CN101592163A - The undercutting of compressor rotor blade - Google Patents
The undercutting of compressor rotor blade Download PDFInfo
- Publication number
- CN101592163A CN101592163A CNA2009101492055A CN200910149205A CN101592163A CN 101592163 A CN101592163 A CN 101592163A CN A2009101492055 A CNA2009101492055 A CN A2009101492055A CN 200910149205 A CN200910149205 A CN 200910149205A CN 101592163 A CN101592163 A CN 101592163A
- Authority
- CN
- China
- Prior art keywords
- tenon portion
- rotor blade
- aerofoil profile
- nip
- profile part
- 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.)
- Pending
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
Abstract
The present invention relates to the undercutting of compressor rotor blade, particularly, the invention discloses a kind of rotor blade 30 that is used for Axial Flow Compressor, rotor blade 30 comprises aerofoil profile part 12 and root 13, aerofoil profile part 12 comprises leading edge 17, root 13 comprises platform 18 and tenon portion 20, platform 18 is the outer radial face of root 13, aerofoil profile part 12 extends from this outer radial face, tenon portion 20 comprises tenon portion front surface 22, just is mounted in the Axial Flow Compressor surface of the tenon portion 20 of directed upstream roughly in case this tenon portion front surface 22 is rotor blades 30.Rotor blade 30 can comprise the nip 32 that is formed on the tenon portion front surface 22, and this nip 32 is with the leading edge 17 of aerofoil profile part 12 and the cross-shaped portion undercutting at least in part of platform 18.
Description
Technical field
The application is broadly directed to the compressor blade in the turbogenerator.More particularly, but not as restrictedly, the application relates to such compressor rotor blade, and this compressor rotor blade design and being configured for reduces the operation stress in the location of blade, so that blade has more repellence to corrosion.
Background technique
In gas turbine engine, compressor generally includes a plurality of levels of rotor blade (being also referred to as " rotor aerofoil profile part " or " compressor blade " usually) with row and stator vane (being also referred to as " stator aerofoil profile part " usually).Rotor blade is around rotor rotation and thus kinetic energy is passed to the air-flow that passes compressor.Followed by the rotor blade row are stator vanes of the static one-tenth row of maintenance.Under acting in conjunction, rotor blade and stator vane make the air-flow rotation respectively and reduce the speed of air, and this feasible static pressure of passing the air-flow of compressor is enhanced.Usually, multistage rotor blade and stator vane are stacked in Axial Flow Compressor, so that reach required emitting than the air pressure ratio that enters.Rotor blade and stator vane are usually by means of tenon portion attachment part or root attachment part or bottom attachment part and be fixed to respectively on impeller and the stator case.
In order to improve the performance of compressor, wash termly so that rotor for cleaning blade and stator vane.In this process, water is directly sprayed into the import of operating compressor.Water bump first order rotor blade, and be carried along with flowing of air then and pass compressor, so that remaining rotor blade and stator vane also are cleaned.Bump on the bump of water on rotor blade, the especially leading edge of the rotor blade in the first order can cause corrosion.This corrosion causes usually along the indenture of the leading edge of rotor blade and/or the formation in crack.Along with the repetition of process, indenture and crack deepen and broaden.
Can recognize as those of ordinary skill in the art, rotor blade at run duration owing to the rotational speed of compressor is born high-caliber mechanical stress.The speed of the corrosion that this high-caliber stress influence takes place on the rotor blade leading edge.That is to say that the amount of the corrosion that leading edge stood of rotor blade is directly proportional with the height of the stress that stands in this place, position usually.Along with stress improves, rate of corrosion also improves.As time goes on, the corrosion of high stress level and growth can cause the high cycle fatigue crackle in the rotor blade, and it finally can cause blade to lose efficacy.Undoubtedly, the rotor blade that takes place at run duration lost efficacy and can cause catastrophic failure to the parts in the downstream of turbine.Therefore, exist the improved system that can take precautions against this possibility better, the demand that continues of method and apparatus.More particularly, existing demand for so improved rotor blade--this rotor blade comes work with the lower stress level at the leading edge place, so that this blade is more corrosion-resistant.
