CN209637884U - Hot gas conducts shell and gas-turbine plant - Google Patents
Hot gas conducts shell and gas-turbine plant Download PDFInfo
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- CN209637884U CN209637884U CN201690000776.6U CN201690000776U CN209637884U CN 209637884 U CN209637884 U CN 209637884U CN 201690000776 U CN201690000776 U CN 201690000776U CN 209637884 U CN209637884 U CN 209637884U
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- shell
- wall
- hot gas
- slit
- gas
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03342—Arrangement of silo-type combustion chambers
Abstract
The utility model relates to a kind of hot gas to conduct shell (7), hot gas conduit (8) including annular cross section, wherein hot gas conduit (8) is inwardly defined by being provided with the shell outer wall (10) of at least one heater gas inlet port opening (11) by inner wall of tube shell (9) and outward, hot gas conduit (8) is in one end by having an annular hot gas outlet opening (13) by inner wall of tube shell (9) and shell outer wall (10) shell end wall (12) closing interconnected and in its other end, one of annular attachment web (14；43) it is protruded inwardly from radially from inner wall of tube shell (9), wherein attachment web (14；43) multiple slits (15 are provided with around it；30；34；39；44), slit passes through attachment web (14 in the axial direction；43) it and all has from attachment web (14；43) free end starts to extend outwardly at least first slot portion (16；31；35；40).The utility model is further to a kind of gas-turbine plant (1) with this hot gas conduction shell (7).
Description
Technical field
The utility model relates to a kind of hot gas to conduct shell, the hot gas conduit including annular cross section, wherein hot gas
Body pipeline is defined by shell outer wall in inside by inner wall of tube shell and in outside, and hot gas conduit is in one end by shell end wall
It closes and there is the hot gas outlet opening of annular in its other end, wherein shell outer wall is provided at least one hot gas
Inner wall of tube shell and shell outer wall are connected to each other by entrance opening, shell end wall, annular attachment web from inner wall of tube shell radially
It is inwardly projecting.In addition, gas turbine housing is included the utility model relates to a kind of gas-turbine plant, in gas turbine shell
Compressor and turbine are received in body；Axis passes through gas turbine housing, and compressor and turbine is connected to each other；And at least
One combustion chamber is disposed at least one combustion chamber outside gas turbine housing, at least one combustion chamber is via arrangement
The hot gas of type as described above inside gas turbine housing conducts shell and is fluidly connected to gas turbine housing,
In the axis by hot gas conduction shell inner wall of tube shell surround, and hollow tube-shape axis protection shell be disposed in inner wall of tube shell
Between axis, which includes outwardly projecting annular shoulder, which is equipped with a circumferential groove, in the circle
The attachment web of hot gas conduction shell is received in circumferential groove, the annular shoulder and hot gas conduct the inner wall of tube shell of shell in radial direction
It is spaced apart on direction with predetermined amount.
Background technique
According to the prior art, it is known that the gas-turbine plant of the hot gas conduction shell with types described above.These
Gas-turbine plant generally includes gas turbine housing, compressor and turbine is received in gas turbine housing, wherein compressor
It is connected to each other with turbine by axis.In addition, multiple combustion chambers are set, these combustion chambers for example in the form of silo combustion chamber and
The two sides of gas turbine housing are disposed in, and conducts shell via hot gas and connects with the internal flow of gas turbine housing
It connects, hot gas conduction shell is inserted in gas turbine housing.Hot gas conduction shell includes the hot gas of annular cross section
Pipeline, hot gas conduit are defined by shell outer wall in inside by inner wall of tube shell and in outside, and shell outer wall is provided with several
The quantity of heater gas inlet port opening, these heater gas inlet ports opening generally corresponds to the quantity of combustion chamber.Hot gas conduit is at it
The closing of shell end wall that inner wall of tube shell is connected by one end with shell outer wall and hot gas conduit include ring in its other end
The hot gas outlet of shape is open, and wherein hot gas conduction shell is disposed in inside gas turbine housing, so that shell end wall court
It is directed toward to compressor and hot gas outlet opening is directed toward towards turbine.In order to which hot gas conduction shell is fixed on whirlpool
The inside of shell is taken turns, annular attachment web protrudes inwardly from radially from the inner walls of turbine shroud, which exists
It is engaged in the circumferential groove of the annular shoulder of hollow tube-shape axis protection shell, which is disposed in hot gas conducting tube
Between the inner wall of tube shell and axis of shell, which is surrounded by the inner wall of tube shell of hot gas conduction shell.
