CN101886553A

CN101886553A - Turbine nozzle with sidewall cooling plenum

Info

Publication number: CN101886553A
Application number: CN2010101841453A
Authority: CN
Inventors: G·M·伊策尔; D·R·约翰斯; E·A·西沃尔
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2009-05-11
Filing date: 2010-05-11
Publication date: 2010-11-17
Also published as: DE102010016620A1; CH701041A2; JP2010261460A; US20100284800A1

Abstract

The present invention relates to a kind of turbine nozzle with sidewall cooling plenum.Particularly, turbine nozzle section (10) comprises outer neckband (12), interior neckband (20), and at least one nozzle guide vane (30) that extends between neckband.Cooling plenum (46) is limited in wherein one of at least the cooperation side (18) of neckband, and along laterally extending through corresponding neckband at least in part.First cooling channel (48) and second cooling channel (49) extend to corresponding first cooling chamber (38) and second cooling chamber (40) from cooling plenum.

Description

Turbine nozzle with sidewall cooling plenum

Technical field

The present invention relates generally to turbine, and relates more specifically to a kind of device of the location in order to the cooling jet section.

Background technique

In typical combustion gas turbine, turbine section is installed in the outlet port of burner, and therefore is exposed in the combustion gas of extreme temperatures.In order to protect turbine component to avoid hot combustion gas, utilize cooling medium that they are cooled off usually.(for example, rotor blade and nozzle guide vane) a kind of common method is from compressor drainage part pressurized air to the cooled turbine airfoil member, and these drainage air are guided to inner passage in the member.Air circulates via the inner passage, so that from the element structure heat extraction.Air can flow out via the little film cooling hole that is formed in the aerofoil profile part, so that produce the cooling air thin layer from the teeth outwards.The film cooling also can be used for interior shroud (band) and outer shroud.In the case, shroud comprises radially the film cooling hole via its extension, and cooling air passes the film cooling hole and form the cooling air film on the hot side of shroud.

For known turbine nozzle structure, neckband and outer neckband in each nozzle section in a plurality of casting nozzle sections includes, and one or more nozzle guide vane.The matching surface of neckband comprises the sealing notch of accommodating Sealing, and the sealing part extends between the neckband of adjacent nozzle section.By make cooling medium pass the bin (plenum) in the peripheral band portion of each nozzle section, the one or more cavitys that pass in the nozzle guide vane come cooling jet, and enter the bin in the corresponding interior neckband, can cool off nozzle guide vane.In some nozzle sections, cooling medium flows through interior neckband then, and passes through these one or more nozzle guide vanes once more before discharging.In other nozzle section, cooling medium only flows through each nozzle section once.

Generally believe, also insufficient for the cooling in some zone of nozzle section, and higher thermal stress and fatigue are easily stood in this type of zone.Now just be devoted to improve the cooling in these zones.For example, U.S. Patent No. 7,029,228 have described a kind of structure, and wherein, cooling groove channel is roughly parallel to one of them that nozzle section fitting surface extends through outer shroud and interior shroud vertically, in order to the fitting surface between coolant seal notch and the hot gas path.

The debatable especially zone of cooling is the zone of extending and roughly be positioned at crosspiece (rail) the parts below on the neckband dorsal part in neckband from fitting surface in the nozzle section, and wherein, these crosspiece parts can comprise striking plate.Stator trailing edge on the opposite side of this zone and neckband overlaps.The neckband of cooling is made of more than one flow circuits usually, and wherein, the air of compressor drainage passes the striking plate in each loop, so that cool off the dorsal part of neckband before entering the gas passageway flowing out via fenestra or notch.These loops are separated by the crosspiece parts, and these crosspiece parts are positioned on the dorsal part opposite with the stator trailing edge of neckband usually.Usually, a series of hole drill is logical to pass this crosspiece, is passed to low tension loop to allow cooling air from high tension loop.Yet, exist crosspiece to stop impact and film cooling to center on the inner face of the neckband of stator trailing edge at the dorsal part place of neckband.In the art, need the insufficient cooling of solution for this zone.

