CN102644484B - Gas turbine engine - Google Patents
Gas turbine engine Download PDFInfo
- Publication number
- CN102644484B CN102644484B CN201110038937.4A CN201110038937A CN102644484B CN 102644484 B CN102644484 B CN 102644484B CN 201110038937 A CN201110038937 A CN 201110038937A CN 102644484 B CN102644484 B CN 102644484B
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- China
- Prior art keywords
- rail
- cooling
- section
- motor
- radially
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to gas turbine engine, it comprises portion's section that annular draws guide vane assembly, middle part is used to guide on engine rotor blade by hot combustion gas at motor, portion's section comprises platform, platform relative to engine revolution axis by radially-inwardly/to being placed on section side, portion, the hot combustion gas flowing that platform has with respect to portion's section is in the rear edge part in downstream, rear edge part comprises from its radially-inwardly/outward extending rail, motor also comprises support and cooling unit guides cooling fluid to carry out cooling part section with supporting portion section, device is positioned at the inner radial/outside of platform, device comprises the vibrating part from its radially outward/extend internally, it is characterized in that device also comprises plate leaf Sealing and at least one retaining pin, retaining pin extends through plate leaf Sealing, rail and vibrating part are to be fixed to device and to carry out the radial position of determination portion section and retaining plate leaf Sealing is in place enters to stop cooling fluid with the interface sealed between rail and vibrating part by portion's section.
Description
Technical field
The present invention relates to gas turbine engine.
More specifically, the present invention relates to the gas turbine engine comprising annular and draw portion's section of guide vane assembly, in use engine process, hot combustion gas is directed on the rotor blade of motor by this section, this section comprise relative to motor spin axis by radially-inwardly/to the platform of side being placed on described portion section, the flowing had with respect to the hot combustion gas of portion's section of described platform is in the rear edge part in downstream, described rear edge part comprise from rear edge part radially-inwardly/outward extending rail, described motor also comprises support and cooling unit guides cooling fluid to carry out cooling part section for supporting portion section, this device is placed in described platform inner radial/outside, this device comprises the vibrating part from this device radially outward/extend internally.
Background technique
Need to simplify this gas turbine engine.
Summary of the invention
According to the present invention, provide a kind of gas turbine engine, it comprises portion's section that annular draws guide vane assembly, in motor using process, hot combustion gas is directed on the rotor blade of motor by this section, this section comprise relative to motor spin axis by radially-inwardly/to the platform of side being placed on described portion section, the flowing had with respect to the hot combustion gas of portion's section of described platform is in the rear edge part in downstream, described rear edge part comprise from rear edge part radially-inwardly/outward extending rail, described motor also comprises support and cooling unit guides cooling fluid to carry out cooling part section for supporting portion section, this device is placed in described platform inner radial/outside, this device comprises the vibrating part from this device radially outward/extend internally, it is characterized in that described device also comprises plate leaf Sealing and at least one retaining pin, described retaining pin extends through described plate leaf Sealing, described rail and described vibrating part, thus (i) described portion section is fixed on described device to determine the radial position of described portion section, and (ii) keep described plate leaf Sealing to be in the position that enters to stop cooling fluid, interface between the described rail of sealing and described vibrating part.
Accompanying drawing explanation
Describe the present invention referring now to accompanying drawing by example, this accompanying drawing releases for the figure of the parts of gas turbine engine according to the present invention.
Embodiment
With reference to accompanying drawing, the annular that the parts of gas turbine engine comprise motor draw guide vane assembly portion's section 1, support and cooling unit 3 and rotor 5.The spin axis of motor can horizontal-extending and can be placed in the below of part shown in figure in the accompanying drawings.Rotor 5 comprises the rotor blade 9 with root of blade 7.Rotor 5 also comprises rotor disk (not shown), and rotor blade 9 is fixed to this rotor disk by means of its rotor hub 7.The hot combustion gas of advancing is directed on rotor blade 9 by portion's section 1 as shown by the directional arrows a in the diagram.Can find out, figures only show the inner radial of portion's section 1 and the parts at rear, illustrate only support and the radially outer of cooling unit 3 and the parts at rear, and illustrate only rotor blade 9 comprise the inner radial of its root of blade 7 and the parts in front.
Portion's section 1 comprises the platform 13 drawing guide vane 11 and the radially inner side place in portion's section 1.Portion's section 1 can also comprise one or more additional platform drawing guide vane 11 and the radial outside in portion's section 1.Allly draw that guide vane is all radial between radial inner platform and outer platform to be extended.Radial inner platform and outer platform will be arcuate form.The view of the portion's section 1 shown in figure is that circumferentially direction is observed.