When gas-turbine plant operation, fuel-air mixture is burned in a combustion chamber, then, pressurized heat
Combustion product gases conduct shell via hot gas from combustion chamber and are introduced into gas-turbine plant, and are conducted to turbine, In
In the turbine, combustion product gases cause axis to start turning.During this process, the thermal energy from combustion product gases is converted into machinery
Energy.Combustion air needed for compressor supply is burnt.In addition, a part for leaving in the compressed air of compressor be often used as it is cold
But fluid, the thermal stress component for cooling gas turbine equipment.Particularly, a kind of such thermal stress component is hot gas conduction
The inner wall of tube shell of shell.Since the surrounding air of compression is conducted through cooling pipe, and the cooling pipe is limited at axis guarantor
Between pillar shell and the inner wall of tube shell of hot gas conduction shell, so the inner wall of tube shell cools off.
It is in the problem of the cooling period of the inner wall of tube shell of hot gas conduction shell, in inner wall of tube shell and attachment abdomen
In transitional region between plate, due to accounting for leading thermal stress effect in inner wall of tube shell, so frequently forming crackle, this is usually led
A large amount of and expensive maintenance and repair are caused to work.Since attachment web is arranged close to previously described cooling, and in shell
The inside of wall is exposed to the excessive temperature of combustion product gases, so the temperature difference between attachment web and the inside of inner wall of tube shell is very
Greatly, thermal stress is consequently led to.
The known optinal plan for reducing crackle formation is, reduces the cooling of attachment web, and in this way
Reduce the temperature difference.In this context, it has been suggested that for guidance cooling air by following cold air openings, the cooling is empty
Attachment web of the gas opening in the annular shoulder of axis protection shell is inwardly arranged radially.However, this mode it is meant that
Entire transitional region between inner wall of tube shell and attachment web becomes very hot since shortage is fully cooled, transitional region
Service life only slightly improve.
The scheme that another kind proposes is that through-hole of the setting for the flowing of cooling air, makes in attachment web itself
Cooling air is obtained to be directly conducted by being attached web.By this method, incipient crack load alternative behavior is significantly improved.So
And a disadvantage of this through-hole being attached in web is: cooling air consumption increases and can be changed.In addition, the solution
And the abrasion increase for being attached web is relevant, because it significantly reduces the contact surface on attachment web.
Utility model content
Based on this prior art, the purpose of the utility model is to provide construct type described by introductory song in an alternate manner
Hot gas conducts shell and gas-turbine plant.
In order to realize the purpose, the utility model proposes a kind of hot gas of type described by introductory song to conduct shell, special
Sign is that attachment web is provided with multiple slits around it, these slits pass through attachment web in the axial direction, wherein often
One slit all has at least first slot portion that extends outwardly since the free end of attachment web.It is practical new according to this
Type, this slit cut preferably by means of water jet and are formed, and this slit serves as relief notches and compensates in inner wall of tube shell
And the thermogenetic stress in the transitional region being attached between web.Experiment shows that incipient crack load cycle quantity can be by
In this slit arrangement and improve several times.If slit is provided with extremely narrow slot width, can also effectively avoid it is additional can
Turn cold but air consumption, and reduces the wear surface on attachment web.
One embodiment according to the present utility model, slit arranged each other with fixed range in the circumferential, especially with
The pitch of (preferably 5 °) in the range of 4 ° to 10 ° and be arranged.Fabulous unloading effect is realized using this pitch.
Preferably, the first slot portion at least partly (preferably all) extends radially.
The width of first slot portion is preferably in 0.05mm and in the range of 1.5mm, the especially model in 0.1mm to 0.5mm
In enclosing.
