CN1816682A - Turbine shroud segment - Google Patents

Turbine shroud segment Download PDF

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Publication number
CN1816682A
CN1816682A CN 200480018949 CN200480018949A CN1816682A CN 1816682 A CN1816682 A CN 1816682A CN 200480018949 CN200480018949 CN 200480018949 CN 200480018949 A CN200480018949 A CN 200480018949A CN 1816682 A CN1816682 A CN 1816682A
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China
Prior art keywords
pair
seal slots
seal
plate
turbine
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Granted
Application number
CN 200480018949
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Chinese (zh)
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CN100538019C (en
Inventor
田中崇
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IHI Corp
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IHI Corp
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Abstract

A shroud segment for being incorporated in a gas turbine engine so as to suppress influence of hot combustion gas on a turbine case of the gas turbine engine is provided with a back plate having first and second plate portions formed in an arc shape and supported by the turbine case, a touching member integrally formed on an inner surface of the back plate for touching with a rotating turbine blade, a pair of first seal slots for receiving a pair of first spline seal plate, a pair of second seal slots for receiving a pair of second spline seal plate and a pair of seal gaps respectively communicating with the first seal slots and the second seal slots. The seal gaps are respectively provided with abutment surfaces recessed from front surfaces of the second seal slots so as to receive front ends of the first spline seal plates.