As known in the art, complete annular is drawn guide vane assembly and is comprised multiple the sections 1 being arranged to ring or annular.Therefore, in the accompanying drawings, the plane of annular is perpendicular to the vertical plane of paper plane, there is portion's section 1, its contiguous and as shown in the figure the below of paper plane and above (namely circumferentially direction) extend continuously with portion's section 1.
The platform 13 flowing A had with respect to the hot combustion gas of portion's section 1 is in the rear edge part 15 in downstream.Hinder marginal part section 15 comprises rail 17, and it is from part 15, extend radially inwardly from the radially-inwardly directed face 19 of platform 13.
Rail 17 is illustrated as the bottom at accompanying drawing in the perspective.In this perspective view, rail 17 compared to its in the accompanying drawings top orientation be inverted.The final rear tip 21 that rail 17 is parallel to part 15 along rear edge part 15 extends.Therefore, rail 17 extends to ground in motor inner circumferential.Circumferential lengths/the degree of rail 17 is same as the circumferential lengths/degree of platform 13 substantially.Although the rail 17 illustrated is straight in stereogram, but in fact its slight curve in case its pedestal 22 locate along the radially-inwardly directed face 19 of its length and platform 13 in syntople (platform 13 be certainly also slightly bend circumferentially to extend and there is radius, as known in the art).The height of rail 17 is different along its length, and rail 17 is included in the convex portion 23 of every one end and the depression 25 between part 23.Part 23 comprises hole 27.Depression 25 makes rail 17 easily bend with the bending of platform 13.
Rear edge part 15 comprises passage 28, and it extends to the face 30 of the radially outward orientation of platform 13 at roughly downstream direction from the radially-inwardly directed face 19 of platform 13.
Support and cooling unit 3 supporting portion section 1 and guide cooling fluid with cooling part section 1.Device 3 is positioned at platform 13 inner radial.Device 3 comprises load-carrying ring 29, sheet metal leaf Sealing 31, two retaining pin 33(only illustrate one of them in the drawings) and cooling plate 35.
Load-carrying ring 29 comprises vibrating part, and it comprises main flange and time flange 37,39, and described main flange and time flange 37,39 extend radially outwardly from load-carrying ring 29.The thickness of time flange 39 reduces thus creates the recessed region 41 that the periphery around load-carrying ring 29 extends compared with main flange 37.The load-carrying ring 29 comprising its flange 37,39 is centered on the spin axis of motor.In the accompanying drawings, the plane of load-carrying ring 29 is perpendicular to the vertical plane of paper plane.
Plate leaf Sealing 31 extends in paper and outside paper, and has the length substantially identical with the rail 17 of portion's section 1.
Retaining pin 33 extends through plate leaf Sealing 31, afterwards by the hole 27 in the convex portion 23 of rail 17, and enters (position of the hole 43 in secondary flange 39 corresponds to the hole 27 in rail 17) in the hole 43 in time flange 39 afterwards.Pin 33 has the interference fit/interference fit with one in rail 17 and time flange 39, and has the drive fit slightly loose with the ratio interference fit of the another one in rail 17 and time flange 39.Pin 33 and plate leaf Sealing 31 have the cooperation of relative pine.
Cooling plate 35 is placed in just in parallel below the radially-inwardly directed face 19 of platform 13, thus is formed in the cooling channel 45 between plate 35 and face 19.Portion's section 1 comprises the additional rail (not shown) parallel with rail 17, and it extends radially inwardly from the leading edge portion (not shown) of platform 13.The downstream of cooling plate 35 is positioned at rail 17 and the upstream extremity (not shown) of plate is positioned at described additional rail.Cooling plate 35 comprises multiple cooling hole 47.
Cooling fluid is supplied in the upstream of main flange and secondary flange 37 and 39, rail 17, plate leaf Sealing 31 and retaining pin 33, be present in chamber 49 between load-carrying ring 29 and portion's section 1.The jet of the radially outward orientation of cooling fluid is formed by the cooling hole 47 in cooling plate 35.The radially-inwardly directed face 19 of these impinging jets chill station 13.Some cooling fluids in cooling channel 45 are advanced through platform 13 as shown by arrow B and arrive and draw the inside of guide vane 11, and some cooling fluids are advanced via the passage 28 in rear edge part 15 thus the face 30 of the radially outward orientation of overlay film cooling (filmcool) platform 13 at the parts of the downstream part of the outlet of leaving channel 28.In addition, cooling fluid is supplied to the region 51 between load-carrying ring 29 and rotor blade 9, as arrow C indication.This fluid is come in conjunction with the fluid of leaving channel 28 approximately towards up in the drawings.
