CN102146811A

CN102146811A - Heat shield

Info

Publication number: CN102146811A
Application number: CN2011100377945A
Authority: CN
Inventors: G·M·伊策尔; V·J·摩根
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2010-02-04
Filing date: 2011-01-31
Publication date: 2011-08-10
Also published as: JP2011163344A; CH702678A2; DE102011000299A1; US20110110790A1

Abstract

A heat shield 100 is disclosed. The heat shield 100 may include a base layer 102 and a spacer layer 101. The spacer layer 101 may be coupled to the base layer 102. The spacer layer 101 may define a plurality of flow channels 49. The base layer 102 and the spacer layer 101 may be configured to associate with a hot gas path component 34.

Description

Thermal shield

Related application

The application is the part continuity application of the u.s. patent application serial number 12/615,674 of submission on November 10th, 2009.

Technical field

Theme disclosed herein relates to the hot gas passage member such as the aerofoil profile part, and relates more particularly to be used for the thermal shield (heat shield) of hot gas passage member.

Background technique

Aerofoil profile part (being stator and blade) is an embodiment who typically is arranged on the hot gas passage member in the hot gas path of combustion gas turbine.The blade that also can be described as " wheel blade " or " rotor " can comprise and is installed in impeller, disk or epitrochanterian aerofoil profile part, so that around the axle rotation.The stator that can be called as " nozzle " or " stator " can comprise the aerofoil profile part that is installed in the shell, and shell encirclement or cover blade shroud are around the axle of its rotation.Typically, a series of blade shrouds are installed in specific location along this around impeller.A series of stators can be installed in the upstream (with respect to the overall flow direction) of this Series Blade, for example are used to improve the efficient of air-flow.The level that is called combustion gas turbine with vaned stator.Level pressurized gas in the compressor, this gas for example will and be lighted with fuel mix, and will be transported to the inlet of combustion gas turbine.Combustion gas turbine can comprise a plurality of levels so that extract merit from gas and the fuel of lighting.Gas interpolation fuel to compression can comprise combustion reaction contribution energy.The product of this combustion reaction flows through combustion gas turbine subsequently.In order to tolerate the high temperature that burning produces, need other hot gas passage member in cooling aerofoil profile part and the turbo machine.Inadequate cooling causes unsuitable stress on aerofoil profile part and the hot gas passage member, and as time passes, this stress causes or impel the tired and inefficacy of aerofoil profile part.In order to prevent the fatigue of the turbine blade in the gas turbine engine that operating temperature causes, the film cooling is attached in the hot gas passage member, for example be attached in the aerofoil profile part Blade Design.For example, in the film cooling of aerofoil profile part blade, cooling air is released from compressor stage, by the inner cavity chamber of line transportation to turbine blade, and by the discharging of the aperture in the blade wall.This air provides thin, cold, heat insulation coating along the outer surface of turbine blade.But energy efficiency is low because it can form uneven cooling in the film cooling, because in the position near the hole, film temperature is than much lower at a distance apart from the hole.Therefore, need improve the cooling of hot gas passage member.

Summary of the invention

Many aspects of the present invention and advantage will partly be discussed in the following description, maybe can become apparent from explanation, maybe can learn by implementing the present invention.

According to an aspect of the present invention, a kind of thermal shield has been described.This thermal shield can comprise base layer and wall.Wall can be connected on the base layer.Wall can limit a plurality of runners.Base layer and wall can be configured to be associated with the hot gas passage member.

With reference to following explanation and claims, these and other feature of the present invention, aspect and advantage will become better understood.In conjunction with in this manual and the accompanying drawing that constitutes the part of this specification illustrate embodiments of the invention, and be used from together with explanation one and explain principle of the present invention.

Description of drawings

It is highlighted and clearly claimed in the appended claim of this specification to be regarded as theme of the present invention.By the detailed description of making below in conjunction with accompanying drawing, of the present invention aforementioned and other feature and advantage are apparent, in the accompanying drawing:

Fig. 1 illustrates the wherein gas turbine system 10 of exemplifying embodiment thermal shield.

Fig. 2 illustrates turbo machine as illustrated in Figure 1.

Fig. 3 illustrates the side perspective view of exemplary thermal shield.