One embodiment according to the present utility model, at least some of slit slit (especially all slits) have with
The second slot portion that first slot portion is connected and (especially intersects with the first slot portion).This additional second slot portion for
Incipient crack load alternative behavior also can have positive influence.
Preferably, the second slot portion at least partly extends in the circumferential.
It is particularly preferred that at least some this slits (especially all slits) are substantially T shape.
According to the utility model, the free end of the second slot portion can have the slit ends of bending adjacent thereto, special
Not, which is bent into the shape of hook, wherein advantageously, the free end group of multiple slit ends of a slit
This direction is each other.Due to this slit ends, notch effect is reduced.
Preferably, the free end of the second slot portion has recess portion adjacent thereto, especially circular recess.This recess portion
For reducing notch effect.
Advantageously, the second slot portion and/or slit ends have the width between 0.05mm and 1.5mm, and the width is special
It is not in the range of 0.1mm to 0.5mm.
A variant according to the present utility model, attachment web are equipped with several elongated through-holes, the quantity of elongated through-hole
It is particularly corresponding to the quantity of slit, wherein through-hole preferably intersects with slit, wherein the special shape of through-hole and slit intersected with each other
It is at T-shaped.This through-hole is for guiding cooling fluid to pass through attachment web.Using this variant, being attached web can be by directly cold
But.
Preferably, through-hole substantially extends in the circumferential.
One embodiment according to the present utility model, through-hole have width in the range of 3mm to 10mm, and the width is special
It is not in the range of 4mm to 6mm.
The free end area of through-hole advantageously circle, to reduce notch effect, wherein free end area it is radial to
The part of outer arrangement is particularly respectively depicted as semi-parabolic shape.Experiment shows to provide parabola relative to notch effect
The curvature of shape leads to better result compared with the curvature of such as circle-arc profile.
In order to realize purpose described in introductory song, the utility model has one it is further proposed that a kind of gas-turbine plant
A gas turbine housing, an axis and at least one combustion chamber being disposed in outside gas turbine housing, in the gas turbine
A compressor and a turbine are received in shell, which passes through gas turbine housing and compressor and turbine is connected to each other,
At least one combustion chamber via be disposed in inside gas turbine housing according to the present utility model hot gas conduction shell and
It is fluidly connected to the gas turbine housing, wherein the axis is surrounded by the inner wall of tube shell of hot gas conduction shell, and in one
Empty tube shape axis protection shell is disposed between inner wall of tube shell and axis, which includes being provided with protruding outward for circumferential groove
Annular shoulder, the attachment web of hot gas conduction shell, annular shoulder and hot gas conduction shell are received in circumferential groove
Inner wall of tube shell is spaced apart in radial directions with predetermined amount.
Preferably, the anti-radiation protection shell of a hollow cylinder shape is provided with multiple cold air openings, anti-radiation protection
Pipe is disposed between axis protection shell and inner wall of tube shell, and is attached to axis protection shell.This anti-radiation protection shell is used
In preventing: the transmitting of heat in axial direction from inner wall of tube shell.In addition, providing hot gas conduction via cold air openings
The impinging air of the inner wall of tube shell of shell is cooling, realizes very effective cooling effect by this method.
Advantageously, anti-radiation protection shell is directly adjacent to annular shoulder and is attached or is attached directly to annular shoulder.This
Have the effect that impinging air cooling also cools down transitional region, wherein the transitional region is in hot gas conducting tube
The inner wall of tube shell of shell and from inner wall of tube shell between attachment web outstanding.