Retaining pin 33 has dual functions: portion's section 1 is (i) fixed to load-carrying ring 29 thus the radial position of determination portion section 1 by them, and (ii) retaining plate leaf Sealing 31 is in the position sealing the interface 53 between rail 17 and flange 37,39 and enter from chamber 49 to stop cooling fluid.This dual functions of retaining pin 33 parts simplifies portion's section 1 and the junction form between support with cooling unit 3.In addition, advantageously, plate leaf Sealing 31 achieves the sealing at interface 53 and can not increase the rigidity of platform 13 significantly.
Rail 17 recessed district 41 circumferentially extends, and the upstream face of the finger of rail 17 55 is positioned at and flushes (being in same level) with the upstream face 57 of the finger of main flange 37.Surface plate leaf Sealing 31 is positioned to against the face 55 and 57 flushed and interface 53 between bridge joint rail 17 and flange 37,39.The face 59 in the sensing downstream of rail 17 is relative with the finger upstream face 61 of time flange 39.
The diameter of the hole 27 in rail 17 and the hole 43 in time flange 39 corresponds to the diameter of the axle of retaining pin 33, and therefore hole 27,43 is formed the circumferential position not only determining radius but also determination portion section 1.If need the circumferential position allowing adjusting portion section 1, then this can be realized by the groove making the hole 27,43 in rail 17 and/or in secondary flange 39 comprise circumference extension.The radial direction of portion's section 1 and circumferential position can be determined, and do not have the Zhou Xiangre of constriction section 1 to increase, this is realized by following feature: the hole 27,43 relevant in two retaining pins 33 has the diameter of the diameter of the axle corresponding to retaining pin, and comprises the circumferential groove extended to another either one or two the relevant hole 27,43 in two retaining pins 33.
Foregoing description relates to the platform that annular draws portion's section of guide vane assembly, and wherein this platform is placed in the radially inner side of described portion section.It is to be appreciated that the present invention also can be used to the platform of portion's section of drawing guide vane assembly about annular, wherein this platform is placed in the radial outside of described portion section.This example can be as follows: (a) is similar to the support of device 3 and cooling unit will be positioned at platform radially outer and will comprise the flange being similar to flange 37,39, described flange extends radially inwardly from described device, and the rear edge part of (b) platform will comprise the rail extended radially outwardly from rear edge part being similar to rail 17.
Foregoing description relates to portion's section that annular draws guide vane assembly, and wherein multiple sections are configured to ring or annular thus form complete annular draw guide vane assembly.Should be appreciated that, in the limit case, portion's section can be that complete annular draws guide vane assembly, wherein only needs portion's section to draw guide vane assembly to construct complete annular, and namely complete annular is drawn guide vane assembly and is made up of the only portion's section itself being whole ring or annular.
Claims (20)
1. a gas turbine engine, comprise: annular draws portion's section (1) of guide vane assembly, in described motor using process, hot combustion gas is directed on the rotor blade (9) of motor by this section (1), described portion section (1) comprises and is radially-inwardly arranged at the platform (13) of the side in described portion section (1) relative to the spin axis of motor, described platform (13) flowing had with respect to the hot combustion gas in described portion section (1) is in the rear edge part (15) in downstream, described rear edge part (15) comprises the rail (17) extended radially inwardly from described rear edge part (15), described motor also comprise support and cooling unit (3) for supporting described portion section (1) guide cooling fluid to cool described portion section (1), described support and cooling unit (3) are positioned at the inner radial of described platform (13), described support and cooling unit (3) comprise the vibrating part (37 extended radially outwardly from described support and cooling unit (3), 39), it is characterized in that: described support and cooling unit (3) also comprise plate leaf Sealing (31) and at least one retaining pin (33), described retaining pin (33) extends through described plate leaf Sealing (31), described rail (17) and described vibrating part (37, 39), thus (i) described portion section (1) is fixed to described support and cooling unit (3) to determine the radial position in described portion section (1), and (ii) keep described plate leaf Sealing (31) to be in the described rail of sealing (17) and described vibrating part (37, 39) position that the interface (53) between stops cooling fluid to enter.
2., wherein there are two or more retaining pins (33) in motor according to claim 1.
3. according to motor according to claim 1 or claim 2, wherein said retaining pin (33) extends through the hole (27,43) in described rail (17) and vibrating part (37,39), and described hole (27,43) is formed the circumferential position determining described portion section (1).
