its shape or replaceability.
Such as, interior diffuser wall 523 and/or external diffusion wall 524 can be made up of multiple department of assembly.In addition, such as, interior diffuser wall 523 and external diffusion wall 524 (comprising pillar 525) can be made into input unit 528 (such as, single foundry goods), wherein, the remainder of interior diffuser wall 523 and external diffusion wall 524 is the overlapped assembly of annular wall.Again such as and as shown in the figure, linear diffusion zone 526 can be made as the overlapped assembly of input unit 528 and annular wall, and turn-around zone 527 can be made up of the first enlarging downstream part 541 and the second enlarging downstream part 543.
According to an embodiment, exhaust diffuser 520 can be biased.Particularly, the second enlarging downstream part 543 can comprise hypomere 536 and epimere 537, and wherein, about diffuser axis 535, compared with hypomere 536, epimere 537 is in the axial direction to further downstream extension.Therefore, and compared with the downstream pipe end perpendicular to diffuser axis 535, here, hypomere 536 and epimere 537 can end at skew end 540.Note, use term " epimere " and " hypomere " so that describe the opposite side of vertically (0 degree) second expansion downstream part 543 shown in discharge configuration, but, also may be embodied as other counterpart, especially there is the releasing system of non-zero degree emission direction.Such as, in the application with 90 degree of emission directions, term " epimere " and " hypomere " can be replaced with " right section " and " left section " respectively.
As shown in the figure, skew end 540 substantially can limit and block plane 549.Block plane 549 to be formed with vertical plane 548 and regain angle 546, wherein, vertical plane 548 is perpendicular to diffuser axis 535.Regaining angle 546 can with vertical plane 548 into about 2 degree.Alternately, regain angle 546 can with vertical plane 548 one-tenth 1 degree to 5 degree.
Similarly, exhaust diffuser 520 can comprise biased external diffusion wall 524.Particularly, external diffusion wall 524 can comprise even section 538 and skew extension part 539, and they are combined and can comprise above-mentioned hypomere 536 and epimere 537.Such as, even section 538 can extend from diffusor entry 521 to downstream, and comprises surface of revolution.This surface of revolution can be limited by the two-dimensional curve rotated around diffuser axis 535, and this two-dimensional curve comprises linearity range and bending section.In addition, skew extension part 539 can extend to diffuser exit 522 from even section 538 to downstream, and comprises the surface of revolution blocked, and ends at above-mentioned skew end 540.
According to an embodiment, exhaust diffuser 520 can comprise and exports 551 " reduction " external diffusion walls 524 (such as expanding in downstream part 543 second) coordinated with exhaust collector.Particularly, external diffusion wall 524 can comprise complicated shape, its can by be described as having disappearance expediently or " reduction " downstream part, basic, " uncut " shape, wherein, the part of disappearance is located substantially on opposite side or the side diametrically substantially of exhaust collector outlet 551.
In addition, basic, " uncut " shape can be the surface of revolution around central axis 95, and " reduction " can comprise the inclined cut angle relative to central axis 95, makes it comprise the maximum withdrawal contrary with discharge direction 559.In addition, the surface of revolution around central axis 95 can comprise above-mentioned linear diffusion zone 526 and turn-around zone 527.
Such as, surface of revolution can be limited by the two-dimensional curve rotated around central axis 95, and described two-dimensional curve comprises linearity range and bending section, and wherein linearity range aligns with the tangent line of bending section.Linearity range and bending section can be shaped, directed, location, above-mentioned for the linear diffusion zone 526 of external diffusion wall 524 and the surface of revolution of turn-around zone 527 to be formed.
Maximum withdrawal 545 is point or the part of external diffusion wall 524, and it corresponds to maximum lack part, truncation part or " reduction " from basic " uncut " shape.Especially, external diffusion wall 524 can its downstream have a single point (or when cutting part for plane time several points), this than other downstream end points on external diffusion wall 524 more away from the downstream of basic " uncut " shape.
