CN110017178A - Hot gas path component for gas turbine - Google Patents
Hot gas path component for gas turbine Download PDFInfo
- Publication number
- CN110017178A CN110017178A CN201811359969.2A CN201811359969A CN110017178A CN 110017178 A CN110017178 A CN 110017178A CN 201811359969 A CN201811359969 A CN 201811359969A CN 110017178 A CN110017178 A CN 110017178A
- Authority
- CN
- China
- Prior art keywords
- tubular wall
- hot gas
- wall structures
- gas path
- path component
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- 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
- F23R3/002—Wall structures
-
- 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
- F23R3/005—Combined with pressure or heat exchangers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/12—Two-dimensional rectangular
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/13—Two-dimensional trapezoidal
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/14—Two-dimensional elliptical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/25—Three-dimensional helical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
-
- 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
- F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow
-
- 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
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
A kind of hot gas path component for gas-turbine unit extends through multiple cooling ducts (27) of tubular wall structures including tubular wall structures (25) and between the upstream end (28) and downstream (29) of tubular wall structures.The interior section (33) of tubular wall structures being defined between inner surface (30) and cooling duct has first thickness (T1), also, the exterior section (35) of tubular wall structures being defined between outer surface (31) and cooling duct has the second thickness (T2) greater than first thickness (T1).Cooling duct has radial height (H), radial height (H) is limited by the maximum radial distance between the interior section of tubular wall structures (25) (33) and exterior section (35) across cooling duct (27), also, the radial height (H) of cooling duct (27) is greater than the first thickness (T1) of the interior section (33) of tubular wall structures (25).
Description
Cross-reference to related applications
This application claims the priority for the European patent application No. 17201913.5 for being filed on November 15th, 2017, the patents
The disclosure of application is merged by reference.
Technical field
The present invention relates to a kind of hot gas path components for gas-turbine unit.
Background technique
As it is known, the burner of gas-turbine unit includes hot gas path, and in the inside of hot gas path, fuel
It mixes with air and burns.The hot gas thus generated is then supplied to the turbine or expansion section of gas-turbine unit, is used for
Thermal energy and kinetic energy is set to be converted into mechanical energy.
Hot gas path is substantially defined by the tubular wall of inner surface and cold outer surface with heat, and can be by several
Component is formed.Hot gas path component may include one or more burning blocks and transition duct, and burning block limits corresponding
Combustion space (for example, in the case where sequential combustion device).Transition duct is configured to for hot gas being directed in turbine inlet, and because
And it is exposed to high temperature.As other components of gas-turbine unit, defining the component of hot gas path, (and especially transition is led
Pipe) cooling is also required, to avoid the damage caused by overheating, and extend the service life.For the purpose for keeping hot gas path component cooling,
A part of total air stream is generally obtained from compressor, and cooling system is fed to by the gas chamber around burner
System.It can be used the known cooling system of several species, such as impinging cooling system, to flow cooling system or nearly wall cooling system
System.However, all known systems all (will be such as expectation by the ignition temperature for not allowing to further increase in hot gas path
As), and actually or the limitation of the operation of otherwise impact gas turbine device.Typical limitation is, cold with being realized
But effect compares the big pressure loss, reduces the air consumption of engine efficiency, especially influences the thermal extraction of nearly wall cooling system.
Nearly wall is cooling actually to utilize small cooling duct, and cooling duct is located in hot gas path wall, thus is in close proximity to hot gas road
The hot surface of diameter wall, and it is highly efficient in principle.However, small channel is merely capable of the small air of delivery promptly heating
Stream.It is thus known that nearly wall cooling system in practice for make hot gas path wall short part it is cooling for be efficient, but
Cooling effect rapidly declines over a longer distance.
Other than thermic load, hot gas path component also needs to bear may during the operation of gas-turbine unit
Quite violent mechanical stress caused by the mechanical oscillation of generation and/or thermoacoustic vibration.For this reason, tubular burner
Hot gas wall is usually relatively thick, to provide required mechanical toughness.However, the bigger thickness of wall with impact arrangement and it is right
The cooling efficiency of flow arrangement mutually conflicts.