4. according to motor according to claim 1 or claim 2, wherein said retaining pin (33) extends through the groove that the circumference in described rail (17) and/or vibrating part (37,39) extends, thus allows the circumferential position regulating described portion section (1).
5. according to motor according to claim 1 or claim 2, wherein said support and cooling unit (3) comprise the load-carrying ring (29) be centered on the described spin axis of described motor, described vibrating part (37, 39) the main flange (37) extended radially outwardly from described load-carrying ring (29) and time flange (39) is comprised, described flange (39) has the thickness of reduction compared with described main flange (37), thus produce the recessed district (41) extended around the periphery of described load-carrying ring (29), described rail (17) extends along the recessed district (41) that described periphery extends.
6. motor according to claim 5, upstream of the finger (55) of wherein said rail (17) and the finger upstream (57) of described main flange (37) are positioned at same level, and described plate leaf Sealing (31) is plane form and rail (17) and the interface (53) between described main flange and secondary flange (37,39) described in upstream of the described finger (55,57) be positioned to against described rail (17) and main flange (37) and bridge joint.
7. motor according to claim 5, wherein said support and cooling unit (3) comprise chamber (49), described cooling fluid is fed into this chamber (49), and described chamber (49) are positioned between described load-carrying ring (29) and described portion section (1) in the upstream of described main flange and time flange (37,39), described rail (17), described plate leaf Sealing (31) and described retaining pin (33).
8. motor according to claim 7, wherein said rear edge part (15) comprises first passage (28), this first passage (28) edge roughly downstream direction extends to the face (30) of the radially outward orientation of described platform (13) from the radially-inwardly directed face (19) of described platform (13), the cooling fluid being supplied to described chamber (49) in described motor using process enters described first passage (28), to advance along described first passage (28) at roughly downstream direction and leave described first passage (28) thus the parts at outlet downstream place of described first passage (28) are being left in the overlay film face (30) that cools described radially outward orientation.
9. motor according to claim 8, wherein said support and cooling unit (3) comprise cooling plate (35), this cooling plate (35) is disposed adjacent to and face (19) radially-inwardly directed described in being parallel to, thus second channel (45) is formed between described cooling plate (35) and described radially-inwardly directed face (19), described cooling plate (35) comprises multiple cooling hole (47), hole (47) is formed the radially outward orientation of cooling fluid jet by the cooling fluid being supplied to described chamber (49) is cooled described in described motor using process, described jet collides and face (19) radially-inwardly directed described in cooling, cooling fluid from described second channel (45) enters described first passage (28).
10. motor according to claim 1, wherein there are two retaining pins (33), described rail (17) is included in the convex portion (23) of every one end and the depression (25) between described convex portion (23), and each convex portion (23) comprises hole (27), corresponding one in described two retaining pins (33) extends through this hole (27).
11. 1 kinds of gas turbine engines, comprise: annular draws portion's section (1) of guide vane assembly, in described motor using process, hot combustion gas is directed on the rotor blade (9) of motor by this section (1), described portion section (1) spin axis comprised relative to motor is arranged at the platform (13) of the side in described portion section (1) by radially outward, described platform (13) flowing had with respect to the hot combustion gas in described portion section (1) is in the rear edge part (15) in downstream, described rear edge part (15) comprises the rail (17) extended radially outwardly from described rear edge part (15), described motor also comprise support and cooling unit (3) for supporting described portion section (1) guide cooling fluid to cool described portion section (1), described support and cooling unit (3) are positioned at the radially outer of described platform (13), described support and cooling unit (3) comprise the vibrating part (37 extended radially inwardly from described support and cooling unit (3), 39), it is characterized in that: described support and cooling unit (3) also comprise plate leaf Sealing (31) and at least one retaining pin (33), described retaining pin (33) extends through described plate leaf Sealing (31), described rail (17) and described vibrating part (37, 39), thus (i) described portion section (1) is fixed to described support and cooling unit (3) to determine the radial position in described portion section (1), and (ii) keep described plate leaf Sealing (31) to be in the described rail of sealing (17) and described vibrating part (37, 39) position that the interface (53) between stops cooling fluid to enter.
, wherein there are two or more retaining pins (33) in 12. motors according to claim 11.
13. according to claim 11 or motor according to claim 12, wherein said retaining pin (33) extends through the hole (27,43) in described rail (17) and vibrating part (37,39), and described hole (27,43) is formed the circumferential position determining described portion section (1).
14. according to claim 11 or motor according to claim 12, and wherein said retaining pin (33) extends through the groove that the circumference in described rail (17) and/or vibrating part (37,39) extends, thus allows the circumferential position regulating described portion section (1).