Summary of the invention

The invention provides a solution in order to improve cooling to the nozzle section neckband of the cooperation side that is transverse to nozzle guide vane trailing edge place.Other aspects and advantages of the present invention will partly be set forth in the following description, or can become clear according to this explanation, maybe can understand by implementing the present invention.

According to aspects of the present invention, provide a kind of turbine nozzle section, it comprises outer neckband, interior neckband, and interior neckband and outside at least one nozzle guide vane of extending between the neckband.Nozzle guide vane has leading edge and trailing edge.In interior neckband and the outer neckband each includes fitting surface, the combustion gas side of extending (about the axis of turbine) vertically, and opposite dorsal part.First cooling chamber and second cooling chamber are limited to the dorsal part place of neckband, and In a particular embodiment, can be opened by the crosspiece parts space of horizontal expansion at least in part.In cooling plenum is limited in one of them the fitting surface of neckband and outer neckband, and the edge laterally extends through corresponding neckband at least in part.Cooling plenum is extensible, so that extend below the crosspiece parts basically in one embodiment, or extends below the nozzle guide vane trailing edge in another embodiment.At least one first cooling air channels is limited in the neckband and enters cooling plenum from first cooling chamber, and at least one second cooling air channels is defined as from second cooling chamber and enters cooling plenum.A plurality of these first cooling air channels and second cooling air channels can provide along the longitudinal length of cooling plenum.This passage is used for air is moved to another cooling chamber via cooling plenum from a cooling chamber.For example, first cooling chamber can be for the impacting with high pressure cooling chamber that compressor drainage air is arranged, and second cooling chamber can be low pressure chamber, cooling air moves to the cooling plenum from the hyperbaric chamber via first cooling air channels thus, and enters the low pressure chamber from cooling plenum via second cooling air channels.Introduce the zone that is positioned at bin below and next door and contiguous cooling air channels that therefore cooling air in the cooling plenum cools off neckband, for example, be positioned at the zone of crosspiece parts below or the trailing edge of nozzle guide vane.

Should be understood that the present invention also comprises the combustion gas turbine with a plurality of nozzle levels, wherein, each nozzle level also comprises a plurality of nozzle sections of implementing as in the text.

With reference to the following description and the appended claims, will be better understood these and other feature of the present invention, aspect and advantage.Be attached in this specification and constitute its a part of accompanying drawing and show embodiments of the invention, and be used from and set forth principle of the present invention together with describing one.

Description of drawings

With reference to accompanying drawing, in specification, illustrated the disclosure that the complete sum that the present invention includes its optimal mode can realize at those of ordinary skill of the present invention, in the accompanying drawings:

Fig. 1 is the perspective view in conjunction with the nozzle section of aspect of the present invention;

Fig. 2 is the fragmentary, perspective view of nozzle section part, has specifically illustrated the cooling plenum in the fitting surface;

Fig. 3 is the amplification fragmentary, perspective view of portion nozzle section, shows the alternative of the cooling plenum in the fitting surface;

Fig. 4 is the diagrammatic sketch of nozzle section neckband, show according to aspects of the present invention the nozzle guide vane trailing edge and the potential high-temperature area at the relevant position place of cooling plenum; And

Fig. 5 is the fragmentary, perspective view of alternative that combines the nozzle section 10 of cooling plenum; And

Fig. 6 is the perspective view of another alternative that combines the nozzle section 10 of cooling plenum.