Fig. 4 illustrates the aerofoil profile part of the Fig. 2 that comprises exemplary thermal shield.

Fig. 5 illustrates the top sectional view with exemplary thermal shield.

Fig. 6 illustrates near the top sectional view of the aerofoil profile part of the exemplary thermal shield that has the aerofoil profile part.

Fig. 7 illustrates the sectional view of exemplary thermal shield.

Fig. 8 illustrates an embodiment of the wall of the thermal shield that is shown separately.

Fig. 9 illustrates an exemplary embodiment of the thermal shield with dovetail joint attachment arrangement.

The component tabulation

10 gas turbine systems

12 engine centerlines

16 compressors

18 burning blocks

20 turbines

26 rotor shafts

28 hot air flows

30 turbine guide vanes

32 turbine blades

34 hot gas passage member, the aerofoil profile part

36 outer walls

38 shells

41 impact openings

42 gaps

43 recessed surfaces

44 trailing edge cooling channels

48 apertures

49 runners

100 thermal shields

101 walls

102 base layeres

103 outer (heat) layer

104 bonding layers

105 casing walls

106 otch

107 spacer segment

108 first series

109 second series

110 walls

111 leading edges

112 trailing edges

113 dovetail joints

115 top plug

116 tips

117 thermal shield dovetail joints

121 first surfaces

122 second surfaces

Embodiment

Now will be in detail with reference to embodiments of the invention, its one or more examples shown in the drawings.Each example is not a limitation of the present invention as explanation of the present invention is provided.In fact, will be apparent that those skilled in the art, do not depart from the scope of the present invention or the prerequisite of spirit under, can make various remodeling and modification in the present invention.For example, can use to produce another again embodiment with another embodiment as an embodiment's part diagram or the feature of describing.Therefore, the present invention is intended to contain this type of remodeling and the modification in the scope that falls into claims and equivalent thereof.

Fig. 1 illustrates the wherein gas turbine system 10 of exemplifying embodiment thermal shield.About combustion gas turbine the exemplary thermal shield described in the literary composition is illustrated.In other exemplary embodiment, the thermal shield described in the literary composition can be that other desired system implements with the protection of thermal shield wherein, such as, but not limited to steam turbine and compressor.Gas turbine system 10 is illustrated as and circumferentially is arranged on around the engine centerline 12.Gas turbine system 10 can comprise compressor 16, burning block 18 and the turbine 20 of bunchiness flow relation.Burning block 18 and turbine 20 often are called as the hot-zone section of gas turbine system 10.Rotor shaft 26 operationally is connected to turbine 20 on the compressor 16.Fuel burns in burning block 18 and produces hot air flow 28, and this hot air flow for example can be about 3000 to the scope of about 3500 Fahrenheits.Hot air flow 28 is directed through turbine 20 to drive gas turbine system 10.

Fig. 2 illustrates the turbine 20 of Fig. 1.Turbine 20 can comprise turbine guide vane 30 and turbine blade 32.Aerofoil profile part 34 can be implemented at stator 30.Aerofoil profile part 34 can be set in the part of the part of a part, burning block 18 of compressor 16 or turbine 20.Stator 30 has the outer wall 36 that is exposed to hot air flow 28.Turbine guide vane 30 can be by the air cooling of passing shell 38 transmission of system 10 from one or more levels of compressor 16.In addition, the outer wall 36 of aerofoil profile part 34 can be equipped with as present described exemplary throw-away-type thermal shield.

Fig. 3 illustrates the side perspective view of exemplary thermal shield 100.Thermal shield 100 can be configured to be associated with hot gas passage member 34, for example is associated with aerofoil profile part 34.For example, aerofoil profile part 34 or any gas passageway member 34 can be at least partially disposed in the hot gas path, for example in the path of hot air flow 28.Thermal shield 100 can be set between hot gas passage member 34 and the hot gas path.In the exemplary embodiment, thermal shield 100 can be the single integral piece that is configured to be fixed on the aforesaid aerofoil profile part 34.As further discussing in the literary composition,, can be the multilayer design though thermal shield is single integral piece.In other exemplary embodiment, each layer of thermal shield 100 can be separation member, and separation member can be configured to be fixed on the aforesaid aerofoil profile part 34.It should be understood that thermal shield 100 is not limited to the application on the aerofoil profile part, but also can be fixed on any part of the gas turbine system 10 that needs the heat protection, for example be fixed on other hot gas passage member 34.What comprised in the literary composition just illustrates the various embodiments of present disclosure to aerofoil profile part and thermal shield and the related any discussion between the aerofoil profile part.In the exemplary embodiment, thermal shield 100 is configured to gas turbine system 10 minimum down times are fixed and remove, and this is because thermal shield 100 is modularization parts of aerofoil profile part 34, and can as described hereinly be removed.In the exemplary embodiment, thermal shield 100 can frictionally be fixed on the aerofoil profile part 34.Thereby thermal shield 100 comprises several friction members.In the exemplary embodiment, thermal shield 100 comprises the casing wall 105 (being upper wall and lower wall) of the shell 38 that is configured to mechanically to engage gas turbine system 10.Shell 38 can comprise different shape and curvature.Thereby according to the shape of shell 38, casing wall 105 can comprise corresponding shape and curvature.Thermal shield 100 also can comprise the wall 110 that is arranged between the casing wall 105.Wall 110 can be perpendicular to casing wall 105 orientations.In addition, casing wall 105 comprises the otch 106 with the curvature of mating with the curvature of aerofoil profile part 34.Otch 106 also mates with the curvature of wall 110.Wall 110 can be configured to be associated with aerofoil profile part 34.For example, the curvature of wall 100 can be mated the curvature of aerofoil profile part 34.In one embodiment, wall 110 can be the multilayer design, and each layer can be configured to be associated with aerofoil profile part 34.In the exemplary embodiment, wall 110 also comprises leading edge 111 and trailing edge 112.Leading edge 111 is the outer lug parts that receive the wall 110 of hot air flow 28 at first with the different angles of attack.Those skilled in the art understands the leading edge that leading edge 111 covers aerofoil profile part 34.

Fig. 4 illustrates the aerofoil profile part 34 of the Fig. 2 that comprises exemplary thermal shield 100.As described herein, thermal shield 100 via between shell 38 and the casing wall 105 and the frictional force between aerofoil profile part 34 and the wall 110 be mechanically secured on the aerofoil profile part 34.In other exemplary embodiment, can implement thermal shield 100 to be fixed on the aerofoil profile part 34 such as, but not limited to the machanical fastener of bolt.In the exemplary embodiment, top plug 115 also can be fixed on the part of shell 38.Top plug 115 can comprise near the series of prongs (prong) 116 that is arranged on the aerofoil profile part 34.Thermal shield 100 can be fixed on tip 116 tops in the time of on being fixed on aerofoil profile part 34, thereby increases the frictional force between thermal shield 100 and the aerofoil profile part 34.In the exemplary embodiment, can comprise several other friction surface and devices on aerofoil profile part 34 and the thermal shield 100, to assist the fixing of thermal shield 100 and to remove.For example, the dovetail joint of a series of cooperations can be arranged on aerofoil profile part 34 and the thermal shield 100.

As described herein, thermal shield 100 can be burning on-the-spot replacing of interim.For example, thermal shield 100 can be connected on the hot gas passage member 34 separably, for example is connected on the aerofoil profile part 34.(slip-on) thermal shield 100 that slides covers the leading edge of the madial wall of aerofoil profile parts 34 and outer side wall and major part on the pressure side and cover high apsis (camber point) to the suction side.The combination of the pin on the high apsis of tip 116 of trailing edge on the pressure side and suction side that the recess on available and the nozzle has a common boundary comes fixing thermal shield 100.Though can implement just fastening (positivedetainment) device of any kind, become serial crooked dovetail joint can cover the madial wall and/or the outer side wall of aerofoil profile part 34.Aerofoil profile part 34 can mate with a series of dovetail joints that cooperate on the thermal shield 100 then.Dovetail joint can be crooked to allow the sliding properties of replaceable heat-insulating cover 100 on the direction of nozzle.In addition, can bolt be set in the transition piece Sealing on the leading edge of aerofoil profile part 34 (itself and burning block 18 have a common boundary) top.Therefore, thermal shield 100 can be when the transition piece of burning block 18 and liner are removed be just in time changed in burning interim.