Maximum withdrawal 545 can along curved measurement.Such as, for each point (that is, each point in the downstream of external diffusion wall 524) external diffusion wall 524 being formed diffuser exit 522 part, central axis 95 and described point can form plane.Correspondingly, the curve corresponding to each point can be limited by the intersection point of its respective planes and basic " uncut " shape.Then maximum withdrawal 545 can be defined as the point (or part) of external diffusion wall 524, and it forms the part of diffuser exit 522 and the longest extrapolation had along plane inner curve from the respective point diffuser exit 522 to the downstream of basic " uncut " shape.
Maximum withdrawal 545 can centrally be measured by axis 95.Such as, maximum withdrawal 545 can comprise the point (or part) of external diffusion wall 524, it forms the part of diffuser exit 522, and has from the maximum axial distance of reference plane, and described reference plane are perpendicular to central axis 95 and be positioned at the rear portion of diffuser exit 522.
Alternatively, maximum withdrawal 545 can radially 96 be measured.Especially, maximum withdrawal 545 can comprise the point (or part) of external diffusion wall 524, and it forms the part of diffuser exit 522, and has along same radial from the maximum radial distance of the point in peripheral wall 553.Because peripheral wall 553 can at it close to opening during discharge direction 559 or otherwise increasing its radius, the measurement of this maximum withdrawal 545 can be restricted to and be greater than in radial direction 96 scope of 180 degree from discharge direction 559.
According to an embodiment, " reduction " of external diffusion wall 524 can be arranged in the second enlarging downstream part 543.Especially, the second enlarging downstream part 543 of external diffusion wall 524 can comprise bevel shape.Such as, the second enlarging downstream part 543 can comprise the surface of revolution around central axis 95, and it closes on diffuser exit 522 by bevel, and also comprises the maximum withdrawal 545 contrary with discharge direction 559.
In order to illustrate, the second enlarging downstream part 543 can comprise bevel horn bell type, its have radially with respect to exhaust collector outlet 551 substantially splaying of alignment subtract part.Especially, bevel second enlarging downstream part 543 can comprise the shape intercepted from basic " uncut " flare form.Splay and subtract part and generally refer to relative to intercepting from basic " uncut " shape or the surface of the second enlarging downstream part 543 of cutting.Basic " uncut " flare form is enlarging surface of revolution, and described surface is limited by the two-dimensional curve rotated around central axis 95.In addition, the upstream extremity of two-dimensional curve can tangentially align corresponding to the line of above-mentioned linear diffusion zone 526, thus seamlessly transits in their interface formation.
As shown in the figure, two-dimensional curve can be essentially the quadrant (such as, between 75 degree and 105 degree) with enlarging radius 544, and is oriented such that the tangent downstream through two-dimensional curve of the radial direction 96 of central axis 95.Also as shown in the figure, enlarging radius 544 can dock with diffuser exit 522 (namely stopping downstream) is constant.Meanwhile, for reference, show extrapolation line 547, instruction two-dimensional curve is at the continuation enlarging radius of the lack part at its maximum withdrawal 545 place.
Similarly, two-dimensional curve can by other non-circular Surface forming.Especially, two-dimensional curve can comprise the nonlinear curve with about 90 degree of arcs.Such as, two-dimensional curve can have the arc between 75 degree and 105 degree.According to an embodiment, the enlarging radius 544 of the second enlarging downstream part 543 can be concentric with the enlarging radius of the first enlarging downstream part 541.
Bevel second enlarging downstream part 543 can be described as basic " uncut " flare form and block, difference between " reduction " of lack part or basic " uncut " flare form.Here, truncation part comprises between vertical plane 548 and the part of blocking basic " uncut " flare form between plane 549.
Vertical plane 548 perpendicular to central axis 95, and limits the whole downstream of basic " uncut " flare form.At least one point of the downstream of the second enlarging downstream part 543 of bevel is positioned on vertical plane 548.Block plane 549 perpendicular to flowing symmetry plane, but favour vertical plane 548 by regaining angle 546.According to an embodiment, regaining angle 546 can be less than 10 degree relative to Vertical direction.According to another embodiment, regaining angle 546 can relative to Vertical direction between 1 degree and 5 degree.According to another embodiment, regaining angle 546 can be about 2 degree relative to Vertical direction.Alternatively, truncation part can comprise the part of basic " uncut " flare form between vertical plane 548 and non-planar surface are cut down.