Summary of the invention
It is an object of the present invention to provide a kind of hot gas path component for gas-turbine unit, the hot gas path components
Allow to overcome or at least weaken described limitation.
According to the present invention, it is provided with a kind of hot gas path component comprising:
Tubular wall structures, with upstream end, downstream, inner surface and outer surface；
Multiple cooling ducts extend through tubular wall structures between upstream end and downstream；
Wherein, the interior section of tubular wall structures being defined between inner surface and cooling duct has first thickness, also, manages
The exterior section of shape wall construction being defined between outer surface and cooling duct has the second thickness greater than first thickness；And
And
Wherein, cooling duct has radial height, and radial height is by between the interior section and exterior section of tubular wall structures
Maximum radial distance across cooling duct is limited, also, the radial height of cooling duct is greater than the inside of tubular wall structures
Partial first thickness.
Hot gas path component thus combines effective cooling effect and mechanical strength, to bear violent thermic load and machinery
Both loads.On the one hand, in fact, cooling duct can be located at the inner surface away from tubular wall structures, (it is directly exposed to heat
Gas) short distance at.Therefore, the dissipation of heat is efficient.On the other hand, cooling duct radially extends through tubular wall knot
Sizable amount of the general thickness of structure, thus be conducive to the process of enough cooling air streams.Thus, not only cooling duct can
To extend very close in inner surface, and thermal extraction can also be kept as it is low.Meanwhile the exterior section of tubular wall structures is thick
To required mechanical resistance is enough to provide, without influencing the dissipation of heat.
According to another aspect of the present invention, second thickness is twice to five times of first thickness.
Above the ratio of indicated first thickness and second thickness helps to ensure the cooling effect at inner surface, and
Both mechanical resistances.
According to another aspect of the present invention, the radial height of cooling duct is the first thickness of the interior section of tubular wall structures
At least three times of degree.
Above the ratio of indicated radial height and first thickness helps to ensure the low heat in cooling air stream
It extracts.
According to another aspect of the present invention, radial height is greater than the width of cooling duct.
According to another aspect of the present invention, adjacent cooling duct passes through interior section transverse to tubular wall structures and outer
The diaphragm of portion part and be separated from each other.
Diaphragm provides the interior section of tubular wall structures and exterior section is mechanically connected and makes the dissipation of heat (to serve as
Dissipation fin) dual function.
According to another aspect of the present invention, diaphragm is substantially perpendicular to the interior section and exterior section of tubular wall structures.
According to another aspect of the present invention, the interior section and exterior section of diaphragm and tubular wall structures form 30 ° and 90 °
Between angle.
Angled diaphragm increases flexibility to tubular wall structures, thus generally reduces the sensitivity to vibration and mechanical stress
Property.
According to another aspect of the present invention, diaphragm tapers to exterior section from the interior section of tubular wall structures, or from pipe
The exterior section of shape wall construction tapers to interior section.
Tapered diaphragm allows for the engineering properties of tubular wall structures and the satisfactory compromise of thermal property.Diaphragm
Rigidity and conductive heat transfer are improved in thicker part, however, relatively thin part causes to be pyrolyzed coupling.Thus, diaphragm thicker or compared with
Thin part can be located at the interior section or exterior section of tubular wall structures, in as desired as and optimize the dissipation of heat,
It is pyrolyzed coupling and mechanical resistance.
According to another aspect of the present invention, cooling duct has the square at the turning with rounding or the turning without rounding
Shape or parallelogram or trapezoidal cross section, or the cross section of ellipse.
The shape and form that can select cross section optimize air stream and cooling effect as desired.
According to another aspect of the present invention, hot gas path component includes at least one fin, out of tubular wall structures
Portion part is longitudinally extended along at least one of cooling duct.
Fin in cooling duct is further improved the dissipation of heat and cooling effectiveness.
According to another aspect of the present invention, cooling duct is equably distributed along the circumferential direction of tubular wall structures.
In this way, realizing uniform cooling effect throughout entire component.