Summary of the invention
Therefore, the invention describes the rotor blade that is used for Axial Flow Compressor, this rotor blade can comprise aerofoil profile part and root, this aerofoil profile part comprises leading edge, this root comprises platform and tenon portion, and this platform is the outer radial face (the aerofoil profile part extends from this outer radial face) of root, and tenon portion comprises tenon portion front surface, in case this tenon portion front surface is that such surface of tenon portion--rotor blade is mounted in the Axial Flow Compressor, this surface is the cardinal principle directed upstream just.Rotor blade can comprise the nip that is formed on the tenon portion front surface, and this nip is with the cross-shaped portion undercutting at least in part of aerofoil profile part leading edge and platform.
The present invention has also described the rotor blade that is used for Axial Flow Compressor, and this rotor blade can comprise aerofoil profile part and root.The aerofoil profile part can comprise aerofoil profile part suction side, aerofoil profile part on the pressure side and leading edge, in case this leading edge is to be defined in aerofoil profile part suction side and the aerofoil profile part rotor blade between on the pressure side just to be mounted in the Axial Flow Compressor edge of directed upstream substantially.Root can comprise platform and tenon portion, and this platform is that such outer radial face of root--the aerofoil profile part extends from this outer radial face, and tenon portion is used for rotor blade is connected to impeller.Tenon portion can comprise tenon portion front surface, tenon portion suction side and tenon portion on the pressure side, in case tenon portion front surface is that such surface of tenon portion--rotor blade is mounted in the Axial Flow Compressor, this surface is the cardinal principle directed upstream just.Rotor blade can also comprise the nip that is formed on the tenon portion front surface, this nip with the cross-shaped portion of the leading edge of aerofoil profile part and this platform basically undercutting open.Nip can begin from the approximate center of tenon portion front surface and extend towards edge tenon portion, that tenon portion front surface and tenon portion are on the pressure side separated.
When reach in conjunction with the accompanying drawings appended claim consulted below after the specific descriptions to preferred implementation, these and other feature of the application will become apparent.
Description of drawings
These and other purpose of the present invention and favourable part can more fully be understood and be familiar with to the following more detailed description to exemplary embodiment of the present of research carefully in conjunction with the drawings, wherein:
Fig. 1 is the perspective view of typical compressor rotor blade.
Fig. 2 is the perspective view that has shown according to the compressor rotor blade of the nip of the application's exemplary embodiment.
Fig. 3 is the perspective view that has shown according to the compressor rotor blade of the nip of the application's alternative embodiment.
The rotor blade of 10 routines
12 aerofoil profile parts
13 roots
14 suction side
16 on the pressure side
17 leading edges
18 platforms
20 tenon portions
22 tenon portion front surfaces
24 tenon portion suction side
26 tenon portions on the pressure side
28 leading edges bottom
30 rotor blades
32 nips
Embodiment
Referring now to accompanying drawing, wherein a plurality of labels part like the representation class in these some views, Fig. 1 has shown conventional rotor blade 10.Just as this field technicians can recognize, rotor blade 10 can comprise aerofoil profile part 12 and bottom or claim root 13 that this aerofoil profile part 12 passes to kinetic energy the air of the compressor of flowing through when rotating the son rotation.Aerofoil profile part 12 generally includes suction side 14 (that is convex side) and 16 (that is concave side) on the pressure side.Aerofoil profile part 12 also has leading edge 17, in case this leading edge 17 suction side 14 and on the pressure side between 16 rotor blade 10 be mounted into and just be often referred to upstream edge in the compressor.
In use, the tenon portion 20 of the rotor blade 10 of Fig. 1 is assemblied on the corresponding compressor wheels groove slightly loosely, begins to rotate up to rotor.Along with wheel turns, centrifugal force radially outwards pushes against tenon portion 20 on the groove in the compressor wheels (or other keeps part) securely.Counter-force is formed at the pressure surface place of wheel, and this counter-force is offset the centrifugal force that is produced by rotor blade 10.Centrifugal force produces stress in rotor blade 10.Cognoscible as those of ordinary skill in the art, stress is concentrated in some position in aerofoil profile part 12 usually.One of them position that stress is concentrated is near the interior radially part (that is, such the position--leading edge 17 is connected to platform 18 this position) of the leading edge 17 of aerofoil profile part 12.The position that this stress is concentrated is in following so-called " bottom of leading edge " or " leading edge bottom " (and being labeled as 28 in the drawings).As previously discussed, cause aqueous corrosion to damage quickly and weaken rotor blade 10 28 places, leading edge bottom heavily stressed at run duration in this position.This infringement is to producing adverse influence in working life of rotor blade 10.
In the application's exemplary embodiment, as shown in FIG. 2, rotor blade 30 (for example, for example, the rotor blade that in the Axial Flow Compressor of industrial combustion gas turbogenerator, uses) generally includes aerofoil profile part 12 and root 13, this aerofoil profile part 12 has suction side 14 and on the pressure side 16, this root 13 has platform 18 and tenon portion 20 (this tenon portion 20 comprise tenon portion front surface 22, tenon portion suction side 24 and tenon portion on the pressure side 26), and this tenon portion 20 is used for blade is connected to the compressor wheels (not shown).Usually, tenon portion 20 is attached to the wheel rim of wheel with rotor blade 10, so that a collection of rotor blade 10 arranges round the periphery of wheel, thereby forms the circumferential alignment of blade 10.
Fig. 2 has also shown the nip 32 based on exemplary embodiment of the present invention, this nip 32 in use can advantageously reduce aerofoil profile part 12 in leading edge bottom 28 (as previously discussed, this leading edge bottom 28 is such zones of leading edge 17, that is, leading edge 17 is connected to platform 18 near this zone) stress that stands of place.Nip 32 can comprise such groove usually, this groove shaped is formed in the tenon portion front surface 22, just radially inboard footpath in platform 18 is (height) apicad, and roughly is positioned at the below (that is, radially inboard in this cross-shaped portion) of leading edge 17 and platform 18 cross-shaped portions.Notice that the description of the position of nip 32 is intended to generally describe groove with respect to such position--be connected to platform 18 in this position leading edge 17, and with respect to tenon portion front surface 22, tenon the portion on the pressure side 26 and position of tenon portion suction side 24.In some cases, the rotor blade structure element of being confirmed in the sentence in front can adopt slightly different form, and is known as other title (for example, being different from above-described tenon portion-groove assembly if rotor blade 10 is connected to the mode of wheel).Those skilled in the art can be easy to recognize that the present invention is still applicable to this rotor blade, and is roughly similar as long as the basic shape of nip 32 and relative position keep.Therefore, although concrete title (for example " tenon portion ") is used for describing the specific feature of rotor blade 10 in this article, yet, desiredly be, these titles and nonrestrictive, and this application the rotor blade of similar characteristics should keep suitable for having roughly.
In one or more embodiments of the application, nip 32 can comprise following characteristic, although each in these attributes is all comprised in each embodiment.Nip 32 normally passes tenon portion front surface 22 and extends into cross-shaped portion in the tenon portion 20, that make platform 18 and leading edge 17 by the groove of undercutting.Visual angle and orientation according to the rotor blade among Fig. 2 10, undercutting can define in this wise, promptly, mean, nip 32 extends in the tenon portion 20, so that under the cross-shaped portion of platform 18 and leading edge 17 and nestle up platform 18 and leading edge 17 cross-shaped portion tenon portion 20 volume at least in part (and, in other embodiments, to a great extent or fully) be removed.The position of the removed volume of tenon portion 20 can also be described as nestling up platform 18 and than the radially more inner volume of cross-shaped portion of platform 18 and leading edge 17.That is to say that nip 32 extends to the such degree of depth in the tenon portion, that is, make it axially align with at least a portion in the cross-shaped portion of platform 18 and leading edge 17.
As shown, nip 32 can be roughly begin in the approximate center of tenon portion front surface 22, and extends towards such edge of tenon portion 20--and this edge on the pressure side 26 separates tenon portion front surface 22 and tenon portion.Like this, as shown in FIG. 2, nip 32 can see through tenon portion on the pressure side 26 and open wide.
When on the pressure side observing on 26 on the tenon portion front surface 22 and in tenon portion, nip 32 can form profile roughly.As shown in FIG. 2, on tenon portion front surface 22, profile can be roughly rectangle and (notice, a limit disappearance of rectangle, this is because the following fact, that is, nip 32 extend through tenon portion 20, with tenon portion front surface 22 and tenon portion 26 edges that separate on the pressure side).In certain embodiments and as shown in FIG. 2, because the chamfered area in bight and pass tenon portion 26 opening on the pressure side, so the shape of this rectangle can form approximate " U " shape, although when observing in the perspective view from Fig. 2, " U " seems just approximately to have been turned over 90 degree widdershins as it.Notice, in other embodiments, rotation angle (as what presented in its perspective view in Fig. 2) can less times greater than or less than 90 the degree.
On the pressure side on 26, this profile also can be rectangle (notice, just as before, also lack wherein limit of rectangle) to a certain extent in tenon portion.Because the chamfered area in bight, the tenon portion on the pressure side rectangular shape on 26 can form approximate " U " shape equally, although in this case, when the perspectives from Fig. 2, should " U " seem just as it is placed on its side, that is, 90 degree have deasil approximately been turned over as it.Notice in other embodiments, rotation angle (as what presented in its perspective view in Fig. 2) can less times greater than or less than 90 the degree.
Nip 32 can so form, and, makes outside the edge just below platform 18 (in other words, the footpath is upwards at platform 18 inboard places) upwards, footpath of groove 32 that is.Usually, edge and the distance between the platform that the footpath of nip 32 makes progress outside are approximately 0.1 inch to 1.0 inches, although the size outside this scope also is possible.The edge that the footpath of nip 32 makes progress outside can be so directed, that is, make it be roughly parallel to tenon portion platform 18.When forming nip 32, the angle of the otch of incision tenon portion front surface 22 and the size of otch can be optimised.In certain embodiments and as shown in FIG. 2, with respect to for the mean camber line (mean camber line) of the aerofoil profile part 12 of platform 18 sections, the angle of incision tenon portion front surface 22 is roughly 90 degree.In this way, the load on the nip 32 in service is roughly along the length of groove and distribute.
The degree of depth of nip 32 will influence operation stress by the distance of being passed through when reorientate the leading edge bottom 28 of aerofoil profile part 12.Darker groove means that usually leading edge bottom 28 will stand lower stress at run duration.In certain embodiments, nip 32 has this degree of depth, that is, make groove 32 enter by run duration blade loading caused at the stress line of the compressor rotor blade at 18 places, leading edge bottom.That is to say that the degree of depth of nip 32 will be for such, that is, make the place, inboard that footpath in the tenon portion, that be positioned at the cross-shaped portion of platform 18 and leading edge 17 makes progress the zone at least in part (and, in other embodiments, to a great extent or fully) be removed.
In service, nip 32 causes leaving the change of the load path direction of leading edge 17 usually.Groove reduced leading edge 17 places at aerofoil profile part 12, especially at 28 places, leading edge bottom (at this place, aerofoil profile part 12 attached platform 18) stress that forms.Usually, cognoscible as those of ordinary skill in the art, it is to be connected because directly throw off with tenon portion 20 basically leading edge bottom 28 that the stress reduction takes place.As previously discussed, reducing stress at 28 places, leading edge 17 and/or leading edge bottom means usually at the reduction of the corrosion of these positions and the longer part life for rotor blade 10.In addition, the shape of nip 32 can be manufactured relatively simply.
Those skilled in the art will recognize that preferably,, utilize the stopper (not shown) to fill nip 32 at run duration.As shown in FIG. 3, in alternative embodiment, nip 32 can have the shape that helps to keep the stopper that inserted.In such embodiments, nip 32 is convergent as follows, that is, make the width of nip 32 narrower and extend in the tenon portion 20 along with nip 32 and broaden at tenon portion front surface 22 places.That is to say that nip 32 outwards opens as follows from the opening at tenon portion front surface 22 places, that is, broaden when making groove 32 in extending into tenon portion 20.Utilize this configuration, the stopper that is formed for being assemblied in closely in the nip 32 relatively can not leave nip 32 from tenon portion front surface 22, and reason is that slot opening is too narrow.However, this stopper still can on the pressure side 26 be inserted into from tenon portion easily.Stopper can be made by any material that can tolerate the mal-condition in the compressor, and for example, stopper can be made by nylon.
In certain embodiments, nip 32 can be used in first order rotor blade, and the corrosion at this place is the most serious usually.In other embodiments, nip 32 can be used in all levels of compressor.
Above description according to a preferred embodiment of the invention, those skilled in the art can figure out improvement, change and change.This improvement, change and change in art technology are intended to be contained by appended claim.In addition, more than describe the described embodiment who obviously only relates to the application, and can carry out countless variations and change, and can not deviate from spirit and scope as claims and the application that equivalent limited thereof at this.
Claims (10)
1. rotor blade 30 that is used for Axial Flow Compressor, described rotor blade 30 comprises aerofoil profile part 12 and root 13, described aerofoil profile part 12 comprises leading edge 17, described root 13 comprises platform 18 and tenon portion 20, described platform 18 is the outer radial face of described root 13, described aerofoil profile part 12 extends from this outer radial face, described tenon portion 20 comprises tenon portion front surface 22, described tenon portion front surface 22 is that described rotor blade 30 comprises in case described rotor blade 30 is mounted into the just surface of the described tenon portion 20 of directed upstream roughly of described Axial Flow Compressor:
Be formed at the nip 32 on the described tenon portion front surface 22, described nip 32 is with the leading edge 17 of described aerofoil profile part and the cross-shaped portion undercutting at least in part of described platform 18.
2. rotor blade 30 according to claim 1 is characterized in that:
Described aerofoil profile part 12 also comprises aerofoil profile part suction side 14 and aerofoil profile part on the pressure side 16;
The leading edge 17 of described aerofoil profile part 12 be defined in described aerofoil profile part suction side 14 and described aerofoil profile part between on the pressure side, in case described rotor blade 30 just is mounted in the described Axial Flow Compressor edge of directed upstream roughly;
Described tenon portion is used for described rotor blade 30 is connected to impeller at least in part; And
Described tenon portion 20 also comprises tenon portion suction side 24 and tenon portion on the pressure side 26, each in them respectively with described aerofoil profile part suction side 14 and described aerofoil profile part 16 the same sides on the pressure side corresponding to described rotor blade 30.
3. rotor blade 30 according to claim 1 is characterized in that, described nip 32 is with the leading edge 17 of described aerofoil profile part 12 and the described cross-shaped portion undercutting fully of described platform 18.
4. rotor blade 30 according to claim 1, it is characterized in that, term " with the leading edge 17 of described aerofoil profile part 12 and the described cross-shaped portion undercutting at least in part of described platform 18 " is defined as and means that described nip 32 extends reach such degree of depth in described tenon portion 20, that is, make at least a portion in the described cross-shaped portion of the leading edge 17 of a part and described aerofoil profile part 12 of described nip 32 and described platform 18 axially align.
5. rotor blade 30 according to claim 4 is characterized in that, the distance between the radially high and described platform 18 of the outermost of described nip 32 radially high is greatly between 0.1 inch to 1.0 inches.
6. rotor blade 30 according to claim 4, it is characterized in that, described nip begin in the approximate center of described tenon portion front surface 22 and towards described tenon portion 20, with described tenon portion front surface 22 and described tenon portion 26 edges that separate and extending on the pressure side.
7. rotor blade 30 according to claim 6 is characterized in that, described nip 32 extends through described tenon portion on the pressure side 26 so that described nip 32 sees through described tenon portion on the pressure side 26 and open wide.
8. rotor blade 30 according to claim 7, it is characterized in that, described nip 32 is tapered as follows, that is, make the width of described nip 32 at described tenon portion front surface 22 places narrower and when described nip 32 extends in the described tenon portion 20 broad then.
9. rotor blade 30 according to claim 1 is characterized in that, described nip 32 is on the described tenon portion front surface 22 and the profile that on the pressure side comprises essentially rectangular in described tenon portion on 26.
10. rotor blade 30 according to claim 1 is characterized in that, is approximately 90 degree for forming otch that described nip 32 cuts described tenon portion front surface 22 with respect to the angle at the mean camber line of the described aerofoil profile part 12 at described platform 18 places.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/127889 | 2008-05-28 | ||
| US12/127,889 US20090297351A1 (en) | 2008-05-28 | 2008-05-28 | Compressor rotor blade undercut |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101592163A true CN101592163A (en) | 2009-12-02 |
Family
ID=41254222
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2009101492055A Pending CN101592163A (en) | 2008-05-28 | 2009-05-27 | The undercutting of compressor rotor blade |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20090297351A1 (en) |
| JP (1) | JP2009287556A (en) |
| CN (1) | CN101592163A (en) |
| DE (1) | DE102009025814A1 (en) |
| FR (1) | FR2931904A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105874169A (en) * | 2014-01-16 | 2016-08-17 | 株式会社Ihi | Vane connection part structure and jet engine utilizing same |
| CN107143381A (en) * | 2017-06-06 | 2017-09-08 | 哈尔滨汽轮机厂有限责任公司 | It is a kind of to reduce the gas turbine turbine first order movable vane piece of stress |
| CN109114832A (en) * | 2018-07-26 | 2019-01-01 | 郑州轻工业学院 | Intelligent double-screw compressor and its intelligent control method for Energy Management Contract |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8550783B2 (en) | 2011-04-01 | 2013-10-08 | Alstom Technology Ltd. | Turbine blade platform undercut |
| US8721291B2 (en) * | 2011-07-12 | 2014-05-13 | Siemens Energy, Inc. | Flow directing member for gas turbine engine |
| US9359905B2 (en) * | 2012-02-27 | 2016-06-07 | Solar Turbines Incorporated | Turbine engine rotor blade groove |
| JP2016035209A (en) * | 2014-08-01 | 2016-03-17 | 三菱日立パワーシステムズ株式会社 | Axial-flow compressor and gas turbine with axial-flow compressor |
| US10260350B2 (en) | 2014-09-05 | 2019-04-16 | United Technologies Corporation | Gas turbine engine airfoil structure |
| EP3015652A1 (en) * | 2014-10-28 | 2016-05-04 | Siemens Aktiengesellschaft | Rotor blade for a turbine |
| US10190595B2 (en) | 2015-09-15 | 2019-01-29 | General Electric Company | Gas turbine engine blade platform modification |
| US11098729B2 (en) | 2016-08-04 | 2021-08-24 | General Electric Company | Gas turbine wheel assembly, method of modifying a compressor wheel, and method of mounting a blade to a gas turbine wheel |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4480957A (en) * | 1983-04-14 | 1984-11-06 | General Electric Company | Dynamic response modification and stress reduction in dovetail and blade assembly |
| US6390775B1 (en) * | 2000-12-27 | 2002-05-21 | General Electric Company | Gas turbine blade with platform undercut |
| US6769877B2 (en) * | 2002-10-18 | 2004-08-03 | General Electric Company | Undercut leading edge for compressor blades and related method |
| US7121803B2 (en) * | 2002-12-26 | 2006-10-17 | General Electric Company | Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge |
| US20040213672A1 (en) * | 2003-04-25 | 2004-10-28 | Gautreau James Charles | Undercut leading edge for compressor blades and related method |
| US6902376B2 (en) * | 2002-12-26 | 2005-06-07 | General Electric Company | Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge |
| US7147440B2 (en) * | 2003-10-31 | 2006-12-12 | General Electric Company | Methods and apparatus for cooling gas turbine engine rotor assemblies |
| US7594799B2 (en) * | 2006-09-13 | 2009-09-29 | General Electric Company | Undercut fillet radius for blade dovetails |
-
2008
- 2008-05-28 US US12/127,889 patent/US20090297351A1/en not_active Abandoned
-
2009
- 2009-05-15 DE DE102009025814A patent/DE102009025814A1/en not_active Withdrawn
- 2009-05-20 FR FR0953388A patent/FR2931904A1/en not_active Withdrawn
- 2009-05-25 JP JP2009124881A patent/JP2009287556A/en active Pending
- 2009-05-27 CN CNA2009101492055A patent/CN101592163A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105874169A (en) * | 2014-01-16 | 2016-08-17 | 株式会社Ihi | Vane connection part structure and jet engine utilizing same |
| CN105874169B (en) * | 2014-01-16 | 2017-09-15 | 株式会社Ihi | The jet engine for linking cage structure and the link cage structure using the blade of blade |
| CN107143381A (en) * | 2017-06-06 | 2017-09-08 | 哈尔滨汽轮机厂有限责任公司 | It is a kind of to reduce the gas turbine turbine first order movable vane piece of stress |
| CN109114832A (en) * | 2018-07-26 | 2019-01-01 | 郑州轻工业学院 | Intelligent double-screw compressor and its intelligent control method for Energy Management Contract |
| CN109114832B (en) * | 2018-07-26 | 2020-12-11 | 郑州轻工业学院 | Intelligent double-screw compressor for contract energy management and intelligent control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2931904A1 (en) | 2009-12-04 |
| DE102009025814A1 (en) | 2009-12-03 |
| US20090297351A1 (en) | 2009-12-03 |
| JP2009287556A (en) | 2009-12-10 |
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| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20091202 |