Description

Turbine shroud segment
Technical field
The present invention relates to the gas turbine engine of aircraft etc., relate in particular to the cover sheet of the turbine cover of gas turbine engine.
Background technique
The turbine of the gas turbine engine of aircraft etc. is provided with the multistage turbine cover, is used to suppress the influence of hot combustion gas to turbine box.Turbine cover directly is exposed to hot combustion gas, thereby may act on serious thermal stress there.Usually, for fear of extra thermal stress, each turbine cover is all cut apart.A plurality of cover sheets (shroud segment) are combined to form each turbine cover.
Each covers sheet and all is provided with support plate, as its main body, and forms with arc.The outer surface of support plate is supported by turbine box.The internal surface of support plate is provided with contact member integratedly, is used for contacting with the turbine blade of rotation, and this internal surface forms cellular or analogous shape.Support plate also is provided with first plate portion and second plate portion.
Two side surfaces of support plate all are respectively equipped with first seal slots.First seal slots is held the first spline sealing plate (spline seal plate), is used to suppress the leakage of hot combustion gas to low pressure turbine case.
Similarly, two of second plate portion side surfaces all are respectively equipped with second seal slots that communicates with first seal slots.Second seal slots is also held the second spline sealing plate, is used to suppress the leakage of hot combustion gas to low pressure turbine case.
This have the first and second spline sealing plates the cover sheet suppress the leakage of hot combustion gas effectively to low pressure turbine case, thereby prevent the superheating of low pressure turbine case.
Correlation technique is disclosed among the Japanese Unexamined Patent Publication No H09-329003.
The first and second spline sealing plates may be separated from from seal slots.For fear of being separated from, the first spline sealing plate front end should be crooked, be arranged in the outer ring of the turbine nozzle of cover sheet previous stage with butt joint.Yet the first crooked spline sealing plate becomes firmer, and forfeiture elasticity.This effect that causes suppressing hot gas leakage reduces.
Summary of the invention
The present invention has realized the solution of the problems referred to above, and is used to provide a kind of cover sheet, its prevent the first spline sealing plate leave, and need not the crooked first spline sealing plate.
According to a kind of technological scheme of the present invention, a kind of cover sheet, be used for being combined in gas turbine engine, to suppress the influence of hot combustion gas to the turbine box of gas turbine engine, be provided with support plate, it forms with arc and is supported by turbine box, and this support plate comprises first plate portion and second plate portion that forms and extend radially inwardly on the axial forward end of first plate portion; Contact member, it is formed on the internal surface of support plate, is used for contacting with rotary turbine blade; And a pair of first seal slots, being used to hold a pair of first spline sealing plate, this first seal slots is circumferentially formed on the both sides of first plate portion, and substantially extends striding across on the whole length of first plate portion; A pair of second seal slots is used to hold a pair of second spline sealing plate, and this second seal slots is circumferentially formed on the second plate portion both sides, and extends on the whole length of crossing over second plate portion substantially; And a pair of sealed airspace that communicates with first seal slots and second seal slots respectively, the sealing space comprises respectively from the butting surface of the front surface of second seal slots depression, with hold the first spline sealing plate front end.
More preferably, this cover sheet further is provided with the first spline sealing plate in a pair of insertion first seal slots and the second spline sealing plate in a pair of insertion second seal slots.
More preferably, be set to greater than 110 degree and less than 125 degree by first plane that is parallel to first seal slots and the formed angle in second plane that is parallel to butting surface.
More preferably, this cover sheet further is provided with the preceding sealing that is connected with the front-end face of support plate, with sealing from the radially inner side of support plate hot gas leakage to turbine box.
More preferably, preceding seal construction firmly contacts with the outer ring of the turbine nozzle that is arranged in cover sheet previous stage for the mode by its elastic force.
Description of drawings
Fig. 1 is the sectional view that covers sheet according to an embodiment of the invention at the arrow I place of Fig. 5;
Fig. 2 is the zoomed-in view around the cover sheet that covers the sheet front end at the arrow II place of Fig. 1;
Fig. 3 is the front elevation of cover sheet;
Fig. 4 is the plan view of cover sheet; And
Fig. 5 is the sectional view of the low-pressure turbine of cover sheet aircraft mounted thereto.
Embodiment
Below with reference to Fig. 1 to 5 embodiments of the invention are described.In whole specification, the definition of direction, such as preceding and after, consistent with the direction of element during reality is used.For example, front end is illustrated in LEFT HAND SIDE in Fig. 1 and 5.In and outward by contiguous and define away from the axis of turbogenerator.
Referring now to Fig. 5.The low-pressure turbine 1 of the turbogenerator of aircraft is provided with turbine box 3.The back turbine box 7 that turbine box 3 is provided with main turbine box 5 and is connected with the rear end one of turbine box 5.The front end of main turbine box 5 is connected with high pressure turbine case 9.
Be used for adjusting a plurality of turbine nozzles 13,15 of hot combustion gas and 17 fixing and be contained in main turbine box 5.Each turbine nozzle 13,15 and 17 all is split into a plurality of nozzle segments (nozzle segment), and its end docks with end and forms complete ring.A plurality of turbine rotors are alternately arranged with turbine nozzle 13,15 and 17, and are respectively equipped with turbine blade 19,21,23 and 25.Turbine rotor rotates uniformly, and is connected to the rotor of low pressure compressor (not shown) and the fan propeller of fan (not shown). Turbine cover 27,29,31 and 33 is arranged around turbine rotor respectively.Each turbine cover 27,29,31 and 33 all is split into a plurality of cover sheets, and its end docks with end and forms complete ring.
Hot combustion gas with energy is provided to low-pressure turbine 1 from the firing chamber (not shown), and with the rotary turbine rotor, low pressure compressor and fan are connected to turbine rotor.Thereby low-pressure turbine 1 extracts energy from hot combustion gas, and it is converted to the energy that drives low pressure compressor and fan.
Cover sheet 35 shown in Fig. 1 to 4 is cut apart from turbine cover 27, and it is arranged in the first order place of low-pressure turbine 1.Each covers sheet 35 and is provided with the support plate 37 that forms with arc.Support plate 37 is provided with the first plate portion 37a and the second plate portion 37b, and the second plate portion 37b is formed on the front end of the first plate portion 37a and is radially inside.
Sheet hook 43 is formed on its radially-outer surface along annular around the front end of support plate 37.Sheet hook 43 can closely be coupled to the annular groove 41 of the preceding case hook 39 of main turbine box 5.C clamp 45 with C word sectional shape is clipped on preceding case hook 39 and the sheet hook 43, and sheet hook 43 is fixed on the preceding case hook 39.Thereby the front end of support plate 37 is supported by main turbine box 5, and is fixing vertically.