According to another aspect of the present invention, cooling duct is along the axis vertical direction of tubular wall structures or along around tubulose
The spirality path of the longitudinal axis of wall construction and extend.
It can choose the design of cooling duct, thus to optimize cooling effect as required.
According to another aspect of the present invention, it is provided with a kind of hot gas path component for gas-turbine unit, is wrapped
Include the hot gas path component as defined in above.
According to another aspect of the present invention, hot gas path component is transition duct.
Transition duct is usually one of component of most critical, because transition duct is exposed to the highest temperature in hot gas path
Degree.Thus, it is particularly beneficial to apply the present invention to transition duct.
According to another aspect of the present invention, it is provided with a kind of gas turbine assembly comprising:
Compressor section extends along main shaft；
Multiple tubular burners are circumferentially arranged around main shaft；
Turbine；
Wherein, at least one of tubular burner includes the hot gas wall member as defined in above.
Detailed description of the invention
Will now be described with reference to the attached figures the present invention, attached drawing shows some non-limiting embodiments of the present invention,
In:
Fig. 1 is the axially fore-and-aft plane of gas-turbine unit and the side view intercepted；
Fig. 2 is the side view of the hot gas path of the gas-turbine unit of Fig. 1；
Fig. 3 is the perspective view of the hot gas path component of the hot gas path of Fig. 2 of embodiment according to the present invention；
Fig. 4 is the rearview of the hot gas path component of Fig. 2；
Fig. 5 is the rearview of the details of the hot gas path component of Fig. 2；
Fig. 6 is the perspective view of hot gas path component according to another embodiment of the present invention；
Fig. 7 is the perspective view of hot gas path component according to another embodiment of the present invention；
Fig. 8 is the rearview of the details of hot gas path component according to another embodiment of the present invention；
Fig. 9 is the rearview of the details of hot gas path component according to another embodiment of the present invention；
Figure 10 is the rearview of the details of hot gas path component according to another embodiment of the present invention；And
Figure 11 is the rearview of the details of hot gas path component according to another embodiment of the present invention.
Specific embodiment
Fig. 1 is shown as a whole and with the simplification view of the gas-turbine unit of 1 mark of number.Gas turbine starts
Machine 1 includes compressor section 2, burner assembly 3 and turbine 5.Compressor section 2 and turbine 5 are along main shaft A
Extend.Burner assembly 3 can be sequential combustion device assembly or single stage combustion device assembly in the example such as Fig. 1.In a reality
It applies in example, burner assembly 3 includes the multiple sequence tubular burners 7 being circumferentially arranged around main shaft A.
The compressor section 3 of gas-turbine unit 1 provides the air stream of compression, and the air stream of the compression is together with fuel
It makes an addition in tubular burner 7, and burns in tubular burner 7.For cooling purpose, what compressor section 2 was conveyed
Air stream is supplied to burner assembly 3, and is supplied to turbine 5.
It is each including first-stage burning device 8 and second level burning in tubular burner 7 (one of display in Fig. 2)
Device 9 and transition duct 10, these components are sequentially arranged, and limit hot gas path 12.
More specifically, first-stage burning device 8 includes first order burner device 14 and first-stage burning room 15.
Second level burner 9 is arranged in the downstream of first-stage burning device 8, and including second level burner device 17 and second
Grade combustion chamber 18.In addition, second level burner 9 is connected to turbine 5 (not showing herein) by transition duct 10.
Second level combustion chamber 18 axially extends in the downstream of first-stage burning device 8.In one embodiment,
Second level combustion chamber 20 includes external bushing 21 and neck bush 22.External bushing 21 away from neck bush 22 at a certain distance from around liner
Set 22, so that convection current cooling duct 23 is defined between external bushing 21 and neck bush 22.
Transition duct 10 is illustrated in greater detail in figs. 3 and 4, and transition duct 10 is in hot gas path 12 by most acutely
Thermal stress component.Transition duct 10 includes multiple cooling ducts 27.
