CN106812556B - A kind of gas turbine hot junction cooling structure and with its gas turbine - Google Patents
A kind of gas turbine hot junction cooling structure and with its gas turbine Download PDFInfo
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- CN106812556B CN106812556B CN201710156584.5A CN201710156584A CN106812556B CN 106812556 B CN106812556 B CN 106812556B CN 201710156584 A CN201710156584 A CN 201710156584A CN 106812556 B CN106812556 B CN 106812556B
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- cooling cover
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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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of gas turbine hot junction cooling structure and with its gas turbine, annular cooling cover plate is set on cirele bend, the back side of cooling cover plate sets floor passage, the cooling air-flow imported by the cooling air-flow hole on cirele bend is impacted at the back side of cooling cover plate, cooling cover plate is quickly cooled down, while also reduces the fuel gas temperature of cooling cover plate front near zone；Then cooling air-flow flow further downstream cools down the installation side of gas turbine guider.Since the floor passage at the cooling cover plate back side generates the effect of approximate pressure stabilizing cavity, cooling air-flow blending can be made uniform, one layer of cooling air film is formed on the surface on guider installation side, significantly improves cooling effect.Cooling air-flow continues flow further downstream, and protective effect is also formed to the outer flow passage surface of gas turbine guider.By using the structure, it can play and be obviously improved turbine cooling effect, extend turbine, especially gas turbine guider service life.
Description
Technical field
The present invention relates to high-temperature component of gas turbine turbine cooling fields, more specifically, are using new structure, improve
Numbers of hot-side engine secondary air system flow road form.By using the structure, it can play and be obviously improved turbine cooling effect, show
Writing reduces the purpose of turbine pneumatic loss, extends turbine, especially gas turbine guider service life, so as to improve turbine
Can, promote engine competitiveness.
Background technology
Modern gas turbines in order to improve its performance, increase motor power, improve engine efficiency, turbine inlet temperature
Constantly promoted.It is generally believed that turbine inlet temperature often improves 55 DEG C, motor power can about increase by 10%.At present, it is advanced
Engine, turbine inlet temperature can even reach 2000K, considerably beyond the fusing point of current all alloys.Increasingly improve
Turbine inlet temperature so that the high-temperature components such as turbine must not be not subject to the thermic load and living load of bigger in engine, cause it
Working environment severe exacerbation, consequence are engine reliability reductions, and the service life shortens.According to statistics, breakdown in the motor, 60%
It appears above in high-temperature component, and has the trend constantly risen in recent years.To find out its cause, one is a lack of pair the reason for important
High-temperature component is effectively cooled down.
At engine hot parts end, what ultra-high temperature was influenced maximum before by turbine is gas turbine guider.From burning
The high-temperature high-pressure fuel gas of room outflow will be directly impacted on gas turbine guider surface, its thermal force is caused to increased dramatically, work
It is extremely severe to make environment；Meanwhile influenced by gas turbine guider inlet and outlet and channel inner pressure, gas turbine guider will
It can be subject to larger axial load, this burst of motive force needs to install side to engine installation section biography by gas turbine guider
It passs.Therefore, in order to ensure the safe operation of engine, it is ensured that the reliably working of gas turbine guider is particularly important.
In existing engine, it is common practice to, ring arranges circumferential cooling air film hole in the combustion chamber, so as to reach
To the purpose on protection guider installation side.But this method, cooling air-flow are emitted directly toward in mainstream and are blended with mainstream, not only
Cooling effect is poor, and larger disturbance is brought to mainstream, affects the aeroperformance of turbine；In addition, cool down gas in design
During fenestra, cooling air film hole is very little, cooling effect unobvious；It is overstocked to cool down air film hole, although cooling effect can be improved,
Difficulty of processing is improved, while reduces the intensity of combustion chamber inner ring.In order to solve the problems, such as this, cooling effect is improved, further
Engine performance is improved, there is an urgent need for a kind of relatively reliable types of cooling.
The content of the invention
In view of the shortcomings of the prior art and deficiency, the present invention is intended to provide a kind of gas turbine hot junction cooling structure and having
Its gas turbine for the cooling layout type of high-temperature component of gas turbine, especially gas turbine guider installation side, leads to
It crosses using the novel cooling structure, optimization secondary air system flow road improves cooling effect, aerodynamic loss reduced, so as to improve
Engine performance.