The rear end of support plate 37, engage slidably mutually with the outer ring 47 of the turbine nozzle 13 of rear cabinet hook 49 in the cover sheet 35 of main turbine box 5 and rear cabinet hook 49 back and contiguous cover sheet 35.Thereby the rear end of support plate 37 is supported by outer ring 47 and rear cabinet hook 49, with fixing vertically.This supporting way allows the thermal walking of support plate 37.
Projection 51 with arc is formed on the radially-outer surface of rear end of support plate 37, so that can engage with the rear cabinet hook 49 that forms on the inner radial surface of main turbine box 5.Projection 51 has protrusion surface 51fa and periphery 51fb, and protrusion surface 51fa is perpendicular to the turbine axis, and relative with the axial front surface 49fa of rear cabinet hook 49, and periphery 51fb is parallel to turbine axis and relative with the internal surface of column 49fb of rear cabinet hook 49.Periphery 51fb is provided with annular lug, nib 53 integratedly, is used for contacting with internal surface of column 49fb.
Axial clearance forms between the axial front surface 49fa of the protrusion surface 51fa of projection 51 and rear cabinet hook 49.Axial clearance is configured to and will be adjusted to predetermined flow velocity by the flow velocity of mobile cooling air CA between main turbine box 5 and support plate 37.In addition, when projection 51 engaged with rear cabinet hook 49, axial clearance was set to narrower than the radial clearance between the internal surface of column 49fb of the periphery 51fb of the projection in the steady state 51 and rear cabinet hook 49.Simultaneously, cooling air CA provides from low pressure compressor, and via the conduction of the conduction hole 55h on the outer ring 55 that is formed on turbine nozzle 11, wherein turbine nozzle 11 vicinities are covered sheets 37 and covered sheet 37 arranged in front.
As shown in Fig. 1 and 4, the rear end of support plate 37 is provided with recess 57, and the adjusting strip 47a of outer ring 47 engages, and rotation is pinned relatively to make it.
The internal surface of support plate 37 is provided with honeycomb 59 integratedly, is used for contacting with the end fin 19a of rotary turbine blade 19.Honeycomb 59 is not limited to the element of honeycomb shape.It can be substituted by any contact member.
As shown in fig. 1, the second plate portion 37b is provided with integratedly with the annular slab shape and is formed on preceding sealing 61 on its axial front surface.Before sealing 61 suppress hot combustion gas from the leakage of the radially inner side of support plate 37 to low pressure turbine case 3, and further suppress cooling air CA from the leakage of conduction hole 55h to the radially inner side of support plate 37.Preceding sealing 61 has elasticity, and is configured to stably contact with the outer ring 55 of turbine nozzle 11 by the mode of elastic force.
As shown in figs. 1 and 2, the both side surface of the first plate portion 37a all is respectively equipped with first seal slots 65.First seal slots 65 is held the first spline sealing plate 63.The first spline sealing plate 63 suppresses the leakage of hot combustion gas to low pressure turbine case 3, and further suppresses the leakage of cooling air CA to the radially inner side of support plate 37.
Similarly, the both side surface of the second plate portion 37b all is respectively equipped with second seal slots 69 that communicates with first seal slots 65.Second seal slots 69 is also held the second spline sealing plate 67.The second spline sealing plate 67 suppresses the leakage of hot combustion gas to low pressure turbine case 3, and further suppresses the leakage of cooling air CA to the radially inner side of support plate 37.
As shown in Fig. 1 and 4, the both sides of the front end of the first plate portion 37a all are provided with a pair of sealed airspace 71.Each sealed airspace 71 all communicates with first seal slots 65 and second seal slots 69 on same side.Each sealed airspace 71 all is provided with butting surface 71f, thereby the first spline sealing plate 63 only stops thus.Butting surface 71f caves in a little from the front surface 69f of second seal slots 69.As shown in Figure 2, the angle υ that is formed by plane D1 that is parallel to butting surface 71f and the plane D2 that is parallel to first seal slots 65 is set to greater than 110 degree and less than 125 degree.
Working method and effect according to the cover sheet 35 of present embodiment will be described below.
When the first spline sealing plate 63 and the second spline sealing plate 67 are installed, at first turbine cover 27 is installed in the low pressure turbine case 3, secondly the both sides of each second spline sealing plate 67 are inserted in the sealed airspace 71 of cover sheet 35 of a pair of mutual vicinity, insert again at last in its second seal slots 69.Next, all insert in the sealed airspace 71 of a pair of cover sheet 35 at the two ends of each first spline sealing plate 63, and further insert in first seal slots 65.Thus, the first spline sealing plate 63 and the second spline sealing plate 67 just are installed to turbine cover 27.
The end face of the second spline sealing plate 67 docks the side of the first spline sealing plate 63, thereby prevents that the second spline sealing plate 67 from leaving from second seal slots 69.The end face of the first spline sealing plate 63 is to connecting butting surface 71f, thereby prevents that the first spline sealing plate 63 from leaving from first seal slots 65.More particularly, angle υ is set to greater than 110 degree, thus its reaction force that applies by butting surface 71f, and prevent that the end face of the first spline sealing plate 63 from going out.In addition, angle υ is set to less than 125 degree, thereby its reaction force by being applied by butting surface 71f prevents that the end face of the first spline sealing plate 63 from entering second seal slots 67.
As above-mentioned working method, the first spline sealing plate 65 and the second spline sealing plate 69 suppress the leakage of hot combustion gas, and cover sheet 35 more low pressure turbine case 3 and hot combustion gas are shielded, thereby the superheating of low pressure turbine case 3 is inhibited.And, the first spline sealing plate 63, the second spline sealing plate 67 etc. suppress the leakage of cooling air CA, and it guarantees to pass through at its flow velocity the state of the gap adjustment between the front surface 49fa of protrusion surface 51fa and rear cabinet hook 49 at mobile between the support plate 37 of main turbine box 5 and back.Thereby cooling air CA cools off low pressure turbine case 3 effectively.
Except above-mentioned working method, preceding sealing 61 also suppresses the leakage of hot combustion gas to low pressure turbine case 3, thereby further guarantees to cover the shield effectiveness of sheet 35.Preceding sealing 61 also suppresses the leakage of cooling air CA to support plate 37 inboards, thereby further guarantees the cooling effect of cooling air CA.
Although the present invention is by as above being described with reference to some embodiment of the present invention, the present invention is not limited to the foregoing description.Those skilled in the art can make the improvement and the variation of the foregoing description according to above-mentioned instruction.
Industrial usability
The invention provides a kind of cover sheet, the leakage of the hot combustion gas of its establishment, and prevent its first spline Leaving of sealing plate.