Tubular wall structures 25 have upstream end 28, downstream 29, inner surface 30 and outer surface 31.Upstream end 28 is attached to
Second level combustion chamber 19, however, downstream 29 is towards turbine 5.Inner surface 30 defines hot gas fluid space, and hot gas passes through the heat
Airflow space and reach turbine 5.Therefore, inner surface 30 is directly exposed to flow through the hot gas of hot gas path 12.
Cooling duct 27 extends through tubular wall structures 25 between upstream end 28 and downstream 29, and along tubular wall structures
25 circumferential direction is equably distributed.At upstream end 28, the convection current cooling duct of cooling duct 27 and second level combustion chamber 18
23 communications.In one embodiment, cooling duct 27 extends along the axis vertical direction of tubular wall structures 25.
Cooling duct 27 also separates the different parts of tubular wall structures 25.As also shown in Fig. 5, tubulose
The interior section 33 of wall construction 25 is defined between inner surface 30 and cooling duct 27, and has first thickness T1 (that is, inner surface
Minimum range between 30 and cooling duct 27).The exterior section 35 of tubular wall structures 25 is defined in outer surface 31 and cooling is logical
Between road 27, and there is second thickness T2.The second thickness T2 of exterior section is greater than the first thickness T1 of interior section 33.Specifically
Ground, second thickness T2 can be twice to five times of first thickness T1.
Cooling duct 27 have radial height H, radial height H by tubular wall structures 25 interior section 33 and outside portion
The maximum radial distance between 35 across cooling duct 27 is divided to be limited.The radial height H of cooling duct is greater than tubulose significantly
The first thickness T1 of the interior section 33 of wall construction 25.Cooling duct 27 thus has sizable cross section, and allows to be enough
Avoid cooling effect may be by the process for the cooling air stream that thermal extraction is seriously affected.Specifically, radial height H can be
At least three times of the first thickness T1 of the interior section 33 of tubular wall structures 25 and up to 20 times.
Radial height H is similarly greater than the width W of cooling duct.
Adjacent cooling duct 27 is separated from each other by diaphragm 37, and diaphragm 37 is transverse to the inside portion of tubular wall structures 25
Points 33 and exterior section 35 and extend.In the embodiment of Fig. 3-5, specifically, diaphragm 37 is substantially perpendicular to tubular wall structures
25 interior section 33 and exterior section 35.In this case, diaphragm 37 has uniform thickness, and passes through smooth rounding
Transition part and the interior section of tubular wall structures 25 33 and exterior section 35 are coupled.As a result, cooling duct 27 has substantially
The cross section of ellipse has substantially straight side.
Cooling duct can have any suitable path between the upstream end and downstream of transition duct, in order to provide
Desired cooling effect.In the embodiment in fig 6, for example, transition duct, which has, has upstream end substantially as has been described
128, the tubular wall structures of downstream 129, inner surface 130, outer surface 131, interior section 133 and exterior section 135 are (herein
It is indicated by number 125).Cooling duct 127 (it similarly has aspect ratio and size as has been described) is along around tubulose
The spirality path of the longitudinal axis B of wall construction 125 and extend.
In one embodiment shown in Fig. 7, transition duct 225, which has, has upstream substantially as has been described
Hold the tubular wall structures of 228, downstream 229, inner surface 230, outer surface 231, interior section 233 and exterior section 235
225.Cooling duct 227 extends between upstream end 228 and downstream 229, and is separated from each other by diaphragm 237.Diaphragm 237
It to be discontinuous, and is interrupted by notch 238, notch 238 can be as in fig. 7 along the substantially circumferential of tubular wall structures 225
Direction and be aligned, or in addition interlock as desired in additional embodiments not shown.The notch of diaphragm 238
238 help to reduce the mechanical stress caused by thermally expanding.
In another embodiment of Fig. 8, transition duct has the tubulose with cooling duct 327 as mentioned
Wall construction 325, only the cross section of cooling duct 327 is substantially rectangular cross-sectional configuration (turning that may have rounding).Dissipation fin 340
It is longitudinally extended from the interior section 333 of tubular wall structures 325 along cooling duct 327.In other embodiments (not shown)
In, according to specific requirement, only some cooling ducts can be equipped with dissipation fin.