To realize the target, the technical solution adopted by the present invention is：
A kind of gas turbine hot junction cooling structure, including gas turbine guider, cirele bend and cooling cover plate, the combustion
Air turbine guider is arranged on the exit of gas-turbine combustion chamber, which is characterized in that
The outer shroud side of the cirele bend is provided with first step portion and second step portion, the first step portion it is outer
Footpath is more than the outer diameter in second step portion, and the first step portion is set close to the top of the cirele bend, described second
Rank portion is set close to the bottom of the cirele bend,
The cooling cover plate is whole in a ring, and the annular cooling cover plate is fixed and is hermetically set in the cirele bend
First step portion on, wherein, it is described annular cooling cover plate thickness and the first step portion thickness it is substantially suitable, it is described
Annular cooling cover plate is fixed on after the first step portion, the outer surface of the annular cooling cover plate and the cirele bend
It is smooth between pneumatic outer surface to smoothly transit,
It is formed between the annular back side of cooling cover plate and the second step portion of the cirele bend and the combustion gas is installed
Nozzle ring installs the card slot on side, the width of the card slot and the basic phase of thickness on gas turbine guider installation side
When, the installation side of the gas turbine guider is fixed and is hermetically set in the second step portion of the cirele bend,
The back side of the annular cooling cover plate is provided with circumferentially uniformly distributed floor, is formed and is evenly distributed between adjacent floor
Floor passage, be arranged circumferentially several cooling air-flow holes along it in the second step portion of the cirele bend, it is described cold
But the radial height of airflow hole is more than the radial height on the installation side of the gas turbine guider, to ensure by the cooling gas
The cooling air-flow that discharge orifice imports is not lived by the installation side bumper of gas turbine guider, the cooling gas imported by the cooling air-flow hole
Jet impulse is flowed at the back side of the annular cooling cover plate, and the annular cooling cover plate is quickly cooled down, is reduced simultaneously
The fuel gas temperature of annular cooling cover plate front near zone, cooling air-flow flow further downstream afterwards, in the gas turbine
The outer surface on the installation side of guider forms one layer of cooling air film and it is cooled down, and cooling air-flow continues flow further downstream,
The outer flow passage surface of the gas turbine guider is cooled down.
The gas turbine hot junction cooling structure of the present invention, operation principle are：
During gas turbine operation, the high-temperature fuel gas from combustion chamber flows into gas turbine guider, causes combustion gas
The operating ambient temperature of nozzle ring is very high, and then generates larger thermic load.The present invention passes through in the cirele bend
First step portion on the annular cooling cover plate is set, and floor passage is set at the back side of the annular cooling cover plate, leads to
The cooling air-flow hole jet impulse crossed in the second step portion that the cooling air-flow from air system passes through the cirele bend exists
The back side (including floor surface and floor passage surface) of annular cooling cover plate, is quickly cooled down annular cooling cover plate, really
The trouble free service of annular cooling cover plate is protected, while also reduces the fuel gas temperature of annular cooling cover plate front near zone；Then
Cooling air-flow flow further downstream cools down the installation side of gas turbine guider.Due to the rib at the annular cooling cover plate back side
Board channel generates the effect of approximate pressure stabilizing cavity, cooling air-flow blending can be made uniform, the table on gas turbine guider installation side
One layer of cooling air film is formed on face, significantly improves cooling effect.Cooling air-flow continues flow further downstream, and gas turbine is led
Protective effect is also formed to the outer flow passage surface of device, (cooling cover plate is positive since mainstream combustion gas has already passed through once cooling
Cooling), therefore fuel gas temperature decreases.Cooling air film is further formed second protection at this time, it is ensured that gas turbine guider
Outer flow passage trouble free service.
More preferably, the floor at the annular cooling cover plate back side, circumferential quantity are not less than 3.
Selectively, the floor is straight floor, tilts floor, aerofoil profile floor or other forms.
More preferably, smooth flat, and the smooth flat and the back of the body are designed as at the high radius in front of the annular cooling cover plate
The floor surface in face should meet certain depth of parallelism requirement, to ensure the assembling of cooling cover plate.