Fig. 5 illustrates the top cross-sectional view of the aerofoil profile part 34 with exemplary thermal shield 100.Fig. 6 illustrates the top cross-sectional view of the aerofoil profile part 34 with near the exemplary thermal shield 100 aerofoil profile part 34.Fig. 5 and Fig. 6 illustrate the thermal shield 100 with the curvature of mating with the curvature of aerofoil profile part 34.As illustrated, aerofoil profile part 34 can comprise a plurality of impact openings 41.Impact opening 41 can be configured to provide cooling air to thermal shield 100.As described herein, impact opening 41 also can be implemented at conventional film cooling.Aerofoil profile part 34 also can comprise the gap 42 that is formed between aerofoil profile part 34 and the thermal shield 100.Gap 42 can receive the cooling air that is used for the film cooling.As further describing in the literary composition, thermal shield 100 comprises wall 101, cooling air this wall of can flowing through.Aerofoil profile part 34 also can comprise recessed surface 43.Recessed surface 43 makes it possible to thermal shield 100 is fixed on the aerofoil profile part 34.Aerofoil profile part 34 also can comprise the trailing edge cooling channel 44 that receives cooling air.As further describing in the literary composition, the wall 101 of thermal shield 100 limits runner 49.In one embodiment, runner 49 can provide cooling air to gap 42 and trailing edge cooling channel 44.

In the exemplary embodiment, thermal shield 100 comprises multilayer.For example, thermal shield 100 can comprise wall 101.Wall 101 can limit a plurality of runners 49.In one embodiment, a plurality of runners 49 can be communicated with each other in fluid.In one embodiment, wall 101 can be undulating horizon 101.Runner 49 receives cooling air from impact opening 41, and can provide cooling air to trailing edge cooling channel 44 and gap 42.Thermal shield 100 also can comprise outer (heat) layer 103.(heat) layer 103 is the materials that hot air flow 28 had heat resistent property outward.For example, outer (heat) layer 103 can be heat insulating ceramic coat or thermal barrier coating (" TBC "), and it can be injected or be fixed on the bonding layer 104, as further describing in the literary composition.Departing from and increase rigidity for thermal shield 100 between wall 101 maintaining heat gas passageway members 34 and the thermal shield 100, and limit a plurality of runners 49, as described herein.

Fig. 7 illustrates the sectional view of exemplary thermal shield 100.Fig. 7 illustrates the aerofoil profile part 34 with 100 one-tenth Mechanical Contact of thermal shield, and this aerofoil profile part 34 can comprise the base layer 102 that is connected to rigidly on the wall 101.Base layer 102 can comprise first surface 121 and second surface 122.Wall 101 can be positioned near the first surface 121.Wall 101 can be configured to allow cooling air to flow between aerofoil profile part 34 and base layer 102.In the exemplary embodiment, base layer 102 can be the high temperature superalloy that structural strength is provided to thermal shield 100, and air mechanics contour both was provided, level and smooth, the non-wavy surface of outer (heat) layer 103 that also is provided for applying.Fig. 7 also illustrates outer (heat) layer 103, and it can be positioned near the second surface 122 of base layer 102.Bonding layer 104 can be positioned between the second surface 122 and outer (heat) layer 103 of base layer 102.Bonding layer 104 can be configured to outer (heat) layer 103 is bonded on the base layer 102.For example, bonding layer 104 can be can be with outer (heat) layer 103 any material that is bonded on the bonding layer 104, for example, and aluminide for example.

Fig. 8 illustrates the wall 101 of thermal shield 100, and this wall is shown separately with diagram runner 49.For illustrated purpose, base layer 102, bonding layer 104 and heat (outward) layer 103 are not shown.In the exemplary embodiment, wall 101 comprises spacer segment 107.Spacer segment 107 limits a plurality of runners 49.Spacer segment 107 can have various styles.For example, in one embodiment, wall 101 can be undulating horizon 101, and spacer segment 107 can be the waveform section 107 that is provided with the waveform style.Yet, it should be understood that wall 101 and spacer segment 107 are not limited to undulating horizon 101 and waveform section 107, but can be any layer 101 and the section 107 that limits a plurality of runners 49.It will also be appreciated that wall can use any formation technology as known in the art to form, and includes but not limited to punching press, punching, roll forming machine or embossing.

It will also be appreciated that spacer segment 107 can be spaced with various width on wall 101.For example, if the high structural stress zone of exist confirming on the thermal shield 100, then the style of spacer segment 107 can be closeer or every nearer, and determine than low stress zones in the density of spacer segment 107 can be lower, or every De Gengkai.In addition, the spacing of the less dense of spacer segment 107 and the increase cooling that thermal shield 100 is provided and therefore improved in the aerofoil profile part 34.In the exemplary embodiment, impact opening 41 is aligned to and roughly is orthogonal to spacer segment 107.Illustrate first series 108 and the second series 109 of spacer segment 107.As mentioned above, first series 108 of spacer segment 107 can provide air-flow to gap 42, and the second series 109 of spacer segment 107 can provide air-flow to trailing edge cooling channel 44.As shown in Figure 8, first series 108 can be aligned to and roughly be orthogonal to second series 109.In other exemplary embodiment, various other configurations of spacer segment 107 have been imagined.

Each spacer segment 107 can limit a plurality of apertures 48.Aperture 48 can be configured to allow cooling air to enter wall 101 and flow between a plurality of runners 49.For example, various apertures 48 can allow cooling air to enter wall 101 from impact opening 41.Other aperture 48 can allow the cooling air in the wall 101 also to pass through between the runner 49 through aperture 48.This can allow in wall 101, forms one deck cooling air between hot gas passage member 34 and base layer 102, thereby the more effective cooling of hot gas passage member 34 is provided, as described below.

Fig. 9 illustrates an exemplary embodiment of the thermal shield 100 with dovetail joint attachment arrangement.For illustrated purpose, only illustrate the wall 101 and the base layer 102 of thermal shield 100.As described herein, though can implement the positive fastening device of any kind, dovetail joint 113 can cover the madial wall and/or the outer side wall of aerofoil profile part 34.The dovetail joint 113 of aerofoil profile part 34 can mate with the thermal shield dovetail joint 117 that cooperates on the thermal shield 100.In the exemplary embodiment, thermal shield dovetail joint 117 can be arranged on the base layer 102 near the spacer segment on the wall 101 107.In other exemplary embodiment, thermal shield dovetail joint 117 can be arranged on the wall 101.

Technique effect comprises the quick spot repair of the hot gas passage member 34 of implementing the thermal shield 100 described in the literary composition.For example, thermal shield 100 can be connected on the hot gas passage member 34 separably.Thermal shield 100 can be configured to hot gas passage member 34 is shielded from the hot gas path such as hot air flow 28, thereby allows the unstressed relatively and strainless operation of hot gas passage member 34, and is as described below.When the stress and strain that for example owing to the big temperature gradient in the hot gas path thermal shield 100 is caused when thermal shield 100 needs place under repair, thermal shield 100 is separated and place under repair or replacing with hot gas passage member 34, and not need hot gas passage member 34 needed for repair and replacement.This type of spot repair can be carried out in the interim of burning.In the first order nozzle that wherein can exemplifying embodiment thermal shield 100 be exemplified as combustion gas turbine, it often is called as S1N.The first order nozzle of combustion gas turbine makes hot air flow 28 converge and quicken after burning block 18, and is the result that first order nozzle is gradually-reducing shape.As mentioned above, thermal shield 100 can cover the first order nozzle aerofoil profile part 34 that the major part of leading edge and aerofoil profile part 34 on the pressure side goes up, and thermal shield 100 can reach the high apsis on the suction side of aerofoil profile part 34.Allowing first order nozzle in conjunction with the described thermal shield 100 of first order nozzle in the literary composition is modularization/removable system, rather than the one-piece design as in the conventional system.Therefore maintenance cost is lowered and prolong the working life of nozzle; When thermal shield 100 begins to wear and tear, can remove and change thermal shield 100.

The multilayer design of thermal shield 100 can significantly reduce the bulk metal part temperature of hot gas passage member 34.As mentioned above, thermal shield 100 comprises outer (heat) layer 103.(heat) layer 103 can be fixed on base layer 102 and the wall 101 by bonding layer 104 outward.Wall 101 can provide air-flow and structure to thermal shield 100.The cooling air in the wall 101 is held back in the multilayer design of thermal shield 100 between base layer 102 and hot gas passage member 34, thus cooling hot gas passage member 34.This cooling means is more much effective than film cooling because cooling air be trapped within two-layer between, rather than mixes with hot air flow 28, this mixes along with the film cooling air moves and the reduction cooling effectiveness downstream from hole exits.Therefore, need less cooling air to come cooling hot gas passage member 34.The minimizing of cooling air can be used to reduce the combustion temperature for identical output power, forms and improve the gas turbine engine efficiency thereby reduce NOx.

The multilayer design of thermal shield 100 can allow the unstressed relatively and no strain operation of hot gas passage member 34.For example, thermal shield 100 can be connected on the hot gas passage member 34 separably.In addition, thermal shield 100 can move with respect to hot gas passage member 34.Therefore, thermal shield 100 may be exposed under the high temperature of the hot air flow 28 of overheated gas path, and may expand with the temperature variation of hot air flow 28 and shrink.Thermal shield 100 can be operated the high temperature that avoids in the hot gas path with protection hot gas passage member 34, thereby reduces stress and strain in the hot gas passage member 34 by the temperature gradient that restriction hot gas passage member 34 is experienced.This can allow the unstressed relatively and no strain of hot gas passage member 34 ground operation.

Though described the present invention in detail in conjunction with the embodiment of limited quantity only, should be understood that the disclosed embodiment of class that the present invention is not limited thereto easily.On the contrary, any amount of modification, remodeling, replacement or the equality unit that can make amendment and match the present invention with in conjunction with not describing so far but with the spirit and scope of the present invention.In addition, though described various embodiment of the present invention, should be understood that All aspects of of the present invention can only comprise a part of described embodiment.Therefore, the present invention should not be regarded as limiting by the description of front, and only the scope by claims limits.

Claims

1. a thermal shield (100) comprising:

Base layer (102); And

Wall (101), described wall (101) are connected to described base layer (102) and go up and limit a plurality of runners (49),

Wherein, described base layer (102) and described wall (101) are configured to be associated with hot gas passage member (34).

2. thermal shield according to claim 1 (100) is characterized in that, described a plurality of runners (49) are communicated with each other in fluid.

3. according to each described thermal shield (100) of claim 1-2, it is characterized in that, described base layer (102) comprises first surface (121) and second surface (122), wherein said wall (101) is positioned near the described first surface (121), and comprise be positioned near the thermosphere (103) the described second surface (122) and be positioned at described thermosphere (103) and described second surface (122) between bonding layer (104), described bonding layer (104) is configured to described thermosphere (103) is adhered on the described base layer (102).

4. according to each described thermal shield (100) of claim 1-3, it is characterized in that described wall (101) comprises a plurality of spacer segment (107) that limit described a plurality of runners (49).

5. thermal shield according to claim 4 (100), it is characterized in that, each of described a plurality of spacer segment (107) all limits a plurality of apertures (48), and described a plurality of apertures (48) are configured to allow cooling air to enter described wall (101) and flow between described a plurality of runners (49).

6. according to each described thermal shield (100) of claim 1-5, it is characterized in that described wall (101) is configured to allow cooling air to flow between described hot gas passage member (34) and described base layer (102).

7. according to each described thermal shield (100) of claim 1-6, it is characterized in that described base layer (102) and described wall (101) are single integral piece.

8. according to each described thermal shield (100) of claim 1-7, it is characterized in that the curvature of described base layer (102) and described wall (101) and the curvature of described hot gas passage member (34) coupling.

9. according to each described thermal shield (100) of claim 1-8, it is characterized in that described hot gas passage member (34) limits a plurality of impact openings (41), described impact opening (41) is configured to provide cooling air to described thermal shield (100).

10. according to each described thermal shield (100) of claim 1-9, it is characterized in that described thermal shield (100) can move with respect to described hot gas passage member (34).