In the embodiment in fig. 9, transition duct, which has to have, passes through the separated cooling duct 427 of diaphragm 437
Tubular wall structures 425.The interior section 433 and exterior section 435 of diaphragm 437 and tubular wall structures 425 formed 30 ° with 90 ° it
Between angle [alpha].As a result, the form of the cross section parallelogram of cooling duct 427.
Another embodiment is shown in FIG. 10.In this case, transition duct has with mutual by diaphragm 537
The tubular wall structures 525 of separated cooling duct 527.Diaphragm 537 tapers to interior from the exterior section 535 of tubular wall structures 525
Portion part 533.As a result, cooling duct 527 has trapezoidal cross section, wherein wider bottom edge is in the outer of tubular wall structures 525
At portion part 535, and lesser bottom edge is at the interior section 533 of tubular wall structures 525.
In the embodiment in figure 11, transition duct, which has to have, passes through the separated cooling duct 627 of diaphragm 637
Tubular wall structures 625.Diaphragm 637 tapers to exterior section 635 from the interior section 633 of tubular wall structures 625.Similarly, exist
In this case, cooling duct has trapezoidal cross section, but wherein interior section of the wider bottom edge in tubular wall structures 625
At 633, and lesser bottom edge is at the exterior section of tubular wall structures 625.
Finally it is clear that can modify to described transition duct and modification, without departing from the present invention
Such as limited range in the dependent claims.
Specifically, any other component of hot gas path may have the structure being outlined above, and the structure is with pipe
Shape wall construction and the relatively large cooling duct extended across tubular wall structures.In unshowned one embodiment, example
Such as, second level combustion chamber can have structure identical with transition duct, and wherein the cooling duct of second level combustion chamber is fluidly
It is connected to the corresponding cooling duct of transition duct.Second level combustion chamber and transition duct can be formed in single unitary body
In.
Claims (15)
1. a kind of hot gas path component for gas-turbine unit, comprising:
Tubular wall structures (25,225,325,425,525,625), with upstream end (28,228), downstream (29,
229), inner surface (30,230) and outer surface (31,231)；
Multiple cooling ducts (27,227,327,427,527,627), the upstream end (28,228) and it is described under
The tubular wall structures (25,225,325,425,525,625) are extended through between You Duan (29,229)；
Wherein, the tubular wall structures (25,225,325,425,525,625) be defined in the inner surface (30,
230) interior section between the cooling duct (27,227,327,427,527,627) (33,233,333,
433,533,633) there is first thickness (T1), and the tubular wall structures (25,225,325,425,525,
625) the be defined in outer surface (31,231) and the cooling duct (27,227,327,427,527,627) it
Between exterior section (35,235,335,435,535,635) have greater than the first thickness (T1) second thickness
(T2)；Also,
Wherein, the cooling duct (27,227,327,427,527,627) has radial height (H), described radial high
Spend (H) by the tubular wall structures (25,225,325,425,525,625) the interior section (33,233,
333,433,533,633) across described cold between the exterior section (35,235,335,435,535,635)
But the maximum radial distance of channel (27,227,327,427,527,627) is limited, also, the cooling duct (27,
227,327,427,527,627) the radial height (H) be greater than the tubular wall structures (25,225,325,
425,525,625) first thickness (T1) of the interior section (33,233,333,433,533,633).
2. hot gas path component according to claim 1, which is characterized in that the second thickness (T2) is described first thick
Spend twice to five times of (T1).
3. hot gas path component according to claim 1 or 2, which is characterized in that the cooling duct (27,227,
327,427,527,627) the radial height (H) be the tubular wall structures (25,225,325,425,525,
625) at least three times of the first thickness (T1) of the interior section (33,233,333,433,533,633).
4. hot gas path component according to any one of the preceding claims, which is characterized in that the radial height
(H) it is greater than the width (W) of the cooling duct (27,227,327,427,527,627).