More preferably, lead-in chamfered is designed as at the relatively low radius in front of the annular cooling cover plate, and it is cold with the annular
But the smooth flat fairing switching at the high radius in front of cover board, to avoid the pneumatic structures such as shock wave or dilatational wave are generated, increases
Add aerodynamic loss.
More preferably, the front of the annular cooling cover plate, should ensure that surface roughness requirements, to reduce the frictional heat of air-flow
Effect.
More preferably, the annular cooling cover plate is fixed on the first step portion of the cirele bend by welding
On.
More preferably, when welding manner is selected to fix, the thickness of the annular cooling cover plate is slightly less than the cirele bend
First step portion width, and should polish after having welded welding position, prevent that there are local crownings.
Selectively, bolted mode can also be used, and that the annular cooling cover plate is fixed on the annular is curved
In the first step portion of pipe.
More preferably, when being connected by screw bolts mode, the thickness of the annular cooling cover plate on the cirele bend with using
Width in the first step portion of installation cooling cover plate is equal.
More preferably, when being connected by screw bolts mode, bolt hole should be designed at the back side of the annular cooling cover plate, to keep away
Exempt from stud protrusion structure to be in sprue, increase aerodynamic loss.
More preferably, the width of the card slot slightly larger than gas turbine guider installation side thickness, with ensure can be with
Gas turbine guider installation side is fixed on to the second step portion composition of the annular cooling cover plate and cirele bend
In card slot, interference will not be generated to assembling due to crossing positioning.
More preferably, the back side of the installation side of gas turbine guider and the annular cooling cover plate, the cirele bend
Meet certain flatness and depth of parallelism requirement between the counterface in second step portion, to ensure that the optimal use of the present invention is imitated
Fruit.
More preferably, the cooling air-flow hole number on the cirele bend is no less than 3.
According to another aspect of the present invention, the present invention also provides a kind of combustion gas wheels with above-mentioned hot junction cooling structure
Machine.
The gas turbine hot junction cooling structure of the present invention and with its gas turbine, improves combustion gas whirlpool in gas turbine
The type of cooling of guider is taken turns, compared with prior art, at least with following significant technique effect：
It 1), can be with since the cooling air-flow that cooling air-flow hole sprays into is not emitted directly toward in the high temperature mainstream of gas turbine
Reduce the pneumatic mixing loss of cooling air-flow and high temperature mainstream；
2) cooling air-flow to the back side of annular cooling cover plate impact cold by the cooling air-flow hole on cirele bend
But, heat exchange efficiency can be increased substantially, while also reduces the mainstream temperature near annular cooling cover plate front outer flow passage；
3) cooling air-flow cools down the installation side of gas turbine guider by the floor passage of annular cooling cover plate,
Floor passage plays the role of similar pressure stabilizing cavity, and cooling air-flow can be made more uniform, significantly improve cooling effect；
4) cooling air-flow is along casing flow further downstream outside gas turbine guider, outer runner wall surface be formed about one layer it is cold
But air film plays a protective role to the outer shroud of entire gas turbine guider；
5) since cooling effect significantly improves, gas turbine guider installation side or even outer flow passage can be reduced
Thermal stress ensures that there are enough mechanical strengths on installation side, so as to improve the reliability of engine and security.
Description of the drawings
Fig. 1 is the gas turbine hot junction cooling structure schematic diagram of the present invention；
Fig. 2 is the cooling cover plate front view of the present invention；
Fig. 3 is the cooling cover plate I partial enlarged views of the present invention；
Fig. 4 is the cooling cover plate B-B sectional views of the present invention；
Fig. 5 is the cooling cover plate schematic diagram with aerofoil profile floor.
Specific embodiment
To make the objectives, technical solutions, and advantages of the present invention more comprehensible, develop simultaneously embodiment referring to the drawings, right
The present invention is further described, and following embodiment is explanation of the invention and the invention is not limited in following embodiments.
As shown in Figure 1, the gas turbine hot junction cooling structure of the present invention, including cooling cover plate 1, cirele bend 2 and combustion gas
Nozzle ring 3, gas turbine guider 3 are arranged on the exit of gas-turbine combustion chamber.The outer shroud side of cirele bend 2 is set
First step portion 201 and second step portion 202 are equipped with, the outer diameter in first step portion 201 is more than the outer diameter in second step portion 202,
And first step portion 201 is set close to the top of cirele bend 2, second step portion 202 is set close to the bottom of cirele bend 2.