Claims (5)

1. a cover sheet is used for being combined in gas turbine engine, to suppress the influence of hot combustion gas to the turbine box of gas turbine engine, has:
Support plate, it forms with arc and is supported by turbine box, and this support plate comprises first plate portion and second plate portion that forms and extend radially inwardly on the axial forward end of first plate portion;
Contact member, it is formed on the internal surface of support plate, is used for contacting with rotary turbine blade; And
A pair of first seal slots is used to hold a pair of first spline sealing plate, and this first seal slots is circumferentially formed on the both sides of first plate portion, and substantially extends striding across on the whole length of first plate portion;
A pair of second seal slots is used to hold a pair of second spline sealing plate, and this second seal slots is circumferentially formed on the second plate portion both sides, and extends on the whole length of crossing over second plate portion substantially; And
The a pair of sealed airspace that communicates with first seal slots and second seal slots respectively, sealing space comprise respectively from the butting surface of the front surface of second seal slots depression, with hold the first spline sealing plate front end.
2. cover sheet as claimed in claim 1 is characterized in that also having:
The first spline sealing plate in a pair of insertion first seal slots; And
The second spline sealing plate in a pair of insertion second seal slots.
3. cover sheet as claimed in claim 1 is characterized in that,
By first plane that is parallel to first seal slots and the formed angle in second plane that is parallel to butting surface is greater than 110 degree and less than 125 degree.
4. cover sheet as claimed in claim 1 is characterized in that also having:
The preceding sealing that is connected with the front-end face of support plate, with sealing from the radially inner side of support plate hot gas leakage to turbine box.
5. cover sheet as claimed in claim 4 is characterized in that, wherein:
Preceding seal construction firmly contacts with the outer ring of the turbine nozzle that is arranged in cover sheet previous stage for the mode by its elastic force.
CNB2004800189499A 2003-07-04 2004-07-02 Turbine shroud segment Expired - Fee Related CN100538019C (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
JP271197/2003 2003-07-04
JP271196/2003 2003-07-04
JP2003271196A JP4200846B2 (en) 2003-07-04 2003-07-04 Shroud segment
US10/740,663 2003-12-22

Publications (2)

Publication Number Publication Date
CN1816682A true CN1816682A (en) 2006-08-09
CN100538019C CN100538019C (en) 2009-09-09

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CNB2004800189499A Expired - Fee Related CN100538019C (en) 2003-07-04 2004-07-02 Turbine shroud segment

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CN (1) CN100538019C (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102016236A (en) * 2008-04-24 2011-04-13 斯奈克玛 Turbine nozzle box for a turbomachine
CN102428254A (en) * 2009-05-15 2012-04-25 斯奈克玛 Unducted propeller including variable pitch blades for a turbine engine
CN103184900A (en) * 2012-01-03 2013-07-03 通用电气公司 Stage of a gas turbine engine and corresponding method of retrofitting
CN103184901A (en) * 2012-01-03 2013-07-03 通用电气公司 Contoured honeycomb seal for turbine shroud
CN103987922A (en) * 2011-12-13 2014-08-13 联合工艺公司 Stator vane shroud having an offset
CN107269323A (en) * 2016-03-31 2017-10-20 通用电气公司 Seal the seal assembly of the corner leakage in gas turbine
CN108798804A (en) * 2017-02-24 2018-11-13 通用电气公司 Spline for turbogenerator
CN109072705A (en) * 2015-12-18 2018-12-21 赛峰飞机发动机公司 The turbine ring assemblies elastically kept in the cold state
CN111279103A (en) * 2017-10-26 2020-06-12 赛峰短舱公司 Propulsion unit for an aircraft