List of parts

10 nozzle sections

12 outer neckbands

14 combustion gas sides

16 dorsal parts

18 cooperate the side

Neckband in 20

22 combustion gas sides

24 dorsal parts

26 cooperate the side

30 nozzle guide vanes

32 leading edges

34 trailing edges

36 cooling cavitys

38 first cooling chambers

40 second cooling chambers

42 crosspiece parts

44 striking plates

46 cooling plenums

48 passages

49 passages

50 sealing notches

52 Sealings

54 fenestras

56 roots

58 fillets (fillet)

Embodiment

Now will be at length with reference to embodiments of the invention, one or more example shown in the drawings.Each example all provides by way of example to elaboration of the present invention, and also unrestricted the present invention.In fact, what those skilled in the art will understand is, do not depart from the scope of the present invention or the situation of spirit under, can make various modifications and variations in the present invention.For example, the feature that is shown or is described as an embodiment's a part can be used in conjunction with another embodiment, in order to produce another embodiment.Therefore, expectation is that these modifications and the modification in the scope that is included into claims and equivalent thereof contained in the present invention.

Fig. 1 is the perspective pictorial view of the nozzle section 10 of exemplary embodiment.Nozzle section 10 comprises the outer neckband 12 with combustion gas side 14 and dorsal part 16.Nozzle section 10 comprises the interior neckband 20 with combustion gas side 22 and dorsal part 24.Outer neckband has the side surface 18 of cooperation, and this cooperation side surface 18 can comprise the Sealing 52 that is arranged in the sealing notch 50 (Fig. 2).Similarly be, interior neckband 20 comprises cooperation side 26, and this cooperation side 26 has the Sealing 52 along its setting.

Nozzle section 10 is included at least one nozzle guide vane 30 that extends between the combustion gas side of

neckband

12,20, and wherein, nozzle guide vane has leading edge 32 and trailing edge 34.Nozzle section 10 can comprise a plurality of stators 30 that are arranged in single section.Nozzle guide vane 30 intersects with the combustion gas side 22 of following neckband 20 at root 56 places.Fillet 58 with recessed radius of curvature roughly forms along root 56.Nozzle guide vane 30 forms in the same manner with the interface on the combustion gas side 14 of outer neckband.

A plurality of nozzle sections 10 center on turbine axis (not shown) along circumferential arrangement, and are fixed on the turbine shroud to form the nozzle level.Usually, turbine comprises a plurality of these nozzle levels.

The

combustion gas surface

14,22 that the flow passage of hot combustion gas reaches outer neckband 12 and interior neckband 20 by nozzle guide vane 30 respectively is defined as passes nozzle section 10.As in related domain, understand like that, hot gas flows through section and around stator 30, and engages the rotor wheel blade (not shown) in turbine downstream and make the turbine rotor rotation.

Matching

surface

18,26 comprises the Sealing 52 that is in sealing notch 50 (Fig. 2), and therefore is arranged in sealing engagement between the adjacent nozzle section 10 of nozzle level.Sealing 52 prevents that cooling air from leaking in the combustion gas flow path between the interface of outer neckband 12 and interior neckband 20.

Referring to Fig. 1, nozzle section 10 comprises first cooling chamber 38 and second cooling chamber 40.Usually, first cooling chamber 38 is configured in order to accommodate the high pressure cooling air, for example, and compressor drainage air.This high-pressure air can be via striking plate 44, bin or any other guide means guide in the second lower cooling chamber 40 of

pressure.Cooling chamber

40,38 comprises in order to seal the cover plate (not shown) of this chamber.Nozzle guide vane 30 has the structure of hollow substantially, and comprises the cooling cavity 36 that is communicated with low pressure cooling chamber 38.Therefore cooling cavity 36 can take it is cooling chamber as.Crosspiece parts 42 are arranged between the cooperation side surface 18 of outer neckband 12 and between the matching surface 26 of interior neckband 20.Crosspiece parts 42 on outer neckband and the interior neckband can have identical or different structure, and can be used for different purposes.Referring to outer neckband 12, as shown in fig. 1, crosspiece parts 42 can be in conjunction with striking plate 44, and can with first or high pressure cooling chamber 38 with second or low pressure cooling chamber 40 separate.Should be understood that the dorsal part 24 of neckband 20 in cooling chamber also is formed on.

