CN106523043A - Branched gas circuit device for gas turbine and gas turbine - Google Patents
Branched gas circuit device for gas turbine and gas turbine Download PDFInfo
- Publication number
- CN106523043A CN106523043A CN201611189548.0A CN201611189548A CN106523043A CN 106523043 A CN106523043 A CN 106523043A CN 201611189548 A CN201611189548 A CN 201611189548A CN 106523043 A CN106523043 A CN 106523043A
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- China
- Prior art keywords
- gas turbine
- gas
- outlet
- ring cavity
- disk body
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- 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.)
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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
- 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 branched gas circuit device for a gas turbine and the gas turbine. The branched gas circuit device for the gas turbine comprises an installation disc body which is used for being installed on the gas turbine. The installation disc body is provided with a first annular cavity and a second annular cavity, and the first annular cavity and the second annular cavity are spaced in the vertical direction and do not communicate. The first annular cavity is provided with a first inlet used for guiding in high-pressure gas and communicates with a plurality of first outlets which are used for purging and dedusting of the surfaces of turbine guide blades of the gas turbine. The second annular cavity is provided with a second inlet used for guiding in cooling gas and communicates with a plurality of second outlets which are used for cooling of the interiors of the turbine guide blades of the gas turbine. By adoption of the branched gas circuit device for the gas turbine and the gas turbine, the defects that in the prior art, since the space of a gas turbine is limited, air holes leading to all blades cannot be formed in a guide blade disc, and consequentially cooling is nonuniform and a gas circuit system is complex are overcome; the effects of cooling the interiors of the turbine guide blades and purging and dedusting the outer surfaces of the turbine guide blades can be achieved at the same time; and the branched gas circuit device for the gas turbine is simple in structure and reliable in performance and has extremely high application and popularization value.
Description
Technical field
The present invention relates to gas turbine design field, especially, is related to a kind of gas turbine point gas path device.Additionally,
The invention further relates to a kind of gas turbine including above-mentioned point of gas path device.
Background technology
Gas turbine also including many complicated gas circuits, such as cools down gas circuit, gas of obturaging in addition to main combustion gas gas circuit
Road, dedusting gas circuit etc..Generally each gas circuit has each special pipeline, to reach the corresponding site of gas turbine.But
Pipeline is excessive, and gas turbine complicated integral structure, maintenance difficulties can be caused to increase.
The turborotor of gas turbine boring is worked in high temperature environments, needs cooling gas to enter its inside
Row cooling；Blade surface needs the air of high pressure to carry out cleaning dedusting to which.Gas turbine internal structure is complicated, spaces compact,
The breather for leading to every blade obviously cannot be installed on guide vane disk, needs to redesign gas circuit to meet requirement.
The content of the invention
The invention provides a kind of gas turbine point gas path device and a gas turbine, multiple to solve existing gas circuit structure
It is miscellaneous, and the technical problem that dedusting is cooled down and cleaned to every blade cannot be met.
The technical solution used in the present invention is as follows：
According to an aspect of the present invention, there is provided an a kind of gas turbine point gas path device, including for being attached to combustion gas
Installation disk body on turbine, install 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
It is provided with for importing the first entrance of gases at high pressure, the first ring cavity connects multiple turborotor tables for gas turbine
Face carries out the first outlet for purging dedusting；Second ring cavity is provided with for importing the second entrance of cooling gas, the connection of the second ring cavity
The second outlet cooled down inside multiple turborotors for gas turbine.
Further, its internal ring wall of installation disk body Jing is installed on gas turbine, and the first ring cavity and the second ring cavity are opened
On the outer shroud wall for installing disk body, the outer shroud wall for installing disk body is provided with first at the first ring cavity and obturages circle, mounting disc
The outer shroud wall of body is provided with second at the second ring cavity and obturages circle.
Further, first entrance is opened in first and obturages on circle, and second entrance is opened in second and obturages on circle.
Further, multiple first outlets are led along the circumferential uniform intervals arrangement for installing disk body, and the first ring cavity Jing first
To channel connection to first outlet, the first guide channel is corresponded with first outlet and is arranged.
Further, multiple second outlets are led along the circumferential uniform intervals arrangement for installing disk body, and the second ring cavity Jing second
To channel connection to second outlet, the second guide channel is corresponded with second outlet and is arranged.
Further, first outlet and second outlet are located on the same end face for installing disk body.
Further, the annular recess played the role of positioning when one end of installation disk body is provided with for being installed with gas turbine,
Annular recess is located at the inwall side for installing disk body, and first outlet and second outlet are respectively positioned on annular recess institute in the plane.
According to a further aspect in the invention, a kind of gas turbine is also provided, above-mentioned point gas circuit dress is set on gas turbine
Put.
Further, the turborotor of the installation end of gas path device facing to gas turbine, first outlet connection are divided
Impact tube, Jing impact tubes carry out purging dedusting to turborotor surface.
Further, second outlet Jing flow-guiding channel is communicated to the air cavity being connected with inside turborotor and turbine is led
Cooled down to blade.
The invention has the advantages that：
Gas turbine of the present invention point gas path device and a gas turbine, by arrange two between the upper and lower every and it is mutually disconnected
First ring cavity, the second ring cavity, wherein, the first many of ring cavity Jing first outlets are carried out to the turborotor surface of gas turbine
Purging dedusting, the second many of ring cavity Jing second outlets are overcome existing to cooling down inside the turborotor of gas turbine
Some gas turbines are cooled down not caused by the passage for leading to every blade cannot be installed on guide vane disk because of limited space
, and the complicated defect of air-channel system, the present invention can realize that the internal cooling to turborotor and appearance purging are removed simultaneously
The effect of dirt, and simple structure, dependable performance, with 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.
Description of the drawings
The accompanying drawing for constituting the part of the application is used for providing a further understanding of the present invention, the schematic reality of the present invention
Apply example and its illustrate, for explaining the present invention, not constituting inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the structural representation of the preferred embodiment of the present invention point gas path device；
Fig. 2 is the close-up schematic view in Fig. 1 at A；
Fig. 3 is the cross-sectional schematic in Fig. 1 along B-B；
Fig. 4 is another structural representation of the preferred embodiment of the present invention point gas path device；
Fig. 5 is the close-up schematic view in Fig. 4 at C；
Fig. 6 is the cross-sectional schematic in Fig. 4 along D-D；
Fig. 7 is the structural representation of point the first ring cavity of gas path device work in the preferred embodiment of the present invention；
Fig. 8 is the structural representation of point the second ring cavity of gas path device work in the preferred embodiment of the present invention.
Description of reference numerals：
1st, guide vane disk；
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 obturage circle；
10th, second obturage circle；
11st, the first guide channel；
12nd, the second guide channel；
13rd, annular recess；
14th, impact tube；
15th, flow-guiding channel；
16th, turborotor.
Specific embodiment
It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase
Mutually combine.Below with reference to the accompanying drawings and in conjunction with the embodiments describing the present invention in detail.
The preferred embodiments of the present invention provide a kind of gas turbine point gas path device, referring to figs. 1 to Fig. 6, this enforcement
Example point gas path device includes the installation disk body 2 for being attached on gas turbine, install disk body 2 be provided between the upper and lower every and mutually do not connect
The first logical ring cavity 3 and the second ring cavity 4, the first ring cavity 3 are provided with for importing the first entrance 5 of gases at high pressure, and the first ring cavity 3 connects
Logical multiple first outlets 6 for purging dedusting is carried out to the turborotor surface of gas turbine；Second ring cavity 4 is provided with use
In the second entrance 7 for importing cooling gas, the second ring cavity 4 is connected and is entered inside multiple turborotors for gas turbine
The second outlet 8 of row cooling.
The present embodiment by arrange two between the upper and lower every and mutually disconnected first ring cavity, the second ring cavity, wherein, the first ring
Jing many first outlets in chamber carry out purging dedusting to the turborotor surface of gas turbine, and the second ring cavity Jing many second goes out
Mouth overcomes existing gas turbine because of limited space, directing vane to cooling down inside the turborotor of gas turbine
Cannot install on piece disk and lead to inhomogeneous cooling caused by the passage of every blade, and the defect that air-channel system is complicated, the present invention
Can realize that the internal cooling to turborotor and appearance purge the effect of dedusting, and simple structure, dependable performance, tool simultaneously
There is great application value.
In the present embodiment, 2 Jing of disk body its internal ring wall is installed and is installed on gas turbine, with reference to Fig. 1 and Fig. 4, the first ring
Chamber 3 and the second ring cavity 4 are opened on the outer shroud wall for installing disk body 2, and the outer shroud wall of installation disk body 2 is at the first ring cavity 3
It is provided with first to obturage circle 9, the outer shroud wall for installing disk body 2 is provided with second at the second ring cavity 4 and obturages circle 10.With reference to Fig. 3 and figure
6, in the present embodiment, first entrance 5 is opened in first and obturages on circle 9, and second entrance 7 is opened in second and obturages on circle 10.High pressure
Gas Jing first entrances 5 are entered in the first ring cavity 3, and cooling gas Jing second entrance 7 is entered in the second ring cavity 4.
In the present embodiment, with reference to Fig. 2 and Fig. 3, multiple first outlets 6 are arranged along the circumferential uniform intervals for installing disk body 2, and
First ring cavity, 3 the first guide channels of Jing 11 are communicated to first outlet 6, 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, with reference to Fig. 5 and Fig. 6, multiple second outlets 8 are arranged along the circumferential uniform intervals for installing disk body 2, and
Second ring cavity, 4 the second guide channels of Jing 12 are communicated to second outlet 8, and the second guide channel 12 is corresponded with second outlet 8 and set
Put.Each second outlet 8 is to cooling down inside corresponding turborotor.
Preferably, in the present embodiment, first outlet 6 and second outlet 8 are located on the same end face for installing disk body 2 so that
Mounting disc compact overall structure.Preferably, when one end of installation disk body 2 is provided with for being installed with gas turbine guide vane disk 1
The annular recess 13 for playing the role of positioning, annular recess 13 are located at the inwall side for installing disk body 2, and first outlet 6 and second outlet 8 are equal
Positioned at 13 institute of annular recess in the plane.
According to a further aspect in the invention, a kind of gas turbine is also provided, dividing for above-described embodiment is set on gas turbine
Gas path device.
With reference to Fig. 7, the turborotor 16 of the installation end of gas path device facing to gas turbine, first outlet 6 is divided to connect
Logical impact tube 14, Jing impact tubes 14 carry out purging dedusting to 16 surface of turborotor.With reference to Fig. 8,8 Jing water conservancy diversion of second outlet
Passage 15 is communicated to and turborotor 16 is cooled down with the air cavity being connected inside turborotor 16, 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, respectively has an entrance on the circle of obturaging of two passages.
Gases at high pressure by upper channel obturage circle entrance enter upper strata ring cavity (i.e. the first ring cavity 3)；Cooling gas are logical by lower floor
Road obturage circle entrance enter lower floor's ring cavity (i.e. the second ring cavity 4).The one collar aperture outlet of upper strata ring cavity is respectively aligned to a circle blade
The impact tube inlet of 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
The one collar aperture outlet of ring cavity enters blade interior by the air cavity being connected with blade interior, and (as shown in Figure 8) is cooled down to which.
The present embodiment is divided to not connected between two ring cavities of gas path device, separate, blade is cooled down respectively so as to reach
With the effect of purging dedusting.The present embodiment point gas path device, simple structure, dependable performance.By cooling gas and gases at high pressure point
Open, respectively reach cooling and purge the function of dedusting.It will be understood by those skilled in the art that can also be increased according to different needs
Ring cavity quantity.
The preferred embodiments of the present invention are the foregoing is only, the present invention is not limited to, for the skill of this area
For art personnel, the present invention can have various modifications and variations.It is all within the spirit and principles in the present invention, made any repair
Change, equivalent, improvement etc., should be included within the scope of the present invention.
Claims (10)
1. a kind of gas turbine is used and divides a gas path device, it is characterised in that include the installation disk body for being attached on gas turbine
(2), 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 for importing the first entrance (5) of gases at high pressure, and the first ring cavity (3) connection is multiple for combustion gas wheel
The turborotor surface of machine carries out the first outlet (6) for purging dedusting；Second ring cavity (4) is provided with for importing cooling
The second entrance (7) of gas, second ring cavity (4) connects to be carried out inside multiple turborotors for gas turbine
The second outlet (8) of cooling.
2. gas turbine according to claim 1 is used and divides a gas path device, it is characterised in that
Described its internal ring wall of installation disk body (2) Jing is installed on the gas turbine, first ring cavity (3) and described second
Ring cavity (4) is opened on the outer shroud wall for installing disk body (2), and the outer shroud wall for installing disk body (2) is described the
One ring cavity (3) place is provided with first and obturages circle (9), and the outer shroud wall for installing disk body (2) is provided with the second ring cavity (4) place
Second obturages circle (10).
3. gas turbine according to claim 2 is used and divides a gas path device, it is characterised in that
The first entrance (5) is opened in described first and obturages on circle (9), and the second entrance (7) is opened in second envelope
On tight circle (10).
4. gas turbine according to claim 2 is used and divides a gas path device, it is characterised in that
Multiple first outlets (6) are arranged along the circumferential uniform intervals for installing disk body (2), and first ring cavity (3)
The first guide channels of Jing (11) is communicated to the first outlet (6), first guide channel (11) and the first outlet (6)
Correspond and arrange.
5. gas turbine according to claim 4 is used and divides a gas path device, it is characterised in that
Multiple second outlets (8) are arranged along the circumferential uniform intervals for installing disk body (2), and second ring cavity (4)
The second guide channels of Jing (12) is communicated to the second outlet (8), second guide channel (12) and the second outlet (8)
Correspond and arrange.
6. gas turbine according to claim 5 is used and divides a gas path device, it is characterised in that
The first outlet (6) and the second outlet (8) are on the same end face for installing disk body (2).
7. gas turbine according to claim 6 is used and divides a gas path device, it is characterised in that
The annular recess (13) that described one end for installing disk body (2) is played the role of positioning when being provided with for being installed with gas turbine, institute
Annular recess (13) is stated positioned at the inwall side for installing disk body (2), the first outlet (6) and the second outlet (8) are
Positioned at the annular recess (13) institute in the plane.
8. a kind of gas turbine, it is characterised in that point gas circuit as described in claim 1 to 7 is arbitrary is set on the gas turbine
Device.
9. gas turbine according to claim 8, it is characterised in that
Turborotor (16) of the installation end of described point of gas path device facing to the gas turbine, the first outlet
(6) impact tube (14) is connected, impact tube (14) carries out purging dedusting to turborotor (16) surface described in Jing.
10. gas turbine according to claim 9, it is characterised in that
The second outlet (8) Jing flow-guiding channels (15) is communicated to the air cavity being connected inside turborotor (16) to described
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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106523043A true CN106523043A (en) | 2017-03-22 |
| CN106523043B CN106523043B (en) | 2018-04-03 |
Family
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Family Applications (1)
| 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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| Country | Link |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5934402A (en) * | 1982-08-20 | 1984-02-24 | Hitachi Ltd | Rotor device of steam turbine |
| US20030223893A1 (en) * | 2002-05-30 | 2003-12-04 | Snecma Moteurs | Cooling the upstream end plate of a high pressure turbine by means of a system of dual injectors at the end of the combustion chamber |
| US20050135927A1 (en) * | 2003-12-22 | 2005-06-23 | Kengo Iwashige | Dynamo-electric machine |
| 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 |
-
2016
- 2016-12-21 CN CN201611189548.0A patent/CN106523043B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5934402A (en) * | 1982-08-20 | 1984-02-24 | Hitachi Ltd | Rotor device of steam turbine |
| US20030223893A1 (en) * | 2002-05-30 | 2003-12-04 | Snecma Moteurs | Cooling the upstream end plate of a high pressure turbine by means of a system of dual injectors at the end of the combustion chamber |
| US20050135927A1 (en) * | 2003-12-22 | 2005-06-23 | Kengo Iwashige | Dynamo-electric machine |
| 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 |
|---|---|
| CN106523043B (en) | 2018-04-03 |
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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. |
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