CN106523043B - Gas turbine is with dividing gas path device and gas turbine - Google Patents
Gas turbine is with dividing gas path device and gas turbine Download PDFInfo
- Publication number
- CN106523043B CN106523043B CN201611189548.0A CN201611189548A CN106523043B CN 106523043 B CN106523043 B CN 106523043B CN 201611189548 A CN201611189548 A CN 201611189548A CN 106523043 B CN106523043 B CN 106523043B
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- Prior art keywords
- gas turbine
- ring cavity
- outlet
- gas
- disk body
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Classifications
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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
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/002—Cleaning of turbomachines
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of gas turbine with dividing gas path device and gas turbine, including the installation disk body for being attached on gas turbine, install disk body be provided between the upper and lower every and mutually disconnected first ring cavity and the second ring cavity, first ring cavity is provided with the first entrance for being used for importing gases at high pressure, and the connection of the first ring cavity is multiple to be used to carry out the turborotor surface of gas turbine the first outlet for purging dedusting；Second ring cavity is provided with the second entrance for being used for importing cooling gas, the multiple second outlets being used for being cooled down inside the turborotor of gas turbine of the second ring cavity connection.Instant invention overcomes existing gas turbine because of limited space, inhomogeneous cooling caused by the passage for leading to every blade can not be installed on guide vane disk, and the defects of air-channel system complexity, the present invention can realize the effect that dedusting is purged to the internal cooling and appearance of turborotor simultaneously, and simple in construction, dependable performance, there is great application value.
Description
Technical field
The present invention relates to gas turbine design field, especially, it is related to a kind of gas turbine with dividing gas path device.In addition,
The invention further relates to a kind of gas turbine for including above-mentioned point of gas path device.
Background technology
Gas turbine is in addition to main combustion gas gas circuit, in addition to many complicated gas circuits, such as cools down gas circuit, obturages gas
Road, dedusting gas circuit etc..Usual each gas circuit has each special pipeline, to reach the corresponding site of gas turbine.But
Pipeline is excessive, can cause gas turbine complicated integral structure, maintenance difficulties increase.
The turborotor of gas turbine boring works in high temperature environments, it is necessary to which cooling gas is entered to its inside
Row cooling；Blade surface needs the air of high pressure to carry out cleaning dedusting to it.Gas turbine internal structure is complicated, spaces compact,
Obviously it can not be installed on guide vane disk and lead to the breather pipe of every blade, it is necessary to redesign gas circuit to meet to require.
The content of the invention
The invention provides a kind of gas turbine with gas path device and gas turbine is divided, answered with solving existing gas circuit structure
It is miscellaneous and the technical problem for every blade being cooled down and being cleaned dedusting can not be met.
The technical solution adopted by the present invention is as follows：
According to an aspect of the present invention, there is provided a kind of gas turbine is with dividing gas path device, including for being attached to combustion gas
Installation disk body on turbine, installation disk body be provided between the upper and lower every and mutually disconnected first ring cavity and the second ring cavity, the first ring cavity
Provided with the first entrance for importing gases at high pressure, the multiple turborotor tables being used for gas turbine of the first ring cavity connection
Face purge the first outlet of dedusting；Second ring cavity is provided with the second entrance for being used for importing cooling gas, the connection of the second ring cavity
Multiple second outlets being used for being cooled down inside the turborotor of gas turbine.
Further, installation disk body is installed on gas turbine through its inner ring wall, and the first ring cavity and the second ring cavity are opened
On the outer shroud wall of installation disk body, the outer shroud wall for installing disk body obturages circle, mounting disc at the first ring cavity provided with first
The outer shroud wall of body obturages circle at the second ring cavity provided with second.
Further, first entrance is opened in first and obturaged on circle, and second entrance is opened in second and obturaged on circle.
Further, circumferential uniform intervals arrangement of multiple first outlets along installation disk body, and the first ring cavity is led through first
First outlet is communicated to passage, the first guide channel is corresponded with first outlet and set.
Further, circumferential uniform intervals arrangement of multiple second outlets along installation disk body, and the second ring cavity is led through second
Second outlet is communicated to passage, the second guide channel is corresponded with second outlet and set.
Further, first outlet and second outlet are on the same end face of installation disk body.