Detailed description of the invention
Gas-turbine plant below in reference to attached drawing and embodiment according to the present utility model and according to the utility model
Various hot gas conduct shell, come to the utility model further feature and advantage be illustrated, wherein
Fig. 1 shows the schematic perspective view of the gas-turbine plant of embodiment according to the present utility model；
Fig. 2 shows the schematic perspective views of the hot gas for the gas-turbine plant described in Fig. 1 conduction shell；
Fig. 3 shows the perspective partial view for the hot gas conduction shell described in Fig. 2；
Fig. 4 shows the amplification sectional view in the following region for the gas turbine described in Fig. 1, shows in Fig. 2 in this region
Hot gas conduction shell out is fixed to the axis protection shell of gas-turbine plant；
Fig. 5 shows the first embodiment of the utility model of the attachment web for the hot gas conduction shell described in Fig. 2
Front view；
Fig. 6 shows the front view of the attachment web of second embodiment according to the present utility model；
Fig. 7 shows the front view of the attachment web of 3rd embodiment according to the present utility model；
Fig. 8 shows the front view of the attachment web of fourth embodiment according to the present utility model；
Fig. 9 shows the view of the alternative embodiment in the region described in Fig. 4；
Figure 10 shows the front view of the attachment web of the 5th embodiment according to the present utility model；With
Figure 11 shows the front view of the attachment web of sixth embodiment according to the present utility model.
Specific embodiment
Attached drawing shows the embodiment of its multiple component of gas-turbine plant 1/ according to the present utility model.Gas turbine is set
Standby 1 includes gas turbine housing 2, and gas turbine housing 2 receives the compressor 3 and turbine 4 being connected to each other via axis 5.In addition, combustion
Gas turbine equipment 1 includes two combustion chambers not being shown specifically in Fig. 1, the two combustion chambers in the form of silo combustion chamber and by
It is arranged in the side of gas turbine housing 2, and via corresponding hot gas pipeline 6 and be accepted in gas turbine housing 2
Body conducts the flowing connection of shell 7.Hot gas conducts the hot gas conduit 8 that shell 7 includes basic annular cross section.Hot gas conduit
8 are inwardly defined by shell outer wall 10 by inner wall of tube shell 9 and outward, and wherein shell outer wall 10, which has, is arranged in shell outer wall 10
In two heater gas inlet ports opening 11, the two heater gas inlet ports opening 11 is fluidly connected to one of pipeline respectively
6, and therefore it is connected to one of combustion chamber.Hot gas conduit 8 is in one end by by inner wall of tube shell 9 and shell outer wall
The 10 shell end walls 12 being connected to each other are closed, and hot gas conduit 8 is provided with annular hot gas outlet opening in its other end
13, wherein shell end wall 12 is directed upwards towards in the side of compressor 3, and hot gas outlet opening 13 is directed upwards towards in the side of turbine 4.
Inwardly projecting annular attachment web 14 is protruded from hot gas outlet 13 neighbouring points of opening from inner wall of tube shell 9 radially.
Web 14 is attached around it, is provided with the multiple slits 15 for passing through attachment web 14 in the axial direction, slit is with equal
Distance arrangement, wherein pitch t is 5 ° in this case.Slit 15 be substantially T shape and including the first slot portion 16 and the
Two slot portions 17, wherein the first slot portion 16 is radially extended since the free end of attachment web 14, the connection of the second slot portion 17
Intersect to the first slot portion 16 and with the first slot portion 16, wherein the free end of the second slot portion 17 be respectively engaged to it is round recessed
Portion 18.The first slot portion 16 and the second slot portion 17 of each slit 24 are included in the width B within the scope of 0.1mm to 0.5mm, and
And it is cut and is generated by means of water jet.For manufacturing purpose, the outside of inner wall of tube shell 9, initially form from its free end it is recessed
Portion 19, this makes it possible to water jet nozzle extremely close to attachment web 14.