Cooling cover plate 1 is whole in a ring, and annular cooling cover plate 1 is fixed and is hermetically set in the first step portion 201 of cirele bend 2
On, wherein, the thickness of annular cooling cover plate 1 and the thickness in first step portion 201 are substantially suitable, and annular cooling cover plate 1 is fixed on
It is smooth between the outer surface of annular cooling cover plate 1 and the pneumatic outer surface of cirele bend 2 to smooth out after first step portion 201
It crosses.Installation gas turbine guider peace is formed between the back side of annular cooling cover plate 1 and the second step portion 202 of cirele bend 2
The card slot of rim 301, the width of card slot is substantially suitable with the thickness on gas turbine guider installation side 301, and gas turbine is oriented to
Device installation side 301 is fixed and is hermetically set in the second step portion 202 of cirele bend.The back side of annular cooling cover plate 1 is set
Circumferentially uniformly distributed floor 101 is equipped with, the floor passage 102 being evenly distributed is formed between adjacent floor 101, cirele bend 2
Several cooling air-flow holes 203 are arranged circumferentially along it in second step portion 202, the radial height in cooling air-flow hole 203 is big
Radial height in gas turbine guider installation side 301, to ensure the cooling air-flow imported by cooling air-flow hole not by combustion gas
The installation side 301 of nozzle ring is blocked, by the cooling air-flow jet impulse that cooling air-flow hole imports in annular cooling cover plate 1
The back side is quickly cooled down annular cooling cover plate 1, while reduces the combustion gas temperature of annular 1 front near zone of cooling cover plate
Degree, cooling air-flow flow further downstream, forms one layer of cooling air film in the outer surface on the installation side 301 of gas turbine guider afterwards
And it is cooled down, cooling air-flow continues flow further downstream, and the outer flow passage surface of gas turbine guider 3 is cooled down.
Preferably, cooling cover plate 1 is fixed on cirele bend 2 by welding or bolt connecting mode.When using weldering
When the mode of connecing fixes cooling cover plate 1, the thickness of cooling cover plate 1 should be slightly less than the width in first step portion 201, to ensure to weld
Afterwards, the face height that weld bead height is not above cirele bend 2 is met by polishing.When the mode of being connected by screw bolts fixes cooling
During cover board 1, the thickness of cooling cover plate 1 can be equal with the width in first step portion 201, but it is ensured that first step portion 201
Obturaging between cooling cover plate 1, prevents cooling air-flow from leaking into mainstream at this.Therefore welding manner company is recommended
It connects, it is ensured that there is no leakages between cooling cover plate 1 and first step portion 201.
To avoid assembling positioning, the width on the installation side 301 of gas turbine guider 3 should be slightly less than second step 202
Width.Circumferentially uniformly distributed cooling air-flow hole 203 is designed on cirele bend 2, and to ensure that flow path is unimpeded, cooling air-flow
The position in hole 203 should be above the radial location on gas turbine guider installation side 301.
Fig. 2 is the front view of cooling cover plate, shows the back side rib structure of cooling cover plate；Fig. 3 is the office of cooling cover plate
Portion's enlarged drawing.Circumferentially uniformly distributed floor 101 is designed at the cooling cover plate back side.Wherein floor can be designed as straight floor, such as Fig. 3
It is shown, it is also designed to tilt the arbitrary other forms such as floor, aerofoil profile floor, if Fig. 5 is the cooling cover plate with aerofoil profile floor
Schematic diagram.At the cooling cover plate back side, the floor passage 102 being evenly distributed is formed between floor 101.
Fig. 4 is the B-B sectional views of cooling cover plate.As shown in the figure, it is designed at the high radius in front of cooling cover plate smooth
Plane 103 is designed with lead-in chamfered 105 at low radius, is connected between smooth flat 103 and lead-in chamfered 105 by rounding 104
It connects.All these measures are to reduce the flow losses of air-flow.