Further, the one end for installing disk body is provided with the annular recess for being used for being played the role of positioning when being installed with gas turbine,
Annular recess is respectively positioned on annular recess institute in the plane positioned at the inwall side of installation disk body, first outlet and second outlet.
According to another aspect of the present invention, a kind of gas turbine is also provided, sets an above-mentioned point gas circuit to fill on gas turbine
Put.
Further, the installation end of gas path device is divided facing to the turborotor of gas turbine, first outlet connection
Impact tube, purging dedusting is carried out to turborotor surface through impact tube.
Further, second outlet is communicated to through flow-guiding channel and turbine is led with the air cavity being connected inside turborotor
Cooled down to blade.
The invention has the advantages that：
Gas turbine of the present invention with dividing gas path device and gas turbine, by set two between the upper and lower every and it is mutually disconnected
First ring cavity, the second ring cavity, wherein, the first ring cavity is carried out through multiple first outlets to the turborotor surface of gas turbine
Dedusting is purged, the second ring cavity, to being cooled down inside the turborotor of gas turbine, overcomes existing through multiple second outlets
Some gas turbines are because of limited space, and cooling caused by the passage for leading to every blade can not be installed on guide vane disk is not
, and the defects of air-channel system complexity, the present invention can realize simultaneously removes to internal cooling and the appearance purging of turborotor
The effect of dirt, and simple in construction, dependable performance, there is great application value.
In addition to objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to accompanying drawings, the present invention is further detailed explanation.
Brief description of the drawings
The accompanying drawing for forming the part of the application is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not form inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the structural representation that the preferred embodiment of the present invention divides gas path device；
Fig. 2 is the close-up schematic view at A in Fig. 1；
Fig. 3 is along B-B schematic cross-sectional view in Fig. 1；
Fig. 4 is another structural representation that the preferred embodiment of the present invention divides gas path device；
Fig. 5 is the close-up schematic view at C in Fig. 4；
Fig. 6 is along D-D schematic cross-sectional view in Fig. 4；
Fig. 7 is the structural representation for dividing the ring cavity of gas path device first to work in the preferred embodiment of the present invention；
Fig. 8 is the structural representation for dividing the ring cavity of gas path device second to work in the preferred embodiment of the present invention.
Description of reference numerals：
1st, guide vane disk；
The 2nd, disk body is installed；
3rd, the first ring cavity；
4th, the second ring cavity；
5th, first entrance；
6th, first outlet；
7th, second entrance；
8th, second outlet；
9th, first circle is obturaged；
10th, second circle is obturaged；
11st, the first guide channel；
12nd, the second guide channel；
13rd, annular recess；
14th, impact tube；
15th, flow-guiding channel；
16th, turborotor.
Embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combination.Describe the present invention in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
The preferred embodiments of the present invention provide a kind of gas turbine with gas path device is divided, referring to figs. 1 to Fig. 6, this implementation
Example divides gas path device to include being used for being attached to installation disk body 2 on gas turbine, installation disk body 2 be provided between the upper and lower every and do not connect mutually
Logical the first ring cavity 3 and the second ring cavity 4, the first ring cavity 3 are provided with the first entrance 5 for being used for importing gases at high pressure, and the first ring cavity 3 connects
Logical multiple first outlets 6 for being used to carry out the turborotor surface of gas turbine purging dedusting；Second ring cavity 4, which is provided with, to be used
In the second entrance 7 for importing cooling gas, the second ring cavity 4 connects multiple be used for entering inside the turborotor of gas turbine
The second outlet 8 of row cooling.
The present embodiment by set two between the upper and lower every and mutually disconnected first ring cavity, the second ring cavity, wherein, the first ring
Chamber carries out purging dedusting to the turborotor surface of gas turbine through multiple first outlets, and the second ring cavity goes out through multiple second
Mouth overcomes existing gas turbine because of limited space, directing vane to being cooled down inside the turborotor of gas turbine
Inhomogeneous cooling caused by the passage for leading to every blade can not be installed on piece disk, and the defects of air-channel system complexity, the present invention
The effect that dedusting is purged to the internal cooling and appearance of turborotor, and simple in construction, dependable performance, tool can be realized simultaneously
There is great application value.