Attachment web 14 is kept in circumferential groove 20, and circumferential groove 20 is in radial directions with inner wall of tube shell 9 with preset distance
And be formed in the annular shoulder 21 of hollow tube-shape axis protection shell 22, axis protection pipe shell 22 conducts shell in hot gas
Axis 5 is surrounded in 7 region, and is disposed between axis 5 and the inner wall of tube shell 9 of hot gas conduction shell 7.Hollow cylinder shape
Anti-radiation protection shell 24 be provided with cold air openings 23, the anti-radiation protection shell 24 of hollow cylinder shape protects shell in axis
Extend between 22 and inner wall of tube shell 9, and is also accepted in the annular recess 25 of axis protection shell 22.It is cyclic annular recessed according to Fig. 4
Portion 25 is formed in from the second annular shoulder 26 that axis protection shell 22 projects radially outwardly, second annular shoulder 26 and attachment
There is the annular shoulder 21 of hot gas conduction shell 7 to be separated by a certain distance and be arranged.First cyclic annular cooling air pipeline 27 is limited
It is scheduled between anti-radiation protection shell 24 and the inner wall of tube shell 9 of hot gas conduction shell 7, in the normal operating of gas-turbine plant 1
Period, cooling air are directed upward through the cooling air pipeline 27 from compressor 3 in the side of turbine 4.Cooling air pipeline
27 continue as cooling air drilling 28, and cooling air drilling 28 extends axially through annular shoulder 21 and in circumferential groove 15
It is formed radially inward.Another ring-type cooling air pipeline 29 be limited at axis protection shell 22 and anti-radiation protection shell 24 it
Between, and the first cooling air pipeline 27 is fluidly connected to via cold air openings 23.
During the normal operating of gas-turbine plant 1, fuel-air mixture is burned in a combustion chamber, wherein firing
It burns room and is supplied with the compression environment air from compressor 3.Pressurized hot combustion gas is generated in a combustion chamber via pipe
Road 6 and heater gas inlet port opening 11 and be introduced into hot gas conduction shell 7 in, then flow through hot gas conduit 8, and pass through heat
Gas vent opening 13 and be introduced into gas turbine housing 2 on the direction of turbine 4.Hot gas conducts in the shell of shell 7
For wall 9 due to being contacted with hot combustion gas by compared with heat-flash stress, hot gas conducts the inner wall of tube shell 9 of shell 7 by means of cooling
Air and be cooled, cooling air absorbs heat when flowing through the first cooling air pipeline 27, from inner wall of tube shell 9, and is passing through shape
It dissipates at after the cooling air drilling 28 in the annular shoulder 21 of axis protection shell 22, on the direction of turbine 4.In shell
The additional cooling of wall 9 realizes that cooling air stream is conducted through by the cooling of the impinging air caused by cooling air stream
Second cooling air pipeline 29, and pass through the region that cold air openings 23 are directed directly toward inner wall of tube shell 9.
In the transitional region that hot gas is inserted between the inner wall of tube shell 9 of shell 7 and attachment web 14, there is big temperature
Difference is exposed to the temperature more much higher than attachment web 14 because inner wall of tube shell 9 is attributed to burning gases.Since slit 15 is assigned
14 one-movement-freedom-degree of attachment web has been given, stress caused by these temperature differences can be compensated largely, because
This significantly increases the quantity that the load cycle before crackle is formed in the inner wall of tube shell 9 in transitional region.As a result, maintenance and
Workshop is every being extended, it means that cost reduces.
Fig. 6 to Fig. 8 shows the view of the attachment web 14 of the slit with optional shape.
According to Fig. 6, slit 30 includes the first slot portion 31 and the second slot portion 32, the first slot portion 31 and the second slit
The design in portion 32 corresponds essentially to the design of the slot portion 16 and 17 of slit 15.The free end of second slot portion 32 all has to connect
Its slit ends 33 are bonded to, slit ends 33 bend to the shape of hook, and the free end of slit ends 33 is essentially toward each other
It is directed toward.
According to Fig. 7, slit 34 includes: the first slot portion 35, which opens from the free end of attachment web 14
Beginning extends radially outwardly；Second slot portion 36, second slot portion 36 are connected to the first slot portion 35 and intersect with it；Two hooks
The transition slot portion 37 of sub- shape, is bonded to the free end of the second slot portion 36, and is directed toward toward each other；And two thirds
Slot portion 38 is bonded to transition slot portion 37, and is basically parallel to the extension of the first slot portion 35.
According to Fig. 8, slit 39 includes the first slot portion 40, the second slot portion 41 and slit ends 42, the first slot portion
40 extend radially outwardly since the free end of attachment web 14, and the second slot portion 41 is connected to the first slot portion 40 and with first
Slot portion 40 is intersected, and slit ends 42 are bonded to the free end of the second slot portion 41 and are bent into the shape of hook, slit ends
Essentially toward being directed toward each other, wherein curvature/radius of slit ends 42, which is chosen in generally higher than Fig. 6, is shown for 42 free end
Slit ends 33 curvature/radius.