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FR2899274B1 (en) 2006-03-30 2012-08-17 Snecma DEVICE FOR FASTENING RING SECTIONS AROUND A TURBINE WHEEL OF A TURBOMACHINE
FR2923527B1 (en) * 2007-11-13 2013-12-27 Snecma STAGE OF TURBINE OR COMPRESSOR, IN PARTICULAR TURBOMACHINE
FR2952965B1 (en) * 2009-11-25 2012-03-09 Snecma INSULATING A CIRCONFERENTIAL SIDE OF AN EXTERNAL TURBOMACHINE CASTER WITH RESPECT TO A CORRESPONDING RING SECTOR
FR2983518B1 (en) * 2011-12-06 2014-02-07 Snecma UNLOCKING DEVICE FOR AXIAL STOP OF A SEALED CROWN CONTACTED BY A MOBILE WHEEL OF AIRCRAFT TURBOMACHINE MODULE
US20140271142A1 (en) * 2013-03-14 2014-09-18 General Electric Company Turbine Shroud with Spline Seal
JP6233578B2 (en) * 2013-12-05 2017-11-22 株式会社Ihi Turbine
CN115263808B (en) * 2022-09-28 2023-02-21 中国航发四川燃气涡轮研究院 Intermediate casing of integrated double-rotor aircraft engine

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102016236A (en) * 2008-04-24 2011-04-13 斯奈克玛 Turbine nozzle box for a turbomachine
CN102016236B (en) * 2008-04-24 2014-06-18 斯奈克玛 Turbine nozzle box for a turbomachine
CN102428254A (en) * 2009-05-15 2012-04-25 斯奈克玛 Unducted propeller including variable pitch blades for a turbine engine
CN102428254B (en) * 2009-05-15 2014-08-20 斯奈克玛 Unducted propeller including variable pitch blades for a turbine engine
CN103987922B (en) * 2011-12-13 2016-02-24 联合工艺公司 There is the stator vane guard shield of dislocation
US9840917B2 (en) 2011-12-13 2017-12-12 United Technologies Corporation Stator vane shroud having an offset
CN103987922A (en) * 2011-12-13 2014-08-13 联合工艺公司 Stator vane shroud having an offset
CN103184900B (en) * 2012-01-03 2017-10-24 通用电气公司 For turbine shroud to the cellular seal of front step
CN103184901B (en) * 2012-01-03 2017-04-26 通用电气公司 Contoured honeycomb seal for turbine shroud
CN103184901A (en) * 2012-01-03 2013-07-03 通用电气公司 Contoured honeycomb seal for turbine shroud
CN103184900A (en) * 2012-01-03 2013-07-03 通用电气公司 Stage of a gas turbine engine and corresponding method of retrofitting
CN109072705A (en) * 2015-12-18 2018-12-21 赛峰飞机发动机公司 The turbine ring assemblies elastically kept in the cold state
CN109072705B (en) * 2015-12-18 2021-02-09 赛峰飞机发动机公司 Elastically retained cold turbine ring assembly
CN107269323A (en) * 2016-03-31 2017-10-20 通用电气公司 Seal the seal assembly of the corner leakage in gas turbine
CN107269323B (en) * 2016-03-31 2022-07-12 通用电气公司 Seal assembly for sealing corner leakage in a gas turbine
CN108798804A (en) * 2017-02-24 2018-11-13 通用电气公司 Spline for turbogenerator
US10648362B2 (en) 2017-02-24 2020-05-12 General Electric Company Spline for a turbine engine
CN108798804B (en) * 2017-02-24 2021-04-06 通用电气公司 Spline for turbine engine
CN111279103A (en) * 2017-10-26 2020-06-12 赛峰短舱公司 Propulsion unit for an aircraft
CN111279103B (en) * 2017-10-26 2022-01-07 赛峰短舱公司 Propulsion unit for an aircraft

Also Published As

Publication number Publication date
JP4200846B2 (en) 2008-12-24
CN100538019C (en) 2009-09-09
JP2005030313A (en) 2005-02-03

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