15. according to claim 11 or motor according to claim 12, wherein said support and cooling unit (3) comprise the load-carrying ring (29) be centered on the described spin axis of described motor, described vibrating part (37, 39) the main flange (37) extended radially outwardly from described load-carrying ring (29) and time flange (39) is comprised, described flange (39) has the thickness of reduction compared with described main flange (37), thus produce the recessed district (41) extended around the periphery of described load-carrying ring (29), described rail (17) extends along the recessed district (41) that described periphery extends.
16. motors according to claim 15, upstream of the finger (55) of wherein said rail (17) and the finger upstream (57) of described main flange (37) are positioned at same level, and described plate leaf Sealing (31) is plane form and rail (17) and the interface (53) between described main flange and secondary flange (37,39) described in upstream of the described finger (55,57) be positioned to against described rail (17) and main flange (37) and bridge joint.
17. motors according to claim 15, wherein said support and cooling unit (3) comprise chamber (49), described cooling fluid is fed into this chamber (49), and described chamber (49) are positioned between described load-carrying ring (29) and described portion section (1) in the upstream of described main flange and time flange (37,39), described rail (17), described plate leaf Sealing (31) and described retaining pin (33).
18. motors according to claim 17, wherein said rear edge part (15) comprises first passage (28), this first passage (28) edge roughly downstream direction extends to the face (30) of the radially outward orientation of described platform (13) from the radially-inwardly directed face (19) of described platform (13), the cooling fluid being supplied to described chamber (49) in described motor using process enters described first passage (28), to advance along described first passage (28) at roughly downstream direction and leave described first passage (28) thus the parts at outlet downstream place of described first passage (28) are being left in the overlay film face (30) that cools described radially outward orientation.
19. motors according to claim 18, wherein said support and cooling unit (3) comprise cooling plate (35), this cooling plate (35) is disposed adjacent to and face (19) radially-inwardly directed described in being parallel to, thus second channel (45) is formed between described cooling plate (35) and described radially-inwardly directed face (19), described cooling plate (35) comprises multiple cooling hole (47), hole (47) is formed the radially outward orientation of cooling fluid jet by the cooling fluid being supplied to described chamber (49) is cooled described in described motor using process, described jet collides and face (19) radially-inwardly directed described in cooling, cooling fluid from described second channel (45) enters described first passage (28).
20. motors according to claim 11, wherein there are two retaining pins (33), described rail (17) is included in the convex portion (23) of every one end and the depression (25) between described convex portion (23), and each convex portion (23) comprises hole (27), corresponding one in described two retaining pins (33) extends through this hole (27).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110038937.4A CN102644484B (en) | 2011-02-16 | 2011-02-16 | Gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110038937.4A CN102644484B (en) | 2011-02-16 | 2011-02-16 | Gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102644484A CN102644484A (en) | 2012-08-22 |
| CN102644484B true CN102644484B (en) | 2016-03-23 |
Family
ID=46657538
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110038937.4A Expired - Fee Related CN102644484B (en) | 2011-02-16 | 2011-02-16 | Gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102644484B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4815933A (en) * | 1987-11-13 | 1989-03-28 | The United States Of America As Represented By The Secretary Of The Air Force | Nozzle flange attachment and sealing arrangement |
| US4883405A (en) * | 1987-11-13 | 1989-11-28 | The United States Of America As Represented By The Secretary Of The Air Force | Turbine nozzle mounting arrangement |
| US5797723A (en) * | 1996-11-13 | 1998-08-25 | General Electric Company | Turbine flowpath seal |
| CN101424196A (en) * | 2007-10-31 | 2009-05-06 | 通用电气公司 | Gas turbines having flexible chordal hinge seals |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090169369A1 (en) * | 2007-12-29 | 2009-07-02 | General Electric Company | Turbine nozzle segment and assembly |
-
2011
- 2011-02-16 CN CN201110038937.4A patent/CN102644484B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4815933A (en) * | 1987-11-13 | 1989-03-28 | The United States Of America As Represented By The Secretary Of The Air Force | Nozzle flange attachment and sealing arrangement |
| US4883405A (en) * | 1987-11-13 | 1989-11-28 | The United States Of America As Represented By The Secretary Of The Air Force | Turbine nozzle mounting arrangement |
| US5797723A (en) * | 1996-11-13 | 1998-08-25 | General Electric Company | Turbine flowpath seal |
| CN101424196A (en) * | 2007-10-31 | 2009-05-06 | 通用电气公司 | Gas turbines having flexible chordal hinge seals |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102644484A (en) | 2012-08-22 |
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Granted publication date: 20160323 Termination date: 20190216 |