Fig. 9 and Figure 10 shows the alternative embodiment of the utility model in the region described in Fig. 4.View shows inner wall of tube shell
9, inner wall of tube shell 9 is provided with annular attachment web 43 inwardly projecting radially adjacent to hot gas outlet opening.It is attached web
43 are provided with the multiple slits 44 extended there through in the axial direction, free end diameter of the slit 44 from attachment web 43 around it
To extending outwardly and arranged with predetermined pitch with fixed range.In addition, attachment web 43 is provided with several elongated through-holes 45, count
Amount corresponds to the quantity of slit 44, and wherein through-hole 45 intersects with slit 44 and fundamental form is at T-shaped together with these slits.The example
In, the width B of slit 44 is in the range of 0.1mm to 0.5mm, and the width b of through-hole 45 is in the range of 3mm to 10mm,
And the length l of through-hole 45 is in the range of 20mm to 40mm.The free end area of through-hole 45 is round, wherein each curvature exists
This is in the shape of semicircle.Attachment web 43 is maintained in circumferential groove 46, and the axis that circumferential groove 46 is formed in hollow cylinder shape is protected
In the annular shoulder 47 of pillar shell 48, annular shoulder 47 is spaced apart in radial directions with predetermined amount with inner wall of tube shell 9, axis protection
Shell 48 surrounds axis 5 in the region of hot gas conduction shell 7, and is disposed in the shell of axis 5 and hot gas conduction shell 7
Between inner wall 9.The anti-radiation protection shell 50 of hollow cylinder shape is provided with cold air openings 49, the radiation of hollow cylinder shape
Protection shell 50 protects extension between shell 48 and inner wall of tube shell 9 in axis and anti-radiation protection shell 50 can also be accepted in ring
In the annular recess 51 of shape shoulder 47.First annular cooling air pipeline 52 is limited at anti-radiation protection shell 50 and hot gas passes
Between the inner wall of tube shell 9 of conduit shell 7, which is arranged for during the normal operating of gas-turbine plant 1, will be from pressure
The cooling air of mechanism of qi 3 is booted up in the side of turbine 4.Cooling air pipeline 52 is set up as in the side of turbine 4 attached
It connects the through-hole 45 on web 43 and continues.Another annular cooling air pipeline 53 is limited at axis protection shell 48 and anti-radiation protection
Between shell 50, and the first cooling air pipeline 52 is fluidly connected to via cold air openings 49.
The variant described in Fig. 9 has the advantages that better than the variant described in Fig. 4: the cooling of attachment web 43 is due to forming
It is improved in the through-hole 45 being attached in web 43.In addition, impinging air is cooling also close to inner wall of tube shell 9 and attachment web
In the region of transitional region between 43 effectively, because anti-radiation protection shell 50 is secured directly to annular shoulder 47.
Figure 11 shows the optional design for the through-hole 54 being used to form in attachment web 43.Describe in through-hole 54 and Figure 10
Through-hole 45 the difference is that: the curvature of free end area of the through-hole 54 in its radially outward region of arranging section is retouched
It states as semi-parabolic shape.This curvature is advantageous in terms of reducing notch effect.
Although illustrating and describing the utility model in detail by way of preferred illustrative embodiment, this is practical
It is novel not by disclosed exemplary limitation, and expert can therefrom export other variations without departing from the model of the utility model
It encloses.
Claims (26)
1. a kind of hot gas conducts shell (7), a hot gas conduit (8) including annular cross section, wherein the hot gas
Pipeline (8) is defined by a shell outer wall (10) in inside by an inner wall of tube shell (9) and in outside, the shell outer wall
(10) it is provided at least one heater gas inlet port opening (11), the hot gas conduit (8) is in one end by will be in the shell
The shell end wall (12) that wall (9) and the shell outer wall (10) are connected to each other is closed and has one in its other end
Annular hot gas outlet is open (13), one of annular attachment web (14；43) from the inner wall of tube shell (9) radially to
Interior protrusion, it is characterised in that the attachment web (14；43) it is provided with around it and passes through the attachment abdomen in the axial direction
Plate (14；43) multiple slits (15；30；34；39；44), wherein each slit all has from the attachment web (14；43)
A free end start at least one outwardly extending first slot portion (16；31；35；40).