In Fig. 1, solid line with the arrow represents gas turbine high temperature mainstream glide path, and dotted line with the arrow represents cooling
The glide path of air-flow.During gas turbine operation, the high-temperature fuel gas from combustion chamber flows into gas turbine guider 3,
The operating ambient temperature for causing gas turbine guider 3 is very high, and then generates larger thermic load.At this point, from air system
The cooling air-flow of system is by 203 jet impulse of cooling air-flow hole in the back side of cooling cover plate 1 (floor surface 101 and floor passage
Surface 102), cooling cover plate 1 is quickly cooled down, it is ensured that the trouble free service of cooling cover plate 1, while also reduce cooling cover plate
The fuel gas temperature of 1 front near zone；Then cooling air-flow flow further downstream, to the installation side 301 of gas turbine guider into
Row cooling.Since floor passage 102 generates the effect of approximate pressure stabilizing cavity, cooling air-flow blending can be made uniform, in gas turbine
The surface on the installation side 301 of guider forms one layer of cooling air film, significantly improves cooling effect.Cooling air-flow continues downward
Trip flowing, also forms protective effect, since mainstream combustion gas has already passed through once to the outer flow passage surface of gas turbine guider 3
It cools down (the positive cooling of cooling cover plate), therefore fuel gas temperature decreases.Cooling air film is further formed second protection at this time,
Ensure the trouble free service of the outer flow passage of gas turbine guider 3.
In conclusion the present invention improves the cooling on gas turbine guider installation side by using new cooling structure
Mode can greatly improve cooling effect, and replace conveniently, only by changing the i.e. adjustable cooling effect of cooling cover plate.
It can be promoted in modern gas turbines structure, there is energetically impetus for the raising of engine performance.
Furthermore, it is necessary to illustrate, the specific embodiment described in this specification, the shape of parts and components is named
Title etc. can be different.The equivalent or simple change that all construction, feature and principles according to described in inventional idea of the present invention are done, is wrapped
It includes in the protection domain of patent of the present invention.Those skilled in the art can be to described specific implementation
Example is done various modifications or additions or is substituted in a similar way, without departing from structure of the invention or surmounts this
Scope as defined in the claims, is within the scope of protection of the invention.
Claims (14)
1. a kind of gas turbine hot junction cooling structure, including gas turbine guider, cirele bend and cooling cover plate, the combustion gas
Nozzle ring is arranged on the exit of gas-turbine combustion chamber, which is characterized in that
The outer shroud side of the cirele bend is provided with first step portion and second step portion, and the outer diameter in the first step portion is big
Outer diameter in second step portion, and the first step portion is set close to the top of the cirele bend, the second step portion
It is set close to the bottom of the cirele bend,
The cooling cover plate is whole in a ring, and the cooling cover plate is fixed and is hermetically set in the First of the cirele bend
In rank portion, wherein, the thickness in the thickness of the cooling cover plate and the first step portion is substantially suitable, and the cooling cover plate is fixed
It is smooth flat between the outer surface of the cooling cover plate and the pneumatic outer surface of the cirele bend after the first step portion
Suitable transition,
It is formed between the back side of the cooling cover plate and the second step portion of the cirele bend and the gas turbine guiding is installed
The card slot on the installation side of device, the width of the card slot is substantially suitable with the thickness on the installation side of the gas turbine guider, institute
The installation side for stating gas turbine guider is fixed and is hermetically set in the second step portion of the cirele bend,
The back side of the cooling cover plate is provided with circumferentially uniformly distributed floor, and the floor being evenly distributed is formed between adjacent floor and is led to
Road is arranged circumferentially several cooling air-flow holes, the cooling air-flow hole in the second step portion of the cirele bend along it
Height be more than the gas turbine guider installation side height, by the cooling air-flow hole import cooling air-flow jet stream
It impacts at the back side of the cooling cover plate, the cooling cover plate is quickly cooled down, while reduce the outer of the cooling cover plate
The fuel gas temperature of near-surface region, cooling air-flow flow further downstream afterwards, on the installation side of the gas turbine guider
Outer surface forms one layer of cooling air film and it is cooled down, and cooling air-flow continues flow further downstream, and the gas turbine is led
It is cooled down to the outer flow passage surface of device.
2. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that the back side of the cooling cover plate
Floor, circumferential quantity are not less than 3.
3. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that the floor is straight floor, inclines
Cant timber or aerofoil profile floor.
4. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that the outer surface of the cooling cover plate
Higher position at be designed as smooth flat, and the smooth flat and the floor surface at the back side of the cooling cover plate should meet one
Fixed depth of parallelism requirement, to ensure the assembling of cooling cover plate；It is designed as drawing at the lower position of the outer surface of the cooling cover plate
Guiding incline, and transfer with the smooth flat fairing at the higher position of the outer surface of the cooling cover plate, to avoid shock wave is generated
Or dilatational wave, increase aerodynamic loss.
5. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that the appearance of the cooling cover plate
Face should ensure that surface roughness requirements, to reduce the friction fuel factor of air-flow.
6. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that the cooling cover plate passes through welding
Mode be fixed in the first step portion of the cirele bend.
7. gas turbine hot junction according to claim 6 cooling structure, which is characterized in that fixed selecting welding manner
When, the thickness of the cooling cover plate is slightly less than the thickness in the first step portion of the cirele bend, and tackles welding after having welded
Position is polished, and prevents that there are local crownings.
8. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that the mode being connected by screw bolts will
The cooling cover plate is fixed in the first step portion of the cirele bend.
9. gas turbine hot junction according to claim 8 cooling structure, which is characterized in that be connected by screw bolts mode
When, the thickness in first step portion of the thickness of the cooling cover plate with being used to install cooling cover plate on the cirele bend is equal.
10. gas turbine hot junction according to claim 9 cooling structure, which is characterized in that when being connected by screw bolts mode,
Bolt hole should be designed at the back side of the cooling cover plate, be in avoid stud protrusion structure in sprue, increase pneumatic damage
It loses.
11. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that the width of the card slot is bigger
Thickness in the installation side of the gas turbine guider, to ensure the installation side of the gas turbine guider being fixed on institute
In the card slot for stating the second step portion composition of cooling cover plate and cirele bend, interference will not be generated to assembling due to crossing positioning.
12. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that the gas turbine guider
Installation side and the back side of the cooling cover plate, the cirele bend second step portion counterface between meet it is certain
Flatness and depth of parallelism requirement.
13. gas turbine hot junction according to claim 1 cooling structure, which is characterized in that cold on the cirele bend
But air-flow hole number is no less than 3.
14. a kind of gas turbine of the hot junction cooling structure with described in any of the above-described claim.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710156584.5A CN106812556B (en) | 2017-03-16 | 2017-03-16 | A kind of gas turbine hot junction cooling structure and with its gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710156584.5A CN106812556B (en) | 2017-03-16 | 2017-03-16 | A kind of gas turbine hot junction cooling structure and with its gas turbine |
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| CN106812556B true CN106812556B (en) | 2018-05-25 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112324577B (en) * | 2020-10-22 | 2021-08-17 | 中国航发沈阳发动机研究所 | Outer runner location structure |
| CN116293817A (en) * | 2023-03-10 | 2023-06-23 | 中国航发湖南动力机械研究所 | Bent pipe structure in combustion chamber and gas turbine engine |
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|---|---|---|---|---|
| EP1813869A2 (en) * | 2006-01-25 | 2007-08-01 | Rolls-Royce plc | Wall elements for gas turbine engine combustors |
| EP1818612A1 (en) * | 2006-02-10 | 2007-08-15 | Snecma | Annular combustion chamber of a turbomachine |
| CN103061889A (en) * | 2013-01-17 | 2013-04-24 | 中国科学院工程热物理研究所 | Thermal insulating structure |
| EP2947296A1 (en) * | 2014-04-04 | 2015-11-25 | United Technologies Corporation | Angled gas turbine combustor rail cooling holes |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110185739A1 (en) * | 2010-01-29 | 2011-08-04 | Honeywell International Inc. | Gas turbine combustors with dual walled liners |
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2017
- 2017-03-16 CN CN201710156584.5A patent/CN106812556B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1813869A2 (en) * | 2006-01-25 | 2007-08-01 | Rolls-Royce plc | Wall elements for gas turbine engine combustors |
| EP1818612A1 (en) * | 2006-02-10 | 2007-08-15 | Snecma | Annular combustion chamber of a turbomachine |
| CN103061889A (en) * | 2013-01-17 | 2013-04-24 | 中国科学院工程热物理研究所 | Thermal insulating structure |
| EP2947296A1 (en) * | 2014-04-04 | 2015-11-25 | United Technologies Corporation | Angled gas turbine combustor rail cooling holes |
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| CN106812556A (en) | 2017-06-09 |
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