Second enlarging downstream part 543 and the exhaust collector of bevel export 551 phases and are truncated in phase.Particularly, the maximum withdrawal 545 of the second enlarging downstream part 543 of described bevel is alignd with exhaust collector turn-around zone 555.Described exhaust collector turn-around zone 555 is defined as the region that be positioned at exhaust collector 550 relative with discharge direction 559 usually, herein, is separated into the relative peripheral flow around circumferential wall 553 from the exhaust 90 of diffuser exit 552 discharge.Such as, here, described exhaust collector turn-around zone is positioned at the bottom of exhaust collector 550.Correspondingly, here, described external diffusion wall 524 comprises maximum withdrawal 545 or maximumly to block in bottom.
As mentioned above, maximum withdrawal 545 is external diffusion walls 524 and maximumly to block, lack part, or the point (or part) that " reductions " of basic " uncut " subtended angle is corresponding, and can along central axis 95 and/or radial 96 measurements.In addition, described maximum withdrawal 545 can be measured relative to its subtended angle.Particularly, described maximum withdrawal 545 can comprise the point (or part) of external diffusion wall 524, and it forms diffuser exit 552 part, and has minimum subtended angle and radian.As mentioned above, the second enlarging downstream part 543 can cut out from the surface of revolution around central axis 95.Such as, the enlarging degree on described external diffusion wall 524 is constant at each axial position.Correspondingly, such as, the discharge direction 559 of exhaust collector 550 relative to TDC upwards or in 0 degree time, the subtended angle at described second top, enlarging downstream part 543 can have maximum radian (such as, about 90 degree), and the subtended angle bottom the second enlarging downstream part 543 can have minimum curvature (such as, about 50 degree).
According to an embodiment, interior diffuser wall 523 can have the shape being similar to external diffusion wall 524.Especially, the first enlarging downstream part 541 can comprise the surface of revolution around central axis 95, and this surface of revolution comprises and has 75 degree to 105 degree radians and the enlarging stopped on the less perpendicular direction of diffuser exit 522.In addition, the first enlarging downstream part 541 can through the radian substantially identical with the maximum radian of the second enlarging downstream part 543.Such as, interior diffuser wall 523 can comprise an enlarging, it is concentric with the enlarging radius 544 of the second enlarging downstream part 543, and the central axis 95 comprised in discharge direction 559 with the plane of radial 96 have about 90 degree of radians with the second enlarging downstream part 543.In addition, the downstream of interior diffuser wall 523 can tangentially be alignd rear wall 554, forms smooth engagement thus at its interface.
Further, interior diffuser wall 523 and external diffusion wall 524 can offset each other.Particularly, as measured in the plane comprising central axis 95, skew comprises the radial separation of the substantial constant by total radian.Such as, interior diffuser wall 523 and external diffusion wall 524 can be offset by its total radian each other by the length of enlarging radius 544.Again such as, interior diffuser wall 523 and external diffusion wall 524 can be offset by its total radian each other by the length of enlarging radius 544+/-20%.
According to an embodiment, the second enlarging downstream part 543 of bevel can be configured to, and makes maximum withdrawal 545 provide minimum clearance 557 between the diffuser exit 522 at maximum withdrawal 545 place and circumferential wall 553.Especially, second enlarging downstream part 543 of bevel can be truncated, to provide the minimum clearance 557 of the spacing of interior diffuser wall 523 and external diffusion wall 524, it is at least the half of the spacing of diffuser exit 522 place's external diffusion wall 524 and circumferential wall 553, and measures in the plane comprising in central axis 95 and maximum withdrawal 545 a bit.Such as, as shown in the figure, when circumferential wall 553 trend is parallel to central axis 95, the second enlarging downstream part 543 of bevel can be truncated, and the minimum clearance 557 between external diffusion wall 524 and circumferential wall 553 is measured along the radial direction 96 through maximum withdrawal 545.