2. shell (7) as described in claim 1, it is characterised in that the slit (15；30；34；39；44) each other with it is fixed away from
From arrangement.
3. shell (7) as claimed in claim 2, it is characterised in that the slit (15；30；34；39；44) each other to be arrived at 4 °
Pitch (t) arrangement in the range of 10 °.
4. shell (7) as described in claim 1, it is characterised in that first slot portion (16；31；35；40) at least partly
Extend in radial directions.
5. shell (7) as described in claim 1, it is characterised in that first slot portion (16；31；35；40) have
Width (B) between 0.05mm and 1.5mm.
6. the shell (7) as described in one of claim 1-5, it is characterised in that at least some of described slit slit have with
First slot portion (16；31；35；40) second slot portion (17 connected；32；36；41).
7. shell (7) as claimed in claim 6, it is characterised in that all slits in the slit have second slit
Portion (17；32；36；41).
8. shell (7) as claimed in claim 6, it is characterised in that second slot portion (17；32；36；41) with described the
One slot portion (16；31；35；40) intersect.
9. shell (7) as claimed in claim 6, it is characterised in that second slot portion (17；32；36；41) at least partly
Extend in the circumferential.
10. shell (7) as claimed in claim 6, it is characterised in that at least some of described slit slit is substantially T shape
's.
11. shell (7) as claimed in claim 10, it is characterised in that all slits in the slit are substantially T shape.
12. the shell (7) as described in one of claim 7-11, it is characterised in that multiple free ending tools of second slot portion
There are multiple slit ends (33 adjacent thereto；42), the slit ends are bendings.
13. shell (7) as claimed in claim 12, it is characterised in that the slit ends (33；42) it is bent into hook
Shape.
14. shell (7) as claimed in claim 12, it is characterised in that the slit ends (33 of a slit；42) institute
Free end is stated to substantially point to each other.
15. the shell (7) as described in one of claim 7-11, it is characterised in that multiple free ending tools of second slot portion
There are multiple recess portions (18) adjacent thereto.
16. shell (7) as claimed in claim 15, it is characterised in that the recess portion (18) is circular recess.
17. shell (7) as claimed in claim 12, it is characterised in that second slot portion (17；32；36；41) and/or institute
State slit ends (33；42) there is the width between 0.05mm and 1.5mm.
18. the shell (7) as described in one of claim 1 to 5, it is characterised in that the attachment web is provided with several elongated logical
Hole (45；54).
19. shell (7) as claimed in claim 18, it is characterised in that the elongated through-hole (45；54) number corresponds to narrow
The number of slot.
20. shell (7) as claimed in claim 18, it is characterised in that multiple through-holes (45 intersected with each other；54) and it is multiple narrow
Flute profile is at T-shaped.
21. shell (7) as claimed in claim 18, it is characterised in that the through-hole (45；54) essence extends in the circumferential.
22. shell (7) as claimed in claim 18, it is characterised in that the through-hole (45；54) there is the model in 3mm to 10mm
Enclose interior width (b).
23. shell (7) as claimed in claim 18, it is characterised in that the through-hole (45；54) multiple free end area are
Round.
24. a kind of gas-turbine plant (1), which is characterized in that have a gas turbine housing (2), an axis (5) and arrangement
In at least one external combustion chamber of the gas turbine housing (2), a compressor (3) and a turbine (4) are accepted in
In the gas turbine housing (2), the axis (5) pass through the gas turbine housing (2) and by the compressor (3) with it is described
Turbine (4) is connected to each other, at least one described combustion chamber via be arranged in the gas turbine housing (2) it is internal as right is wanted
It asks the conduction of hot gas described in one of 1-23 shell (7) and is fluidly connected to the gas turbine housing (2), wherein the axis
(5) it is surrounded by the inner wall of tube shell (9) of hot gas conduction shell (7), and a hollow tube-shape axis protects shell
(22；48) it is disposed between the inner wall of tube shell (9) and the axis (5), the protection shell includes outwardly projecting one
Annular shoulder (21；47), the annular shoulder (21；47) it is provided with a circumferential groove (20；46), the hot gas conducts shell
(7) the attachment web (14；43) it is accepted in the circumferential groove (20；46) in, the annular shoulder and the hot gas
The inner wall of tube shell (9) for conducting shell (7) is spaced apart in radial directions with predetermined amount.
25. gas-turbine plant (1) as claimed in claim 24, it is characterised in that protect shell (22 in the axis；48) with
The anti-radiation protection shell (24 an of hollow cylinder shape is disposed between the inner wall of tube shell (9)；50), the anti-radiation protection pipe
Shell (24；50) multiple cold air openings (23 are provided with；49), and it is attached to the axis protection shell (22；48).
26. gas-turbine plant (1) as claimed in claim 25, it is characterised in that the anti-radiation protection shell is directly adjacent to institute
It states annular shoulder and is attached or is attached directly to the annular shoulder.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102015207760.8A DE102015207760A1 (en) | 2015-04-28 | 2015-04-28 | Hot gas carrying housing |
| DE102015207760.8 | 2015-04-28 | ||
| PCT/EP2016/058891 WO2016173920A1 (en) | 2015-04-28 | 2016-04-21 | Hot gas-conducting casing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209637884U true CN209637884U (en) | 2019-11-15 |
Family
ID=55953112
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201690000776.6U Active CN209637884U (en) | 2015-04-28 | 2016-04-21 | Hot gas conducts shell and gas-turbine plant |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP3256783B1 (en) |
| CN (1) | CN209637884U (en) |
| DE (1) | DE102015207760A1 (en) |
| HU (1) | HUE043070T2 (en) |
| WO (1) | WO2016173920A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102017211866A1 (en) * | 2017-07-11 | 2019-01-17 | MTU Aero Engines AG | Guide vane segment with curved relief gap |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4413477A (en) * | 1980-12-29 | 1983-11-08 | General Electric Company | Liner assembly for gas turbine combustor |
| DE10032454A1 (en) * | 2000-07-04 | 2002-01-17 | Man Turbomasch Ag Ghh Borsig | Device for cooling an unevenly highly temperature-stressed component |
| DE50306044D1 (en) * | 2003-09-05 | 2007-02-01 | Siemens Ag | Shovel of a turbine |
| US7805946B2 (en) * | 2005-12-08 | 2010-10-05 | Siemens Energy, Inc. | Combustor flow sleeve attachment system |
| EP2157284A1 (en) * | 2008-08-21 | 2010-02-24 | Siemens Aktiengesellschaft | Gas turbine assembly with a non-cylindrical transition duct and method for guiding the flow onto the turbine |
| US8511089B2 (en) * | 2009-07-31 | 2013-08-20 | Rolls-Royce Corporation | Relief slot for combustion liner |
-
2015
- 2015-04-28 DE DE102015207760.8A patent/DE102015207760A1/en not_active Ceased
-
2016
- 2016-04-21 WO PCT/EP2016/058891 patent/WO2016173920A1/en active Application Filing
- 2016-04-21 CN CN201690000776.6U patent/CN209637884U/en active Active
- 2016-04-21 EP EP16721373.5A patent/EP3256783B1/en active Active
- 2016-04-21 HU HUE16721373A patent/HUE043070T2/en unknown
Also Published As
| Publication number | Publication date |
|---|---|
| EP3256783A1 (en) | 2017-12-20 |
| DE102015207760A1 (en) | 2016-11-03 |
| WO2016173920A1 (en) | 2016-11-03 |
| EP3256783B1 (en) | 2019-02-20 |
| HUE043070T2 (en) | 2019-08-28 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220913 Address after: Munich, Germany Patentee after: Siemens Energy International Address before: Munich, Germany Patentee before: SIEMENS AG |
|
| TR01 | Transfer of patent right |