Cooling circuit is limited by each cavity and the structure member of nozzle section 10.What should understand is that the present invention is not limited by any particular configuration of cooling circuit.In an illustrated embodiment, the cooling air of introducing in first cooling chamber 38 provides impact and/or convection current cooling to nozzle section 10 construction element in this zone.Cooling air is via in striking plate 44 introducings second or the low pressure cooling chamber 40 (or the cavity 36 that is communicated with cooling chamber 40 or other zone).The part cooling air can pass neckband 12 via fenestra 54 diffusions and enter in the combustion-gas flow.This limited amount cooling air provides the film cooling to the combustion gas side surface of corresponding neckband 12,20.As difference illustrates in the accompanying drawings, can adopt any array and location to these fenestras 54.

Nozzle guide vane 30 is hollow substantially, and comprises one or more cavitys 36.Cooling air moves in order to cooling jet stator 30 via cavity 36.Cavity 36 also can be via passing fluid bore 54 that stator 30 limits with the suction side of nozzle guide vane 30 with on the pressure side be communicated with.In this way, the outer surface of nozzle guide vane 30 is by the cooling air film cooling that causes from the teeth outwards.Cooling air moves through stator 30 and in entering in the cavity of neckband 20, and can pass fenestra 54 and spread in shroud 20.The structure that depends on nozzle section 10, cooling air can be before from cooling circuit, discharging via the other parts recirculation of nozzle section 10.

Referring to different diagrammatic sketch, the crosspiece parts 42 that extend between the cooperation side 18 of neckband 12 and between the cooperation side 26 of following neckband 20 have formed the problem area about cooling outside.The existence of crosspiece has suppressed to impact cooling, the especially cooling of the impact in nozzle guide vane 30 trailing edge zones.Fig. 4 shows the potential high-temperature area at the nozzle guide vane 30 trailing edge places that concentrate on the stator suction side or the diagrammatic sketch of " focus " (dashed region).The position of crosspiece parts 42 is by being shown in dotted line among Fig. 4.Referring to Fig. 2, Fig. 3 and Fig. 5, appreciable is that side 18 is roughly contiguous to cooperate nozzle guide vane 30 trailing edges 34 terminal points of side with respect to this along cooperating in the position of the crosspiece parts 42 in these specific embodiments.As seeing in Fig. 1, Fig. 4 and Fig. 5 that crosspiece parts 42 have separated the trailing edge by the nozzle guide vane that dotted line limited 30 of root shown in Fig. 5 56.In other words, crosspiece parts 42 extend or extend across the rear portion of nozzle guide vane 30, and this rear portion appends on the heating power focus shown in Fig. 4.

Referring to different diagrammatic sketch and according to aspects of the present invention, cooling plenum 46 is limited in wherein one of at least the

fitting surface

18,26 of outer neckband 12 or interior neckband 20 one.What should understand is, this cooling plenum 46 can be included in outer neckband 12 and interior neckband 20 among both, and is included in two fitting surfaces of each corresponding neckband.For the purpose of discussing, the cooperation side 18 of neckband 12 has been described cooling plenum 46 further in this paper reference.

Cooling plenum 46 is limited to and is positioned at any desired position in the fitting surface, so that along extending laterally in the neckband in order to cool off the location of neckband.In an illustrated embodiment, cooling plenum 46 is limited to the position of contiguous crosspiece parts 42.For example, referring to Fig. 2 and Fig. 3, cooling plenum 46 can take it is that crosspiece parts 42 with in the last neckband 12 are aimed at as, or extension at least in part below the crosspiece parts 42 in last neckband 12.Cooling plenum 46 edges laterally extend through corresponding neckband at least in part, and can extend fully through neckband, so that cooperate side surface 18 to extend to relative cooperation side surface 18 from one.Therefore cooling air enters in the cooling plenum 46 through guiding, and along the zone of the root or the base portion cooling neckband 12 of crosspiece parts 42.Therefore, when cooling air moved through cooling plenum 46, the zone around the neckband 12 of nozzle guide vane 30 trailing edges 34 was also cooled off by impact and/or convection current.Specifically shown in the diagrammatic sketch of Fig. 4, wherein, the position of cooling plenum 46 is shown by dashed lines for this.Appreciable from this figure is that cooling plenum also passes trailing edge 34 zones of nozzle guide vane 30, and therefore will be used to cool off the potential problems focus of the adjacent nozzles stator 30 suction side trailing edges shown in Fig. 4.

Cooling plenum 46 can provide the cooling air that passes each device.In an illustrated embodiment, a plurality of air passagewayss are used for cooling air moved or be transported to cooling plenum 46, move or carry along cooling plenum 46, and move or transfer out cooling plenum 46.For example, referring to Fig. 1, Fig. 4 and Fig. 5, at least one first cooling air channels 48 can be limited in the crosspiece parts 42 (or other structure of neckband 12), so that cooling air bin 46 is positioned to and 38 one-tenth fluid air communication of first cooling chamber.Therefore, compressor drainage air or other cooling air of introducing in the cooling chamber 38 moves in the cooling plenum 46.At least one second air passageways 49 is limited in the crosspiece parts, and settles position one-tenth to become the fluid air communication with second cooling chamber 40 (it comprises zone or the cavity that is communicated with chamber 40) cooling plenum 46.Therefore, cooling air can move through cooling plenum 46, and enters cooling chamber 40 via 49 outflows of second air passageways.In an illustrated embodiment, a plurality of

passages

48 and 49 limit along the length of cooling plenum 46 in the vertical.These passages of any amount or position all are possible.The location of depending on neckband to be cooled, cooling plenum 46 can be along laterally extending across neckband 12 fully, and

cooling channel

48 and 49 can be positioned at each lengthwise position place along cooling plenum 46 whole length.Although and failed call, first cooling channel 48 and second cooling channel 49 are capable of being combined in pairs, make each first cooling channel 48 include the second corresponding cooling air channels 49.The location of these passages can be staggered along the longitudinal length of bin 46.

What should understand is that bin 46 is not limited to any specific cross section profile or other structure.For example, in the embodiment shown in Fig. 2, bin 46 is the cross section profile of circular.In the embodiments of figure 3, cooling air bin 46 has the cross section profile of substantially elliptical.

Still referring to Fig. 2 and Fig. 3, in an illustrated embodiment, cooling plenum 46 is limited to corresponding neckband and cooperates in the side 18, is in substantially between the trailing edge 34 of crosspiece parts 42 on neckband 12 dorsal parts and the nozzle guide vane 30 on the neckband 12 combustion gas sides.If fitting surface surface 18 comprises the sealing notch 50 that extends vertically, just then cooling plenum 46 is limited between sealing notch 50 and the combustion gas side 14.

What should understand is, in the embodiment that the present invention also comprises, cooling air bin 46 is limited in the fitting surface surface 18 so that extend transversely in the neckband 12 of adjacent nozzles stator 30 trailing edges 34, no matter and the length of any crosspiece parts on neckband 12 dorsal parts 16 how.For example, the dorsal part 16 of neckband 12 can comprise having the structure member that suppresses to impact any design of cooling off the certain zone of neckband.In this case, cooling plenum 46 can be limited to and cooperate in the side surface 18, so as to extend to roughly with neckband 12 that this structure member overlaps in, particularly in the trailing edge zone of nozzle guide vane 30.The cooling air that moves through bin 46 will cool off around the zone of the neckband 12 of nozzle guide vane 30 trailing

edges.Cooling channel

48,49 can be limited in the neckband, become the fluid air communication with the second place so that cooling plenum 46 is positioned to primary importance, wherein, the cooling air bin also is used for air is moved to another position from a position, and the problem area to neckband 12 provides useful impact cooling simultaneously.This conception is shown in Figure 6 substantially, and wherein, cooling plenum 46 is limited in the fitting surface surface 26 of end neckband 20, so that roughly extend across the rear end part of nozzle guide vane 30 in neckband 20.Bin 46 can or can not extend below the crosspiece parts or extend along the crosspiece parts, and these crosspiece parts also stride across the dorsal part of neckband 20 along horizontal expansion.

In the embodiment show in figure 5, at least one cooling air channels 49 is positioned to 36 one-tenth fluid air communication of cavity with stator 30 with bin 46.This structure can be used for air is directly introduced the cavity 36 from bin 46, or air is directly removed to the bin 46 from cavity 36.

Although described this theme in detail with reference to concrete exemplary embodiment and method thereof, what those skilled in the art will understand is, preamble being obtained when understanding, can easily produce improvement, modification and equivalent arrangements to these embodiments.Therefore, the scope of present disclosure is by way of example, but not by the restriction, and as those of ordinary skill in the art will understand easily, described disclosure is not got rid of these modifications, modification and/or the interpolation that comprises this theme.

Claims

1. a turbine nozzle section (10) comprising:

Outer neckband (12), interior neckband (20), and in described neckband and described outside at least one nozzle guide vane (30) of extending between the neckband, described nozzle guide vane has leading edge (32) and trailing edge (34);

In described in neckband and the described outer neckband each all also comprises the fitting surface (18) that extends vertically, and combustion gas side (14) and opposite dorsal part (16);

Be limited to first cooling chamber (38) and second cooling chamber (40) at the described dorsal part place of described interior neckband and described outer neckband;

Be limited to described in wherein one of at least the wherein cooling plenum (46) in one of at least of described fitting surface of neckband or described outer neckband, described cooling plenum edge laterally extends through corresponding neckband at least in part; And

Be defined as in described neckband from described first cooling chamber and enter at least one first cooling air channels (48) in the described cooling plenum, and be defined as in described neckband from described second cooling chamber and enter at least one second cooling air channels (49) in the described cooling plenum.

2. turbine nozzle section according to claim 1 (10), it is characterized in that, described first cooling chamber (38) is the hyperbaric chamber, and described second cooling chamber (40) is a low pressure chamber, described first cooling chamber and described second cooling chamber are separated by the crosspiece parts (42) along horizontal expansion at least in part, described cooling plenum (46) edge below described crosspiece parts laterally extends through corresponding neckband at least in part, and thus, cooling air moves to the described cooling plenum from described hyperbaric chamber via described first cooling air channels (48), and enters the described low pressure chamber via described second cooling air channels (49) from described cooling plenum.

3. turbine nozzle section according to claim 2 (10), it is characterized in that, described first cooling air channels (48) and described second cooling air channels (49) are setovered in the axial direction along described cooling plenum (46), and described cooling plenum is limited in corresponding neckband between the described trailing edge (34) of described crosspiece parts (42) and described nozzle guide vane (30).

4. according to claim 1 any one described turbine nozzle section (10) to the claim 3, it is characterized in that, described fitting surface (18) also comprises the sealing notch (50) that limits in the axial direction along described fitting surface, described cooling plenum (46) is limited between the described combustion gas side (22) of described sealing notch and corresponding neckband (12,20).

5. according to claim 1 any one described turbine nozzle assembly (10) to the claim 3, it is characterized in that, described first cooling chamber (38) is for supplying to have the impacting with high pressure cooling chamber of compressor drainage air, and described cooling plenum (46) extends fully through corresponding neckband (12,20) and is between the relative fitting surface in the described fitting surface (18).

6. according to claim 1 any one described turbine nozzle section (10) to the claim 3, it is characterized in that described cooling plenum (46) extends through corresponding neckband (12,20) at least in part along laterally striding across described trailing edge (34).

7. according to claim 1 any one described turbine nozzle section (10) to the claim 3, it is characterized in that, described cooling plenum (46) extends fully through corresponding neckband (12,20) and is between the relative fitting surface in the described fitting surface (18).

8. combustion gas turbine that comprises a plurality of nozzle levels, each described nozzle level also comprises a plurality of nozzle sections (10), each nozzle section is respectively according to claim 1 any one described nozzle section to the claim 3.