5. hot gas path component according to any one of the preceding claims, which is characterized in that adjacent cooling duct
(27,227,327,427,527,627) pass through diaphragm (37,237,337,437,537,637) and be separated from each other,
The diaphragm (37,237,337,437,537,637) transverse to the tubular wall structures (25,225,325,425,
The interior section (33,233,333,433,533,633) 525,625) and the exterior section (35,235,
335, 435, 535, 635)。
6. hot gas path component according to claim 5, which is characterized in that the diaphragm (37,237,337,437,
537,637) be substantially perpendicular to the tubular wall structures (25,225,325,525,625) the interior section (33,
233,333,533,633) and the exterior section (35,235,335,535,635) or the diaphragm (437) and institute
The interior section (433) and the exterior section (435) for stating tubular wall structures (425) form the angle between 30 ° and 90 °
Degree.
7. hot gas path component according to claim 5 or 6, which is characterized in that the diaphragm (537,637) is from described
The interior section (533,633) of tubular wall structures (525,625) tapers to the exterior section (535,635), or from
The exterior section (535,635) of the tubular wall structures (525,625) tapers to the interior section (533,633).
8. the hot gas path component according to any one of claim 5-7, which is characterized in that the diaphragm (237) is
It is discontinuous, and interrupted by notch (238).
9. hot gas path component according to any one of the preceding claims, which is characterized in that the cooling duct
(27,227,327,427,527,627) there is turning with rounding or without the rectangle at turning of rounding or parallel
Quadrangle or trapezoidal cross section, or the cross section of ellipse.
10. hot gas path component according to any one of the preceding claims, which is characterized in that the hot gas path structure
Part includes at least one fin (340), the interior section (333) of the fin (340) from the tubular wall structures (325)
It is longitudinally extended along at least one of the cooling duct (327).
11. hot gas path component according to any one of the preceding claims, which is characterized in that the cooling duct
(27,227,327,427,527,627) along the tubular wall structures (25,225,325,425,525,625)
Circumferential direction is equably distributed.
12. hot gas path component according to any one of the preceding claims, which is characterized in that the cooling duct
(27,227) along the axis vertical direction of the tubular wall structures (25), or along around the vertical of the tubular wall structures (125)
Extend to the spirality path of axis.
13. a kind of hot gas path component for gas-turbine unit, including according to any one of preceding claims institute
The hot gas path component stated.
14. hot gas path component according to claim 13, which is characterized in that the hot gas path component is that transition is led
Pipe.
15. a kind of gas-turbine unit, comprising:
Compressor section (2) extends along main shaft (A)；
Multiple tubular burners (7) are circumferentially arranged around the main shaft (A)；
Turbine (5)；
Wherein, at least one of described tubular burner (7) includes heat according to any one of the preceding claims
Gas wall component.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP17201913.5A EP3486431B1 (en) | 2017-11-15 | 2017-11-15 | Hot gas path component for a gas turbine engine and a gas turbine engine comprising the same |
| EP17201913.5 | 2017-11-15 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110017178A true CN110017178A (en) | 2019-07-16 |
| CN110017178B CN110017178B (en) | 2023-06-16 |
Family
ID=60327226
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811359969.2A Active CN110017178B (en) | 2017-11-15 | 2018-11-15 | Hot gas path component for a gas turbine |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP3486431B1 (en) |
| CN (1) | CN110017178B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102019204544A1 (en) * | 2019-04-01 | 2020-10-01 | Siemens Aktiengesellschaft | Tube combustion chamber system and gas turbine system with such a tube combustion chamber system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07198142A (en) * | 1993-12-20 | 1995-08-01 | Abb Manag Ag | Equipment for convection-cooling airtight combustion chamber |