According to an embodiment, exhaust collector 550 can comprise " expansion " exhaust collector turn-around zone 555.Particularly, antetheca 552 can be configured to the minimum axial direction distance 558 making to obtain rear wall 554 and to maintain in exhaust collector turn-around zone 555 and near circumferential wall 553.Such as, minimum axial direction distance 558 can be at least four times of minimum clearance 557.Such as state again minimum axial direction distance 558 and at least double distance in diffuser exit 522 place between diffuser wall 523 and external diffusion wall 524, minimum axial direction distance 558 is measured in the plane of point comprising central axis 95 and maximum withdrawal 545.Again such as, minimum axial direction distance 558 can be roughly the same near the axial distance between the antetheca 552 of diffuser exit 522 and rear wall 554 with relative to exhaust collector turn-around zone 555.
In the above example, antetheca 552 can be angled or non-perpendicular.Such as, antetheca 552 can be angled, to provide expanded volume in discharge direction 559.Alternatively, antetheca 552 and rear wall 554 can be substantially parallel to each other (such as, both are all vertical), make minimum axial direction distance 558 substantially evenly near exhaust diffuser 520.Alternatively, antetheca 552 can be substantially vertical.
Industrial applicibility
The present invention is applicable to vent systems substantially, and this vent systems is used for gas turbine engine and has the gas turbine engine of exhaust diffuser.Described embodiment is not limited to be combined with the gas turbine engine of particular type, but can also be applied to fixed or portable gas turbine engine or its variant any.When applying, gas turbine engine and assembly thereof are applicable to multiple commercial Application, such as but not limited to, such as, each side (comprising the transport of oil and natural gas, collection, storage, recovery and lifting) of oil and natural gas industry, power generation industries, space flight and transport industry.
In general, the embodiment of the vent systems of gas turbine engine disclosed by the invention is applicable to use, runs, maintains, keeps in repair and improves gas turbine engine, and may be used for raising performance and efficiency, reduces M R, and/or reduces costs.In addition, the embodiment of vent systems disclosed by the invention is applicable to any stage in gas turbine engine working life, from being designed into shaping and manufacturing first, and until end of life.Therefore, as preventive measure or when even responding accident, this vent systems can be used as repacking and the strengthening of existing gas turbine engine.In addition, the feature of various combination goes for transforming previous designs.Have with the gas turbine engine of another vent systems same-interface when vent systems disclosed by the invention can be arranged on, so that when exchanging with the vent systems compared with prior types, this situation is especially true.
The gas turbine engine with exhaust collector and radial discharge direction can have lazy flow region at the opposite side of exhaust collector outlet (exhaust collector pivot region), with towards diffuser outlet.The embodiment of vent systems disclosed by the invention can comprise and assemblage characteristic, such as, export with exhaust collector biased or " reduction " external diffusion wall combined, the interior diffuser wall of enlarging, and " expansion " exhaust collector turn-around zone, to reduce the pressure of turbine outlet.Therefore, the invention provides a kind of exhaust diffuser, wherein, extend relative to the radial direction of discharge direction, external diffusion wall is cut down in lazy flow region or radial direction extends less, therefore decreases the size of self and potential obturator in turn-around zone inside.
As mentioned above, use vent systems to increase turbine pressure ratio, produce more axle power and higher efficiency.Particularly, by substantial analysis and empirical test, compared to previous design, inventor has found that efficiency significantly improves.Therefore, the combination of preceding feature can provide the engine performance of overall improvement.
Aforementioned detailed description is only exemplary in essence, is not intended to restriction the present invention or application of the present invention and purposes.Described embodiment is not limited to be combined with the gas turbine engine of particular type.Therefore, although for the ease of explaining, the embodiment of the present invention is illustrated and is described as implementing in stationary gas turbogenerator, should be understood that, it can implement in various other types gas turbine engine and various other system and environment.In addition, any arbitrary principle being present in preceding sections does not limit the present invention.Will also be appreciated that example illustrates and can comprise the size and graphical illustration exaggerated, with in order to describe shown reference items better, and unless expressly stated, otherwise not thinking for restriction.
Claims (10)
1. the exhaust diffuser for gas turbine engine (100) (520), described exhaust diffuser (520) comprising:
Diffusor entry (521);
Diffuser exit (522);
Interior diffuser wall (523), it comprises the first tubular member extended between described diffusor entry (521) and described diffuser exit (522) around diffuser axis (535), described first tubular member comprises the first enlarging downstream part (541) near described diffuser exit (522), and
External diffusion wall (524), it comprises around described diffuser axis (535) and at least partly around the second tubular member of described interior diffuser wall (523) and extension between described diffusor entry (521) and described diffuser exit (522), described external diffusion wall (524) and described interior diffuser wall (523) form diverging flow passage between described diffusor entry (521) and described diffuser exit (522), described second tubular member comprises the second enlarging downstream part (543), described second enlarging downstream part (543) comprises
Hypomere (536), and
Epimere (537), relative to described diffuser axis (535), described epimere (537) extends to downstream in the axial direction further than described hypomere (536).
2. exhaust diffuser according to claim 1 (520), wherein, described external diffusion wall (524) comprises further:
Even section (538), it extends from described diffusor entry (521) to downstream, described even section (538) comprises surface of revolution, described surface of revolution limited by the two-dimensional curve rotated around described diffuser axis (535), described two-dimensional curve comprises linearity range (526) and bending section, and
Skew extension part (539), it extends to described diffuser exit (522) from described even section (538) to downstream, described skew extension part (539) comprises the surface of revolution blocked ending at skew end (540), described skew end (540) defines substantially blocks plane (549), described plane (549) of blocking defines the withdrawal angle (546) with vertical plane (548), described vertical plane (548) is perpendicular to described diffuser axis (535), described withdrawal angle (546) becomes 1 to 5 to spend with described vertical plane (548), and
Wherein, described even section (538) and described skew extension part (539) are together around described hypomere (536) and described epimere (537).
3. exhaust diffuser according to claim 1 (520), wherein, described first enlarging downstream part (541) extends radially outwardly from described diffuser axis (535), and the surface of revolution comprised around described diffuser axis (535), described surface of revolution comprises the enlarging of the radian with 75 degree to 105 degree, and described enlarging ends at described diffuser exit (522) place on the direction being essentially perpendicular to described diffuser axis (535).
4. according to exhaust diffuser in any one of the preceding claims wherein (520), it comprises multiple diffuser pillar (525) further, its circumference is distributed in described diffuser axis (535) around, and extends between described external diffusion wall (524) and described interior diffuser wall (523).
5. the vent systems for gas turbine engine (100) (500), described vent systems (500) comprises exhaust diffuser in any one of the preceding claims wherein (520), and comprise further and be configured to receive the exhaust collector (550) from the exhaust (90) of described diffuser exit (522) periphery, described exhaust collector (550) comprising:
Exhaust collector outlet (551), it is positioned at the position relative substantially with described hypomere (536) relative to described diffuser axis (535),
Antetheca (552),
Rear wall (554), and
Peripheral wall (553), it extends between described antetheca (552) and described rear wall (554), and described peripheral wall (553) is around the major part of described diffuser exit (522).
6. vent systems according to claim 5 (500), wherein, described exhaust collector (550) comprises the exhaust collector turn-around zone (555) contrary with described discharge direction (559) further; And
Wherein, described antetheca (552) and described rear wall (554) minimally axial distance (558), described minimum axial direction distance (558) is at least twice of the distance in described in described diffuser exit (522) place between diffuser wall (523) and described external diffusion wall (524), and it measures in the plane comprising the point in described diffuser axis (535) and described hypomere (536) maximum withdrawal (545).
7. exhaust diffuser according to claim 5 (520), it is included in the minimum clearance (557) between the described diffuser exit (522) at maximum withdrawal (545) place of described hypomere (536) and described peripheral wall (553) further, described minimum clearance (557) is at least half of the spacing of diffuser wall (523) and described external diffusion wall (524) in described in described diffuser exit (522) place, and it measures in the plane comprising described diffuser axis (535) and the point on described maximum withdrawal (545).
8. vent systems according to claim 5 (500), wherein, described gas turbine engine (100) comprises central axis (95); And
Wherein, described exhaust collector outlet (551) is configured to relative to described gas turbine engine (100), radially discharges described exhaust (90) from top dead center in the discharge direction (559) between positive 135 degree and negative 135 degree of described central axis (95).