In the present embodiment, installation disk body 2 is installed on gas turbine through its inner ring wall, reference picture 1 and Fig. 4, the first ring
The ring cavity 4 of chamber 3 and second is opened on the outer shroud wall of installation disk body 2, installs the outer shroud wall of disk body 2 at the first ring cavity 3
Circle 9 is obturaged provided with first, the outer shroud wall of installation disk body 2 obturages circle 10 at the second ring cavity 4 provided with second.Reference picture 3 and figure
6, in the present embodiment, first entrance 5 is opened in first and obturaged on circle 9, and second entrance 7 is opened in second and obturaged on circle 10.High pressure
Gas enters in the first ring cavity 3 through first entrance 5, and cooling gas enters in the second ring cavity 4 through second entrance 7.
In the present embodiment, reference picture 2 and Fig. 3, circumferential uniform intervals of multiple first outlets 6 along installation disk body 2 are arranged, and
First ring cavity 3 is communicated to first outlet 6 through the first guide channel 11, and the first guide channel 11 is corresponded with first outlet 6 and set
Put.Each first outlet 6 carries out purging dedusting to corresponding turborotor respectively.
In the present embodiment, reference picture 5 and Fig. 6, circumferential uniform intervals of multiple second outlets 8 along installation disk body 2 are arranged, and
Second ring cavity 4 is communicated to second outlet 8 through the second guide channel 12, and the second guide channel 12 is corresponded with second outlet 8 and set
Put.Each second outlet 8 inside corresponding turborotor to cooling down.
Preferably, in the present embodiment, first outlet 6 and second outlet 8 are on the same end face of installation disk body 2 so that
Mounting disc compact overall structure.Preferably, the one end for installing disk body 2 is provided with for when being installed with gas turbine guide vane disk 1
The annular recess 13 to play the role of positioning, for annular recess 13 positioned at the inwall side of installation disk body 2, first outlet 6 and second outlet 8 are equal
Positioned at the institute of annular recess 13 in the plane.
According to another aspect of the present invention, a kind of gas turbine is also provided, point of above-described embodiment is set on gas turbine
Gas path device.
Reference picture 7, the installation end of gas path device is divided to connect facing to the turborotor 16 of gas turbine, first outlet 6
Logical impact tube 14, purging dedusting is carried out through impact tube 14 to the surface of turborotor 16.Reference picture 8, second outlet 8 is through water conservancy diversion
Passage 15 is communicated to the air cavity being connected with the inside of turborotor 16 and turborotor 16 is cooled down, wherein, water conservancy diversion
Passage 15 is on guide vane disk 1.
The present embodiment is divided to gas path device to be divided into two independent passages, and two obturaging on circle for passage respectively have an entrance.
The entrance that gases at high pressure obturage circle by upper channel enters upper strata ring cavity (i.e. the first ring cavity 3)；Cooling gas is led to by lower floor
The entrance that circle is obturaged in road enters lower floor's ring cavity (i.e. the second ring cavity 4).The collar aperture outlet of upper strata ring cavity is respectively aligned to a circle blade
The impact tube inlet on head, gases at high pressure are ejected into blade surface by impact tube and carry out purging dedusting (as shown in Figure 7)；Lower floor
One collar aperture of ring cavity exports enters blade interior by the air cavity being connected with blade interior, it is cooled down (as shown in Figure 8).
The present embodiment is divided to not connected between two ring cavities of gas path device, and independently of each other, blade is cooled down respectively so as to reach
With the effect of purging dedusting.The present embodiment divides gas path device, simple in construction, dependable performance.By cooling gas and gases at high pressure point
Open, respectively reach the function of cooling and purging dedusting.It will be understood by those skilled in the art that it can also be increased according to different needs
Ring cavity quantity.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (9)
1. a kind of gas turbine is with dividing gas path device, it is characterised in that including the installation disk body for being attached on gas turbine
(2),
The installation disk body (2) be provided between the upper and lower every and mutually disconnected first ring cavity (3) and the second ring cavity (4), described first
Ring cavity (3) is provided with the first entrance (5) for being used for importing gases at high pressure, and the first ring cavity (3) connection is multiple to be used for combustion gas wheel
The turborotor surface of machine purge the first outlet (6) of dedusting；Second ring cavity (4), which is provided with, to be used to import cooling
The second entrance (7) of gas, the second ring cavity (4) connection is multiple to be used to carry out inside the turborotor to gas turbine
The second outlet (8) of cooling；The installation disk body (2) is installed on the gas turbine through its inner ring wall, first ring
Chamber (3) and second ring cavity (4) are opened on the outer shroud wall of the installation disk body (2), outside the installation disk body (2)
Circle (9) is obturaged in ring wall face at the first ring cavity (3) place provided with first, and the outer shroud wall of the installation disk body (2) is described the
Circle (10) is obturaged provided with second in two ring cavities (4) place.