| US20060219191A1 (en) * | 2005-04-04 | 2006-10-05 | United Technologies Corporation | Heat transfer enhancement features for a tubular wall combustion chamber |
| CN102213429A (en) * | 2010-04-09 | 2011-10-12 | 通用电气公司 | Combustor liner helical cooling apparatus |
| CN103764974A (en) * | 2011-09-27 | 2014-04-30 | 三菱重工业株式会社 | Combustor tail pipe, gas turbine with tail pipe, and method for manufacturing tail pipe |
| CN107250512A (en) * | 2015-02-24 | 2017-10-13 | 三菱日立电力系统株式会社 | Burner coldplate, the transition piece and burner that possess the burner coldplate and the gas turbine for possessing burner |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB626275A (en) * | 1947-08-22 | 1949-07-12 | Parsons & Co Ltd C A | Improvements in or relating to flame tubes for gas turbine combustion chambers |
| US8955330B2 (en) * | 2011-03-29 | 2015-02-17 | Siemens Energy, Inc. | Turbine combustion system liner |
| US10663169B2 (en) * | 2014-07-25 | 2020-05-26 | Mitsubishi Hitachi Power Systems, Ltd. | Cylinder for combustor, combustor, and gas turbine |
-
2017
- 2017-11-15 EP EP17201913.5A patent/EP3486431B1/en active Active
-
2018
- 2018-11-15 CN CN201811359969.2A patent/CN110017178B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07198142A (en) * | 1993-12-20 | 1995-08-01 | Abb Manag Ag | Equipment for convection-cooling airtight combustion chamber |
| US20060219191A1 (en) * | 2005-04-04 | 2006-10-05 | United Technologies Corporation | Heat transfer enhancement features for a tubular wall combustion chamber |
| CN102213429A (en) * | 2010-04-09 | 2011-10-12 | 通用电气公司 | Combustor liner helical cooling apparatus |
| CN103764974A (en) * | 2011-09-27 | 2014-04-30 | 三菱重工业株式会社 | Combustor tail pipe, gas turbine with tail pipe, and method for manufacturing tail pipe |
| CN107250512A (en) * | 2015-02-24 | 2017-10-13 | 三菱日立电力系统株式会社 | Burner coldplate, the transition piece and burner that possess the burner coldplate and the gas turbine for possessing burner |
Also Published As
| Publication number | Publication date |
|---|---|
| EP3486431B1 (en) | 2023-01-04 |
| CN110017178B (en) | 2023-06-16 |
| EP3486431A1 (en) | 2019-05-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9052111B2 (en) | Turbine engine combustor wall with non-uniform distribution of effusion apertures | |
| US9316396B2 (en) | Hot gas path duct for a combustor of a gas turbine | |
| CN102242934B (en) | For burner assembly and the cooling means thereof of turbine | |
| US8516822B2 (en) | Angled vanes in combustor flow sleeve | |
| US20100186415A1 (en) | Turbulated aft-end liner assembly and related cooling method | |
| US10584878B2 (en) | Flexible swirlers | |
| CN106795812B (en) | For the heat exchange of turbine and the plate of improvement noise reduction | |
| US20090120093A1 (en) | Turbulated aft-end liner assembly and cooling method | |
| US9840924B2 (en) | Gas turbine system with a transition duct having axially extending cooling channels | |
| US20110120135A1 (en) | Turbulated aft-end liner assembly and cooling method | |
| CN101839481A (en) | The single-piece tubular type burner of cascading water cooling | |
| JP2016042014A (en) | Systems and apparatus relating to gas turbine combustors | |
| CN110017178A (en) | Hot gas path component for gas turbine | |
| KR20140012187A (en) | Thermally compliant support for a combustion system | |
| US20160320064A1 (en) | Two-stage combustor for gas turbine engine | |
| EP2578937A2 (en) | Film cooled combustion liner assembly | |
| EP2107314A1 (en) | Combustor for a gas turbine | |
| US9194586B2 (en) | Two-stage combustor for gas turbine engine | |
| KR20160108163A (en) | Sequential liner for a gas turbine combustor | |
| EP3954870B1 (en) | Transition duct for a gas turbine plant and gas turbine plant comprising said transition duct | |
| KR101557453B1 (en) | Liner including cooling structure providing double sleeve of gas turbine and cooling method thereof | |
| US11841140B2 (en) | Pre-vaporization tube for a turbine engine combustion chamber | |
| US20140047846A1 (en) | Turbine component cooling arrangement and method of cooling a turbine component |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |