CN105065121A - Disk cavity air distributor device of heavy duty gas turbine - Google Patents
Disk cavity air distributor device of heavy duty gas turbine Download PDFInfo
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- CN105065121A CN105065121A CN201510402289.4A CN201510402289A CN105065121A CN 105065121 A CN105065121 A CN 105065121A CN 201510402289 A CN201510402289 A CN 201510402289A CN 105065121 A CN105065121 A CN 105065121A
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- dish
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- outer cylinder
- inner barrel
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Abstract
The invention discloses a disk cavity air distributor device of a heavy duty gas turbine. The disk cavity air distributor device comprises an outer barrel (1), a middle barrel (2) and an inner barrel (3) which are sequentially arranged from outside to inside. The middle barrel (2) and the inner barrel (3) define a cavity A with a rear opening. A plug cover (4) is mounted at the front end of the outer barrel (1). A cavity B is formed among the outer barrel (1), the plug cover (4) and the middle barrel (2). A cavity C is formed in the inner barrel (3). A radial air guiding pipe (5) penetrates through the outer barrel (1), the middle barrel (2) and the inner barrel (3) in sequence, and an axial air guiding pipe (6) penetrates through the plug cover (4) and the middle barrel (2) in sequence. The disk cavity air distributor device has the beneficial effects that while safe operation of a rotor is guaranteed, three air flow channels which do not disturb one another are constructed, and streams of air flow of different temperatures and pressures are deployed, so that it is guaranteed that the streams of air flow are not mixed, and the purposes of air-guiding cooling, tight sealing and safe high-speed rotation of the rotor are achieved.
Description
Technical field
The present invention relates to gas turbine disc chamber gas flow guidance structure design field, particularly heavy duty gas turbine dish chamber air distributor apparatus.
Background technique
The gas turbine that industrial field relates to mainly comprises the large parts of gas compressor, fuel chamber and turbine three.Air is compressed into the air of High Temperature High Pressure after entering gas compressor, the burning of supply chamber fuel, high-temperature high-pressure fuel gas expansion work in turbine of generation.Wherein wheel disc, movable vane, axle and attached rotatable parts are referred to as rotor, and other non-rotatable members are referred to as stator.
During gas turbine work, gas turbine body temperature can raise gradually, especially Turbine section, and turbine parts, except selecting comparatively except good material, also need the safety and the life-span that are ensured combustion engine by the Cooling Design of complexity.Generally at present bleed from gas compressor to cool turbine, so the whether reasonable efficiency to gas turbine of Cooling Design has a significant impact in the gas turbine.
And the cooling of heavy duty gas turbine high-temperature rotor parts, obturaging etc. needs to draw three strands of cross one another high pressure low temperature air-flows from mechanism of qi position in dish chamber, and temperature, pressure is all not identical.In the rotor disk chamber not occurring High Rotation Speed in the past, bleed multiply is intersected mutually, and the situation that temperature, pressure is all not identical.
Summary of the invention
The object of the invention is to the shortcoming overcoming prior art, provide a kind of ensure rotor safe operation while, structure three non-interfering air-flow paths heavy duty gas turbine dish chamber air distributor apparatus.
Object of the present invention is achieved through the following technical solutions: heavy duty gas turbine dish chamber air distributor apparatus, comprise the outer cylinder body along setting gradually from outside to inside, middle cylinder and inner barrel, and radial guiding tracheae, axial air pipe, dish A, dish B and dish C, middle cylinder is connected with the forward end seal of inner barrel, preferably, on front side of inner barrel 8, cylinder is positioned on middle cylinder, thus middle cylinder and inner barrel surround the cavity A of after-opening, the front end of outer cylinder body is provided with blanking cover, thus outer cylinder body and form cavity B between blanking cover and middle cylinder, the inside of inner barrel forms cavity C, radial guiding tracheae is successively through outer cylinder body, middle cylinder and inner barrel, and radial guiding tracheae and outer cylinder body, be between middle cylinder and inner barrel and be tightly connected, dish A and dish B are installed on the outer cylinder body on the outer cylinder body on the left of radial conduit and on the right side of radial conduit respectively, thus be communicated with cavity C and dish A by radial guiding tracheae and coil the space of the outer cylinder body outside between B, dish C be installed on be positioned at dish B on rear side of middle cylinder on, axial air pipe is successively through blanking cover and middle cylinder, axial air pipe and being between blanking cover and middle cylinder is tightly connected, thus be communicated with blanking cover space outerpace and cavity A by axial air pipe.
The present invention constructs three isolated, non-interfering air-flow paths mutually by said structure:
Passage one: the air-flow entered on rear side of inner barrel is isolated through cavity A and cavity B through radial guiding tracheae, flow to the space of the outer cylinder body outside between dish A and dish B.
Passage two: the air-flow entered from blanking cover bottom flows successively along cavity B, and flow through from the outside of axial air pipe and radial guiding tracheae successively, and finally flow between dish B and dish C.
Passage three: the air-flow warp beam entered from blanking cover top, to air pipe, is completely cut off through cavity B by axial air pipe, entered cavity A, and flow along cavity A, flow through in cavity A from the outside of radial guiding tracheae, and finally flow to the space on rear side of dish C.
Realize the allotment to the air-flow of each stock different temperatures, pressure, ensure its not blending mutually, guarantee that rotor safety high speed rotates.
Preferably, the rear end of outer cylinder body is connected and fixed by bolt and dish B, is also bolted fixing between outer cylinder body and dish A, thus by outer cylinder body closed disk A, dish B disk chamber.
Preferably, the rear end of middle cylinder is provided with gear shaping, and the wing grafting that middle cylinder is stretched out in dish C by gear shaping is fixed.
Preferably, blanking cover is fastened by bolts on outer cylinder body.
Preferably, the rear end of described middle cylinder is positioned at the rear side of outer cylinder body, and the rear end of inner barrel is positioned at the rear side of middle cylinder.
Circumferentially be evenly equipped with six radial guiding tracheaes, the mounting structure of each radial guiding tracheae is identical, all successively through outer cylinder body, middle cylinder and inner barrel; Circumferentially be evenly equipped with four axial air pipes, the mounting structure of each axial air pipe is identical, all successively through blanking cover and middle cylinder.For ensureing that air distributor apparatus does not affect rotor high-speed running, the air pipe that distributor is arranged, fastening piece are all that circumference is uniform, and matrix is all cylinder.After distributor assembling, dynamic balancing is carried out to it
Described radial guiding tracheae upper end portion is left boss and is coordinated with the radial hole inwall of outer cylinder body, and air pipe stretches out outer wall 1mm, and circumferentially 6 uniform enlargings are fixed.
The present invention has the following advantages:
The present invention is arranged in the rotor disk chamber of high speed spinning, while ensureing rotor safe operation, construct three non-interfering air-flow paths, allocate the air-flow of each stock different temperatures, pressure, ensure its mutually not blending, realize bleed cooling, obturage and object that rotor safety high speed rotates.Economic, practical, save cost greatly, achieve the object of the mutual not blending of multiply crosscurrent.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention
In figure, 1-outer cylinder body, 2-middle cylinder, 3-inner barrel, 4-blanking cover, 5-radial guiding tracheae, the axial air pipe of 6-, 7-dish A, 8-dish B, 9-dish C.
Embodiment
Below in conjunction with accompanying drawing, the present invention will be further described:
As shown in Figure 1, heavy duty gas turbine dish chamber air distributor apparatus, comprise the outer cylinder body 1 along setting gradually from outside to inside, middle cylinder 2 and inner barrel 3, and radial guiding tracheae 5, axial air pipe 6, dish A7, dish B8 and dish C9, middle cylinder 2 is connected with the forward end seal of inner barrel 3, preferably, on front side of inner barrel 38, cylinder is positioned on middle cylinder 2, thus middle cylinder 2 and inner barrel 3 surround the cavity A of after-opening, the front end of outer cylinder body 1 is provided with blanking cover 4, thus outer cylinder body 1 and form cavity B between blanking cover 4 and middle cylinder 2, the inside of inner barrel 3 forms cavity C, radial guiding tracheae 5 is successively through outer cylinder body 1, middle cylinder 2 and inner barrel 3, and radial guiding tracheae 5 and outer cylinder body 1, be between middle cylinder 2 and inner barrel 3 and be tightly connected, dish A7 and dish B8 are installed on the outer cylinder body 1 on the outer cylinder body 1 on the left of radial conduit and on the right side of radial conduit respectively, thus be communicated with cavity C and dish A7 by radial guiding tracheae 5 and coil the space of outer cylinder body 1 outside between B8, dish C9 be installed on be positioned at dish B8 on rear side of middle cylinder 2 on, axial air pipe 6 is successively through blanking cover 4 and middle cylinder 2, axial air pipe 6 and being between blanking cover 4 and middle cylinder 2 is tightly connected, thus be communicated with blanking cover 4 space outerpace and cavity A by axial air pipe 6.
The present invention constructs three isolated, non-interfering air-flow paths mutually by said structure:
Passage one: the air-flow entered on rear side of inner barrel 3 is isolated through cavity A and cavity B through radial guiding tracheae 5, flow to the space of outer cylinder body 1 outside between dish A7 and dish B8.
Passage two: the air-flow entered from blanking cover 4 bottom flows successively along cavity B, and flow through from the outside of axial air pipe 6 and radial guiding tracheae 5 successively, and finally flow between dish B8 and dish C9.
Passage three: the air-flow warp beam entered from blanking cover 4 top, to air pipe 6, is completely cut off through cavity B by axial air pipe 6, entered cavity A, and flow along cavity A, flow through in cavity A from the outside of radial guiding tracheae 5, and finally flow to the space on rear side of dish C9.
Realize the allotment to the air-flow of each stock different temperatures, pressure, ensure its not blending mutually, guarantee that rotor safety high speed rotates.
Preferably, the rear end of outer cylinder body 1 is connected and fixed by bolt and dish B8, is also bolted fixing between outer cylinder body 1 and dish A7, thus by outer cylinder body 1 closed disk A7, dish B8 disk chamber.
Preferably, the rear end of middle cylinder 2 is provided with gear shaping, and the wing grafting that middle cylinder 2 is stretched out in dish C9 by gear shaping is fixed.
Preferably, blanking cover 4 is fastened by bolts on outer cylinder body 1.
Preferably, the rear end of described middle cylinder 2 is positioned at the rear side of outer cylinder body 1, and the rear end of inner barrel 3 is positioned at the rear side of middle cylinder 2.
Circumferentially be evenly equipped with six radial guiding tracheaes 5, the mounting structure of each radial guiding tracheae 5 is identical, all successively through outer cylinder body 1, middle cylinder 2 and inner barrel 3; Circumferentially be evenly equipped with four axial air pipes 6, the mounting structure of each axial air pipe 6 is identical, all successively through blanking cover 4 and middle cylinder 2.For ensureing that air distributor apparatus does not affect rotor high-speed running, the air pipe that distributor is arranged, fastening piece are all that circumference is uniform, and matrix is all cylinder.After distributor assembling, dynamic balancing is carried out to it
Described radial guiding tracheae 5 upper end portion is left boss and is coordinated with the radial hole inwall of outer cylinder body 1, and air pipe stretches out outer wall 1mm, and circumferentially 6 uniform enlargings are fixed.
Claims (5)
1. heavy duty gas turbine dish chamber air distributor apparatus, it is characterized in that: comprise the outer cylinder body (1) along setting gradually from outside to inside, middle cylinder (2) and inner barrel (3), and radial guiding tracheae (5), axial air pipe (6), dish A (7), dish B (8) and dish C (9), middle cylinder (2) is connected with the forward end seal of inner barrel (3), middle cylinder (2) and inner barrel (3) surround the cavity A of after-opening, the front end of outer cylinder body (1) is provided with blanking cover (4), outer cylinder body (1) and form cavity B between blanking cover (4) and middle cylinder (2), the inside of inner barrel (3) forms cavity C, radial guiding tracheae (5) is successively through outer cylinder body (1), middle cylinder (2) and inner barrel (3), dish A (7) and dish B (8) are installed on the outer cylinder body (1) on the outer cylinder body (1) on the left of radial conduit and on the right side of radial conduit respectively, dish C (9) be installed on be positioned at dish B (8) rear side middle cylinder (2) on, axial air pipe (6) is successively through blanking cover (4) and middle cylinder (2).
2. heavy duty gas turbine dish chamber according to claim 1 air distributor apparatus, it is characterized in that: the rear end of described outer cylinder body (1) is connected and fixed by bolt and dish B (8), is also bolted fixing between outer cylinder body (1) and dish A (7).
3. heavy duty gas turbine dish chamber according to claim 1 air distributor apparatus, it is characterized in that: the rear end of described middle cylinder (2) is provided with gear shaping, the wing grafting that middle cylinder (2) is stretched out in dish C (9) by gear shaping is fixed.
4. heavy duty gas turbine dish chamber according to claim 1 air distributor apparatus, is characterized in that: described blanking cover (4) is fastened by bolts on outer cylinder body (1).
5. heavy duty gas turbine dish chamber according to claim 1 air distributor apparatus, it is characterized in that: be circumferentially evenly equipped with six radial guiding tracheaes (5), the mounting structure of each radial guiding tracheae (5) is identical; Circumferentially be evenly equipped with four axial air pipes (6), the mounting structure of each axial air pipe (6) is identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510402289.4A CN105065121A (en) | 2015-07-09 | 2015-07-09 | Disk cavity air distributor device of heavy duty gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510402289.4A CN105065121A (en) | 2015-07-09 | 2015-07-09 | Disk cavity air distributor device of heavy duty gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105065121A true CN105065121A (en) | 2015-11-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510402289.4A Pending CN105065121A (en) | 2015-07-09 | 2015-07-09 | Disk cavity air distributor device of heavy duty gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN105065121A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106523043A (en) * | 2016-12-21 | 2017-03-22 | 中国南方航空工业(集团)有限公司 | Branched gas circuit device for gas turbine and gas turbine |
| CN110566515A (en) * | 2019-09-22 | 2019-12-13 | 中国航发沈阳发动机研究所 | gas-entraining structure on inner side of gas compressor |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5472313A (en) * | 1991-10-30 | 1995-12-05 | General Electric Company | Turbine disk cooling system |
| CN1514111A (en) * | 2003-07-16 | 2004-07-21 | 沈阳黎明航空发动机（集团）有限责任 | Turbine machine matched with gas turbine |
| CN101178029A (en) * | 2006-11-10 | 2008-05-14 | 通用电气公司 | Interstage cooled turbine engine |
| CN101631931A (en) * | 2007-03-12 | 2010-01-20 | 西门子公司 | Turbine comprising at least one rotor that consists of rotor disks and a tie bolt |
-
2015
- 2015-07-09 CN CN201510402289.4A patent/CN105065121A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5472313A (en) * | 1991-10-30 | 1995-12-05 | General Electric Company | Turbine disk cooling system |
| CN1514111A (en) * | 2003-07-16 | 2004-07-21 | 沈阳黎明航空发动机（集团）有限责任 | Turbine machine matched with gas turbine |
| CN101178029A (en) * | 2006-11-10 | 2008-05-14 | 通用电气公司 | Interstage cooled turbine engine |
| CN101631931A (en) * | 2007-03-12 | 2010-01-20 | 西门子公司 | Turbine comprising at least one rotor that consists of rotor disks and a tie bolt |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106523043A (en) * | 2016-12-21 | 2017-03-22 | 中国南方航空工业(集团)有限公司 | Branched gas circuit device for gas turbine and gas turbine |
| CN106523043B (en) * | 2016-12-21 | 2018-04-03 | 中国南方航空工业(集团)有限公司 | Gas turbine is with dividing gas path device and gas turbine |
| CN110566515A (en) * | 2019-09-22 | 2019-12-13 | 中国航发沈阳发动机研究所 | gas-entraining structure on inner side of gas compressor |
| CN110566515B (en) * | 2019-09-22 | 2020-12-18 | 中国航发沈阳发动机研究所 | Gas-entraining structure on inner side of gas compressor |
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Application publication date: 20151118 |
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