9. vent systems according to claim 5 (500), wherein, described antetheca (552) is vertical substantially.
10. according to exhaust diffuser in any one of the preceding claims wherein (520), wherein, the surface of revolution of described brachymemma is limited at least in part by the two-dimensional curve rotated around described diffuser axis (535), described two-dimensional curve comprises the linear segment of upstream extremity and the curved portion of downstream, and described linear segment aligns with the tangent line of described curved portion in point of intersection.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/902619 | 2013-05-24 | ||
| US13/902,619 US20140348647A1 (en) | 2013-05-24 | 2013-05-24 | Exhaust diffuser for a gas turbine engine exhaust system |
| PCT/US2014/039038 WO2014190095A1 (en) | 2013-05-24 | 2014-05-21 | Exhaust diffuser for a gas turbine engine exhaust system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105229278A true CN105229278A (en) | 2016-01-06 |
Family
ID=51934129
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201480029347.7A Pending CN105229278A (en) | 2013-05-24 | 2014-05-21 | For the exhaust diffuser of gas turbine engine exhaust system |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20140348647A1 (en) |
| CN (1) | CN105229278A (en) |
| DE (1) | DE112014002109T5 (en) |
| RU (1) | RU2015152287A (en) |
| WO (1) | WO2014190095A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109630219A (en) * | 2018-12-16 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of gas turbine exhaust |
| CN113646544A (en) * | 2019-04-03 | 2021-11-12 | 罗伯特·博世有限公司 | Delivery unit for delivering and/or controlling a gaseous medium for a fuel cell system |
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| US9347367B2 (en) * | 2013-07-10 | 2016-05-24 | Electro-Motive Diesel, Inc. | System having dual-volute axial turbine turbocharger |
| CN107923247B (en) | 2015-08-12 | 2020-12-25 | 通用电气公司 | Diffuser for a turbine engine and method of forming the same |
| US20170241294A1 (en) * | 2016-02-18 | 2017-08-24 | Solar Turbines Incorporated | Exhaust system for gas turbine engine |
| GB2548582B (en) * | 2016-03-22 | 2019-02-06 | Cummins Ltd | Turbine Diffuser and Method of Manufacture of a Turbine Diffuser |
| KR20180082118A (en) * | 2017-01-10 | 2018-07-18 | 두산중공업 주식회사 | Cut-back of blades or vanes of gas turbine |
| EP3354868A1 (en) * | 2017-01-30 | 2018-08-01 | General Electric Company | Asymmetric gas turbine exhaust diffuser |
| PL243501B1 (en) | 2018-12-28 | 2023-09-04 | Gen Electric | Turbine exhaust manifold |
| DE102019101602A1 (en) * | 2019-01-23 | 2020-07-23 | Man Energy Solutions Se | Fluid machine |
| PL434311A1 (en) * | 2020-06-15 | 2021-12-20 | General Electric Company | Exhaust manifold conversion system and method |
| US20230030721A1 (en) * | 2021-07-29 | 2023-02-02 | Solar Turbines Incorporated | Narrow, high performance collector design |
| US11732611B1 (en) * | 2022-01-31 | 2023-08-22 | Solar Turbines Incorporated | Long-arm flange design for connecting and supporting thin-walled parts subject to high bending and thermal loads |
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- 2014-05-21 RU RU2015152287A patent/RU2015152287A/en not_active Application Discontinuation
- 2014-05-21 DE DE112014002109.1T patent/DE112014002109T5/en not_active Withdrawn
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| CN113646544A (en) * | 2019-04-03 | 2021-11-12 | 罗伯特·博世有限公司 | Delivery unit for delivering and/or controlling a gaseous medium for a fuel cell system |
Also Published As
| Publication number | Publication date |
|---|---|
| DE112014002109T5 (en) | 2016-01-14 |
| RU2015152287A (en) | 2017-06-27 |
| WO2014190095A1 (en) | 2014-11-27 |
| US20140348647A1 (en) | 2014-11-27 |
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