2. gas turbine according to claim 1 is with dividing gas path device, it is characterised in that
The first entrance (5) is opened in described first and obturaged on circle (9), and the second entrance (7) is opened in second envelope
On tight circle (10).
3. gas turbine according to claim 1 is with dividing gas path device, it is characterised in that
Circumferential uniform intervals of multiple first outlets (6) along the installation disk body (2) are arranged, and first ring cavity (3)
The first outlet (6), first guide channel (11) and the first outlet (6) are communicated to through the first guide channel (11)
Correspond and set.
4. gas turbine according to claim 3 is with dividing gas path device, it is characterised in that
Circumferential uniform intervals of multiple second outlets (8) along the installation disk body (2) are arranged, and second ring cavity (4)
The second outlet (8), second guide channel (12) and the second outlet (8) are communicated to through the second guide channel (12)
Correspond and set.
5. gas turbine according to claim 4 is with dividing gas path device, it is characterised in that
The first outlet (6) and the second outlet (8) are on the same end face of the installation disk body (2).
6. gas turbine according to claim 5 is with dividing gas path device, it is characterised in that
One end of the installation disk body (2) is provided with the annular recess (13) for being used for being played the role of positioning when being installed with gas turbine, institute
It is equal positioned at the inwall side of the installation disk body (2), the first outlet (6) and the second outlet (8) to state annular recess (13)
Positioned at the annular recess (13) institute in the plane.
7. a kind of gas turbine, it is characterised in that set on the gas turbine and divide gas circuit as described in claim 1 to 6 is any
Device.
8. gas turbine according to claim 7, it is characterised in that
The installation end of described point of gas path device is facing to the turborotor (16) of the gas turbine, the first outlet
(6) impact tube (14) is connected, purging dedusting is carried out to turborotor (16) surface through the impact tube (14).
9. gas turbine according to claim 8, it is characterised in that
The second outlet (8) is communicated to the air cavity being connected inside turborotor (16) to described through flow-guiding channel (15)
Turborotor (16) is cooled down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611189548.0A CN106523043B (en) | 2016-12-21 | 2016-12-21 | Gas turbine is with dividing gas path device and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611189548.0A CN106523043B (en) | 2016-12-21 | 2016-12-21 | Gas turbine is with dividing gas path device and gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN106523043A CN106523043A (en) | 2017-03-22 |
| CN106523043B true CN106523043B (en) | 2018-04-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611189548.0A Active CN106523043B (en) | 2016-12-21 | 2016-12-21 | Gas turbine is with dividing gas path device and gas turbine |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101050727A (en) * | 2007-05-09 | 2007-10-10 | 韩培洲 | Medium cooling isobaric backheating gas turbine |
| CN105065121A (en) * | 2015-07-09 | 2015-11-18 | 中国航空工业集团公司沈阳发动机设计研究所 | Disk cavity air distributor device of heavy duty gas turbine |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5934402A (en) * | 1982-08-20 | 1984-02-24 | Hitachi Ltd | Rotor device of steam turbine |
| FR2840351B1 (en) * | 2002-05-30 | 2005-12-16 | Snecma Moteurs | COOLING THE FLASK BEFORE A HIGH PRESSURE TURBINE BY A DOUBLE INJECTOR SYSTEM BOTTOM BOTTOM |
| JP3982491B2 (en) * | 2003-12-22 | 2007-09-26 | 株式会社日立製作所 | Rotating electric machine |
-
2016
- 2016-12-21 CN CN201611189548.0A patent/CN106523043B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101050727A (en) * | 2007-05-09 | 2007-10-10 | 韩培洲 | Medium cooling isobaric backheating gas turbine |
| CN105065121A (en) * | 2015-07-09 | 2015-11-18 | 中国航空工业集团公司沈阳发动机设计研究所 | Disk cavity air distributor device of heavy duty gas turbine |
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| Publication number | Publication date |
|---|---|
| CN106523043A (en) | 2017-03-22 |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |