US20040086383A1 - Turbine nozzle retention apparatus at the carrier horizontal joint face - Google Patents
Turbine nozzle retention apparatus at the carrier horizontal joint face Download PDFInfo
- Publication number
- US20040086383A1 US20040086383A1 US10/284,211 US28421102A US2004086383A1 US 20040086383 A1 US20040086383 A1 US 20040086383A1 US 28421102 A US28421102 A US 28421102A US 2004086383 A1 US2004086383 A1 US 2004086383A1
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- United States
- Prior art keywords
- groove
- nozzle
- key
- carrier half
- nozzles
- 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.)
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- 230000014759 maintenance of location Effects 0.000 title claims description 10
- 230000000295 complement effect Effects 0.000 claims 1
- 230000002452 interceptive effect Effects 0.000 abstract 1
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
Definitions
- the present invention relates to apparatus for retaining nozzles stacked one against the other in a groove of a carrier of a turbine and particularly relates to a turbine nozzle retention apparatus for retaining the nozzles in carrier grooves at the horizontal joint faces between upper and lower carrier halves which does not interfere with radially loading the nozzles.
- a carrier for the axially spaced, circumferential arrays of nozzles.
- the carrier typically includes carrier halves which extend arcuately 180° and are secured to one another at a horizontal joint face to form a 360° array of nozzles at each axial stage position.
- the nozzles comprise an airfoil having a radial outer dovetail-shaped base for reception in a generally correspondingly dovetail-shaped groove in the carrier.
- the opposite side faces of each base of the nozzles are angled relative to the axis of the turbine enabling the base to accommodate the angularity of the airfoil.
- each carrier half groove When the nozzles are installed in each carrier half groove, the nozzle bases are stacked one against the other within the grooves forming a semi-circular array of nozzles.
- Radial loading pins are also provided for each nozzle. Each pin is disposed between the base of the nozzle and the base of the groove biasing the nozzle radially inwardly. A clearance between adjacent end nozzles across the horizontal joint of the upper and lower carrier halves is necessary when the carrier halves are secured to one another. Accordingly, there is a need for a retaining device at the horizontal joint face for retaining the nozzles within the carrier half groove and which does not interfere with the radial loading of the nozzles.
- each carrier half has a plurality of axially spaced grooves having semi-circular configurations about the carrier half. Each groove has a dovetail configuration. Nozzles having a correspondingly dovetail-shaped radially outer base are inserted into the carrier groove and stacked one against the other to form an arcuate array of nozzles. At each joint interface where a clearance between adjacent nozzles of the upper and lower carrier halves is required, each end nozzle projects beyond its associated joint face.
- the nozzle base of each end nozzle includes a notch formed along its radial outward face and which notch includes an abutment face extending in an axial direction.
- a key slot is formed in each carrier half at each joint face and lies in alignment with the notch and the abutment face.
- An elongated key is disposed in the notch in engagement against the abutment face of the nozzle base.
- a radial loading pin is disposed in a recess in the outermost wall of the carrier groove and engages the portion of the nozzle base which is not notched to provide the radial inward bias to the end nozzle.
- the key is secured to the carrier half and in the key slot at the joint face, for example, by peening between the joint face and the key.
- the key may be retained in the key slot by one or more screws having heads recessed below the joint interface.
- the key therefore prevents circumferential movement of the nozzle from the carrier groove while the radial loading pin biases the nozzle radially inwardly.
- the end nozzle and retainer key of the present invention is provided at at least one of two horizontal joint faces for each groove of each carrier half.
- all four horizontal joint faces of the two carrier halves forming each annular groove of the carrier are provided with the nozzle retention apparatus hereof.
- nozzle retention apparatus for a turbine comprising a generally semi-cylindrical nozzle carrier half for extending about an axis of the turbine and having an arcuate, radially inwardly opening, shaped groove terminating at opposite ends in respective joint faces, a plurality of nozzles for the turbine, each nozzle including an airfoil and an outer base having a shape generally corresponding to the shape of the groove and received in the groove, a key slot in one of the horizontal joint faces at one end of the groove, one of the nozzles in the groove of the carrier half at the one horizontal joint face extending circumferentially beyond the joint face and having a notch formed in the base thereof extending inwardly of the one joint face and a key in the key slot secured to the carrier half and engaging in the notch of the one nozzle to retain the nozzles in the carrier half groove.
- nozzle retention apparatus for a turbine comprising a generally semi-cylindrical nozzle carrier half for extending about an axis of the turbine and having an arcuate, radially inwardly opening dovetail-shaped groove terminating at opposite ends in respective joint faces, a plurality of nozzles for the turbine, each nozzle including an airfoil and an outer base having a dovetail shape generally corresponding to the dovetail shape of the groove and received in the dovetail-shaped groove, a key slot in one of the horizontal joint faces at one end of the groove, one of the nozzles in the groove of the carrier half at the one horizontal joint face having a notch formed in the base inwardly of the one joint face, a key in the key slot secured to the carrier half and engaging in the notch of the one nozzle to retain the nozzles in the carrier half groove and a pin engaging the one nozzle to bias the one nozzle in a radial inward direction and extending
- FIG. 1 is a fragmentary perspective view of a carrier illustrating axially spaced carrier grooves for a turbine and illustrated with the nozzles stacked in the grooves;
- FIG. 2 is a perspective view of a representative nozzle disposed within the carrier grooves between end nozzles at the joint interfaces;
- FIG. 3 is a perspective view of an end nozzle and a key for retaining the nozzle at a carrier joint face
- FIG. 4 is a view similar to FIG. 3 illustrating the nozzle at the horizontal joint face with a radial loading pin inserted;
- FIG. 5 is an enlarged fragmentary view at the joint face illustrating the key in the key slot peened to the carrier shell.
- FIG. 6 is a view similar to FIG. 5 illustrating retention of the key in the slot by screws.
- a carrier for the nozzles 12 of a turbine, for example, a steam turbine.
- the carrier 10 includes upper and lower carrier halves 14 and 15 , respectively, which are joined one with the other along a horizontal joint face 16 .
- nozzles 12 are arranged in an annular array thereof at axially spaced locations along the carrier 10 .
- Each array of nozzles 12 includes a plurality of discrete nozzles 12 stacked one against the other.
- nozzles 12 When a rotor, not shown, is disposed within the lower carrier half and the carrier halves 14 and 15 are secured one to the other at the joint interface 16 , the nozzles 12 , together with airfoils or buckets on the rotor, form multiple stages of a turbine.
- each nozzle includes an airfoil 17 including an inner band 18 and a base 20 having a dovetail configuration.
- Each base 20 has opposite sides parallel to one another and, when disposed in the carrier grooves, the opposite sides are angled relative to the axis of rotation of the turbine.
- a pair of flanges 22 and 24 projecting in both axially upstream and downstream directions defining recesses 26 therebetween.
- the upper and lower carrier sections 14 and 15 respectively, are provided with generally correspondingly-shaped grooves 27 as the bases of the nozzles 12 .
- the radial outward base of each groove also has a radial outward annular recess 30 (FIG. 4).
- the nozzles 12 are stacked in the grooves one against the other in each of the upper and lower carrier halves 14 and 15 , respectively.
- the remaining nozzles of the carrier section may be inserted by locating the dovetail-shaped bases 20 of succeeding nozzles in the opposite end of the groove 27 and sliding the nozzles into abutment one with the other until the groove 27 is entirely filled.
- radial biasing pins 32 are inserted into the carrier groove from the opposite end of groove 27 .
- the pins 32 engage between the radial outer base of the groove 27 and the radial outer faces of the bases 20 of the nozzles 12 to bias the nozzles 12 radially inwardly.
- the pins 32 have a flat face on one side for engaging the nozzle base 20 and are inserted from the opposite end of the carrier groove 27 from the nozzles being inserted into the groove.
- end nozzles 13 are provided at each of the opposite ends of each groove 27 of a carrier half. It will be appreciated, however, that such end nozzle 13 and the following described retention apparatus may be provided only at one end of each groove of each carrier half with the opposite end being otherwise secured.
- the end nozzles 13 for each of the carrier halves 14 and 15 are provided with a notch 34 along the radial outer face of the base 20 of the nozzle 12 .
- the notch 34 includes an abutment face 36 which is formed generally parallel to the axis of rotation of the turbine.
- the notch 34 is essentially wedge-shaped as illustrated.
- each carrier groove 27 preferably has a similar arrangement with, however, the notch and the abutment face being formed on the opposite side of the end nozzle. That is, left and right hand end nozzles 13 are provided with the notches 34 and abutment faces 36 formed on respective opposite sides of their bases.
- a key slot 38 is formed in the horizontal joint face 16 , preferably at the end of each groove.
- the key slot 38 extends in an axial direction forward and aft of the extent of the nozzle bases 20 .
- Key slot 38 has a depth from the horizontal joint face 16 at least equal to the depth of the abutment face 36 from the joint faces when the end nozzle 13 is located at the horizontal joint face.
- a key 40 is disposed in the key slot 38 .
- the key 40 comprises an elongated rectilinear locking element which seats in the key slot 38 and bears against the abutment face 36 of the end nozzle base 20 .
- key 40 is secured in the key slot 38 , for example, by peening 41 adjacent opposite ends of the key 40 . That is, the metal of the key 40 and portions of the adjoining joint face 16 is deformed to interfere with one another and thereby secure the key in the key slot with the key butting the abutment face 36 , retaining the stacked nozzles 12 and 13 in the carrier half from displacement from the grooves.
- the key 40 may also be secured in the key slot 38 and to the carrier half by means other than peening.
- the key 40 may have bore holes for receiving screws 44 threadedly received in the base of the key slot 38 and in the carrier half.
- the final radial load pin 32 is disposed between the base of the groove and bears against the base of the end nozzle 13 to bias the end nozzle radially inwardly, similarly as the other stacked nozzles in the carrier groove.
- the radial loading pin 32 at the end joint interface does not interfere with the key 40 and key slot 38 arrangement securing the nozzles in the carrier grooves.
- the key 40 and radial pins 32 as well as the means for securing the key in the slot and preventing displacement of the nozzles from the grooves in a circumferential direction are all flush with or slightly recessed below the joint face 16 . This is significant in order to secure the joint faces of the upper and lower carrier halves to one another with appropriate sealing, not shown, and with the appropriate clearance between the adjoining end nozzles at each of the joint faces.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The present invention relates to apparatus for retaining nozzles stacked one against the other in a groove of a carrier of a turbine and particularly relates to a turbine nozzle retention apparatus for retaining the nozzles in carrier grooves at the horizontal joint faces between upper and lower carrier halves which does not interfere with radially loading the nozzles.
- In turbines, for example, steam turbines, there is provided a carrier for the axially spaced, circumferential arrays of nozzles. The carrier typically includes carrier halves which extend arcuately 180° and are secured to one another at a horizontal joint face to form a 360° array of nozzles at each axial stage position. While various techniques have been employed to retain the nozzles within the grooves of the carrier, typically the nozzles comprise an airfoil having a radial outer dovetail-shaped base for reception in a generally correspondingly dovetail-shaped groove in the carrier. Generally, the opposite side faces of each base of the nozzles are angled relative to the axis of the turbine enabling the base to accommodate the angularity of the airfoil. When the nozzles are installed in each carrier half groove, the nozzle bases are stacked one against the other within the grooves forming a semi-circular array of nozzles. The end nozzle at each horizontal joint face, prior to securing the carrier halves to one another, projects outwardly of the joint face. Radial loading pins are also provided for each nozzle. Each pin is disposed between the base of the nozzle and the base of the groove biasing the nozzle radially inwardly. A clearance between adjacent end nozzles across the horizontal joint of the upper and lower carrier halves is necessary when the carrier halves are secured to one another. Accordingly, there is a need for a retaining device at the horizontal joint face for retaining the nozzles within the carrier half groove and which does not interfere with the radial loading of the nozzles.
- In accordance with a preferred embodiment of the present invention, there is provided a turbine nozzle retention apparatus for retaining nozzles at the joint interface of each carrier half that does not interfere with but works in conjunction with the radial loading device, e.g., the radial loading pins. For example, each carrier half has a plurality of axially spaced grooves having semi-circular configurations about the carrier half. Each groove has a dovetail configuration. Nozzles having a correspondingly dovetail-shaped radially outer base are inserted into the carrier groove and stacked one against the other to form an arcuate array of nozzles. At each joint interface where a clearance between adjacent nozzles of the upper and lower carrier halves is required, each end nozzle projects beyond its associated joint face.
- To retain the end nozzle in the horizontal joint face while accommodating a radial loading pin, the nozzle base of each end nozzle includes a notch formed along its radial outward face and which notch includes an abutment face extending in an axial direction. A key slot is formed in each carrier half at each joint face and lies in alignment with the notch and the abutment face. An elongated key is disposed in the notch in engagement against the abutment face of the nozzle base. A radial loading pin is disposed in a recess in the outermost wall of the carrier groove and engages the portion of the nozzle base which is not notched to provide the radial inward bias to the end nozzle. The key is secured to the carrier half and in the key slot at the joint face, for example, by peening between the joint face and the key. Alternatively, the key may be retained in the key slot by one or more screws having heads recessed below the joint interface. The key therefore prevents circumferential movement of the nozzle from the carrier groove while the radial loading pin biases the nozzle radially inwardly. It will be appreciated that the end nozzle and retainer key of the present invention is provided at at least one of two horizontal joint faces for each groove of each carrier half. Preferably, all four horizontal joint faces of the two carrier halves forming each annular groove of the carrier are provided with the nozzle retention apparatus hereof.
- In a preferred embodiment according to the present invention, there is provided nozzle retention apparatus for a turbine comprising a generally semi-cylindrical nozzle carrier half for extending about an axis of the turbine and having an arcuate, radially inwardly opening, shaped groove terminating at opposite ends in respective joint faces, a plurality of nozzles for the turbine, each nozzle including an airfoil and an outer base having a shape generally corresponding to the shape of the groove and received in the groove, a key slot in one of the horizontal joint faces at one end of the groove, one of the nozzles in the groove of the carrier half at the one horizontal joint face extending circumferentially beyond the joint face and having a notch formed in the base thereof extending inwardly of the one joint face and a key in the key slot secured to the carrier half and engaging in the notch of the one nozzle to retain the nozzles in the carrier half groove.
- In a further preferred embodiment according to the present invention, there is provided nozzle retention apparatus for a turbine comprising a generally semi-cylindrical nozzle carrier half for extending about an axis of the turbine and having an arcuate, radially inwardly opening dovetail-shaped groove terminating at opposite ends in respective joint faces, a plurality of nozzles for the turbine, each nozzle including an airfoil and an outer base having a dovetail shape generally corresponding to the dovetail shape of the groove and received in the dovetail-shaped groove, a key slot in one of the horizontal joint faces at one end of the groove, one of the nozzles in the groove of the carrier half at the one horizontal joint face having a notch formed in the base inwardly of the one joint face, a key in the key slot secured to the carrier half and engaging in the notch of the one nozzle to retain the nozzles in the carrier half groove and a pin engaging the one nozzle to bias the one nozzle in a radial inward direction and extending between the key and a radially inwardly facing surface along a base of the groove.
- FIG. 1 is a fragmentary perspective view of a carrier illustrating axially spaced carrier grooves for a turbine and illustrated with the nozzles stacked in the grooves;
- FIG. 2 is a perspective view of a representative nozzle disposed within the carrier grooves between end nozzles at the joint interfaces;
- FIG. 3 is a perspective view of an end nozzle and a key for retaining the nozzle at a carrier joint face;
- FIG. 4 is a view similar to FIG. 3 illustrating the nozzle at the horizontal joint face with a radial loading pin inserted;
- FIG. 5 is an enlarged fragmentary view at the joint face illustrating the key in the key slot peened to the carrier shell; and
- FIG. 6 is a view similar to FIG. 5 illustrating retention of the key in the slot by screws.
- Referring now to the drawings, particularly to FIG. 1, there is illustrated a carrier, generally designated10, for the
nozzles 12 of a turbine, for example, a steam turbine. Thecarrier 10 includes upper andlower carrier halves horizontal joint face 16. As illustrated,nozzles 12 are arranged in an annular array thereof at axially spaced locations along thecarrier 10. Each array ofnozzles 12 includes a plurality ofdiscrete nozzles 12 stacked one against the other. When a rotor, not shown, is disposed within the lower carrier half and thecarrier halves joint interface 16, thenozzles 12, together with airfoils or buckets on the rotor, form multiple stages of a turbine. - As illustrated in FIG. 2, each nozzle includes an
airfoil 17 including aninner band 18 and abase 20 having a dovetail configuration. Eachbase 20 has opposite sides parallel to one another and, when disposed in the carrier grooves, the opposite sides are angled relative to the axis of rotation of the turbine. In the illustrated form of the dovetail-shaped base of each nozzle, there is provided a pair offlanges directions defining recesses 26 therebetween. The upper andlower carrier sections shaped grooves 27 as the bases of thenozzles 12. The radial outward base of each groove also has a radial outward annular recess 30 (FIG. 4). - Typically, the
nozzles 12 are stacked in the grooves one against the other in each of the upper andlower carrier halves shaped bases 20 of succeeding nozzles in the opposite end of thegroove 27 and sliding the nozzles into abutment one with the other until thegroove 27 is entirely filled. As the nozzles are inserted,radial biasing pins 32 are inserted into the carrier groove from the opposite end ofgroove 27. Thepins 32 engage between the radial outer base of thegroove 27 and the radial outer faces of thebases 20 of thenozzles 12 to bias thenozzles 12 radially inwardly. Thepins 32 have a flat face on one side for engaging thenozzle base 20 and are inserted from the opposite end of thecarrier groove 27 from the nozzles being inserted into the groove. Once the nozzles are stacked in the groove, the final or end nozzle 13 (FIG. 3) for each carrier section at thehorizontal joint face 16 is specifically configured for securement at the horizontal joint, as well as to avoid interference with and facilitate radial loading of theend nozzle 13 in a radial inward direction. - Preferably,
end nozzles 13, as described herein, are provided at each of the opposite ends of eachgroove 27 of a carrier half. It will be appreciated, however, thatsuch end nozzle 13 and the following described retention apparatus may be provided only at one end of each groove of each carrier half with the opposite end being otherwise secured. To accomplish the foregoing, and referring to FIG. 3, theend nozzles 13 for each of thecarrier halves notch 34 along the radial outer face of thebase 20 of thenozzle 12. Thenotch 34 includes anabutment face 36 which is formed generally parallel to the axis of rotation of the turbine. Thus, thenotch 34 is essentially wedge-shaped as illustrated. When theend nozzles 13 are disposed in thegrooves 27 at the joint faces, the abutment faces 36 lie below the horizontal joint faces 16 and a portion of eachnozzle base 20 projects above the correspondinglyhorizontal joint face 16. Theend nozzle 13 at the opposite end of eachcarrier groove 27 preferably has a similar arrangement with, however, the notch and the abutment face being formed on the opposite side of the end nozzle. That is, left and righthand end nozzles 13 are provided with thenotches 34 andabutment faces 36 formed on respective opposite sides of their bases. - Prior to assembly of the
nozzles carrier shell grooves 27, akey slot 38 is formed in thehorizontal joint face 16, preferably at the end of each groove. Thekey slot 38 extends in an axial direction forward and aft of the extent of thenozzle bases 20.Key slot 38 has a depth from thehorizontal joint face 16 at least equal to the depth of theabutment face 36 from the joint faces when theend nozzle 13 is located at the horizontal joint face. As illustrated in FIG. 4, akey 40 is disposed in thekey slot 38. The key 40 comprises an elongated rectilinear locking element which seats in thekey slot 38 and bears against theabutment face 36 of theend nozzle base 20. - As illustrated in FIG. 5, key40 is secured in the
key slot 38, for example, by peening 41 adjacent opposite ends of the key 40. That is, the metal of the key 40 and portions of the adjoiningjoint face 16 is deformed to interfere with one another and thereby secure the key in the key slot with the key butting theabutment face 36, retaining thestacked nozzles key slot 38 and to the carrier half by means other than peening. For example, and as illustrated in FIG. 6, the key 40 may have bore holes for receivingscrews 44 threadedly received in the base of thekey slot 38 and in the carrier half. - To radially load each
end nozzle 13, the finalradial load pin 32 is disposed between the base of the groove and bears against the base of theend nozzle 13 to bias the end nozzle radially inwardly, similarly as the other stacked nozzles in the carrier groove. Thus, theradial loading pin 32 at the end joint interface does not interfere with the key 40 andkey slot 38 arrangement securing the nozzles in the carrier grooves. - It will be appreciated that the key40 and
radial pins 32 as well as the means for securing the key in the slot and preventing displacement of the nozzles from the grooves in a circumferential direction are all flush with or slightly recessed below thejoint face 16. This is significant in order to secure the joint faces of the upper and lower carrier halves to one another with appropriate sealing, not shown, and with the appropriate clearance between the adjoining end nozzles at each of the joint faces. - While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (17)
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/284,211 US6722848B1 (en) | 2002-10-31 | 2002-10-31 | Turbine nozzle retention apparatus at the carrier horizontal joint face |
KR1020030076160A KR100818825B1 (en) | 2002-10-31 | 2003-10-30 | Turbine nozzle retention apparatus at the carrier horizontal joint face |
DE10350946A DE10350946B4 (en) | 2002-10-31 | 2003-10-30 | Turbine nozzle holding device on the horizontal connecting surface of the carrier |
CZ20032963A CZ302360B6 (en) | 2002-10-31 | 2003-10-30 | Turbine nozzle retention apparatus at carrier horizontal joint face |
JP2003369785A JP4439239B2 (en) | 2002-10-31 | 2003-10-30 | Turbine nozzle holding device at horizontal joint surface of support |
CNB2003101044865A CN100343490C (en) | 2002-10-31 | 2003-10-30 | Turbine nozzle retention apparatus at the carrier horizontal joint face |
RU2003132118/06A RU2331775C2 (en) | 2002-10-31 | 2003-10-31 | Device to locate turbine nozzle arranged on holder horizontal coupling surface (versions) |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/284,211 US6722848B1 (en) | 2002-10-31 | 2002-10-31 | Turbine nozzle retention apparatus at the carrier horizontal joint face |
Publications (2)
Publication Number | Publication Date |
---|---|
US6722848B1 US6722848B1 (en) | 2004-04-20 |
US20040086383A1 true US20040086383A1 (en) | 2004-05-06 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/284,211 Expired - Fee Related US6722848B1 (en) | 2002-10-31 | 2002-10-31 | Turbine nozzle retention apparatus at the carrier horizontal joint face |
Country Status (7)
Country | Link |
---|---|
US (1) | US6722848B1 (en) |
JP (1) | JP4439239B2 (en) |
KR (1) | KR100818825B1 (en) |
CN (1) | CN100343490C (en) |
CZ (1) | CZ302360B6 (en) |
DE (1) | DE10350946B4 (en) |
RU (1) | RU2331775C2 (en) |
Cited By (5)
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US20100172755A1 (en) * | 2009-01-06 | 2010-07-08 | General Electric Company | Method and apparatus for insuring proper installation of stators in a compressor case |
US20140064945A1 (en) * | 2012-09-04 | 2014-03-06 | General Electric Company | Stator Vane Assembly |
EP2798177A4 (en) * | 2011-12-29 | 2015-07-01 | Elliott Co | Hot gas expander inlet casing assembly and method |
EP3228825A1 (en) * | 2016-04-06 | 2017-10-11 | General Electric Company | Steam turbine drum nozzle having alignment feature and steam turbine |
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US6908279B2 (en) * | 2003-11-25 | 2005-06-21 | General Electric Company | Method of installing stationary blades of a turbine and turbine structure having a radial loading pin |
US7410345B2 (en) * | 2005-04-11 | 2008-08-12 | General Electric Company | Turbine nozzle retention key |
US20060245923A1 (en) * | 2005-04-27 | 2006-11-02 | General Electric Company | Arcuate nozzle segment and related method of manufacture |
US7645117B2 (en) * | 2006-05-05 | 2010-01-12 | General Electric Company | Rotary machines and methods of assembling |
US9051845B2 (en) * | 2012-01-05 | 2015-06-09 | General Electric Company | System for axial retention of rotating segments of a turbine |
US20140072419A1 (en) * | 2012-09-13 | 2014-03-13 | Manish Joshi | Rotary machines and methods of assembling |
US9828866B2 (en) | 2013-10-31 | 2017-11-28 | General Electric Company | Methods and systems for securing turbine nozzles |
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US905437A (en) * | 1908-03-20 | 1908-12-01 | Halfdan Birger Karlin | Elastic-fluid turbine. |
IT1167241B (en) * | 1983-10-03 | 1987-05-13 | Nuovo Pignone Spa | IMPROVED SYSTEM FOR FIXING STATOR NOZZLES TO THE CASE OF A POWER TURBINE |
US4819313A (en) * | 1988-06-03 | 1989-04-11 | Westinghouse Electric Corp. | Method of salvaging stationary blades of a steam turbine |
US5259727A (en) * | 1991-11-14 | 1993-11-09 | Quinn Francis J | Steam turbine and retrofit therefore |
DE19547653C2 (en) * | 1995-12-20 | 1999-08-19 | Abb Patent Gmbh | Guide device for a turbine with a guide vane carrier and method for producing this guide device |
DE19654471B4 (en) * | 1996-12-27 | 2006-05-24 | Alstom | Rotor of a turbomachine |
EP1018594B1 (en) * | 1999-01-06 | 2006-12-27 | General Electric Company | Wheelspace windage cover plate for a turbine |
US6224332B1 (en) * | 1999-05-14 | 2001-05-01 | General Electric Co. | Apparatus and methods for installing, removing and adjusting an inner turbine shell section relative to an outer turbine shell section |
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2002
- 2002-10-31 US US10/284,211 patent/US6722848B1/en not_active Expired - Fee Related
-
2003
- 2003-10-30 DE DE10350946A patent/DE10350946B4/en not_active Expired - Fee Related
- 2003-10-30 JP JP2003369785A patent/JP4439239B2/en not_active Expired - Fee Related
- 2003-10-30 CZ CZ20032963A patent/CZ302360B6/en not_active IP Right Cessation
- 2003-10-30 KR KR1020030076160A patent/KR100818825B1/en not_active IP Right Cessation
- 2003-10-30 CN CNB2003101044865A patent/CN100343490C/en not_active Expired - Fee Related
- 2003-10-31 RU RU2003132118/06A patent/RU2331775C2/en not_active IP Right Cessation
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100172755A1 (en) * | 2009-01-06 | 2010-07-08 | General Electric Company | Method and apparatus for insuring proper installation of stators in a compressor case |
US8047778B2 (en) * | 2009-01-06 | 2011-11-01 | General Electric Company | Method and apparatus for insuring proper installation of stators in a compressor case |
EP2798177A4 (en) * | 2011-12-29 | 2015-07-01 | Elliott Co | Hot gas expander inlet casing assembly and method |
US9863321B2 (en) | 2011-12-29 | 2018-01-09 | Elliott Company | Hot gas expander inlet casing assembly and method |
US20140064945A1 (en) * | 2012-09-04 | 2014-03-06 | General Electric Company | Stator Vane Assembly |
US9243509B2 (en) * | 2012-09-04 | 2016-01-26 | General Electric Company | Stator vane assembly |
EP3228825A1 (en) * | 2016-04-06 | 2017-10-11 | General Electric Company | Steam turbine drum nozzle having alignment feature and steam turbine |
US10287903B2 (en) | 2016-04-06 | 2019-05-14 | General Electric Company | Steam turbine drum nozzle having alignment feature, related assembly, steam turbine and storage medium |
EP3555426A4 (en) * | 2016-12-19 | 2020-09-23 | General Electric Company | Rotary machine and nozzle assembly therefor |
Also Published As
Publication number | Publication date |
---|---|
CN100343490C (en) | 2007-10-17 |
CZ302360B6 (en) | 2011-04-06 |
KR20040038816A (en) | 2004-05-08 |
JP2004150434A (en) | 2004-05-27 |
RU2331775C2 (en) | 2008-08-20 |
US6722848B1 (en) | 2004-04-20 |
DE10350946B4 (en) | 2009-10-08 |
DE10350946A1 (en) | 2004-05-13 |
RU2003132118A (en) | 2005-05-10 |
CZ20032963A3 (en) | 2004-10-13 |
JP4439239B2 (en) | 2010-03-24 |
CN1500970A (en) | 2004-06-02 |
KR100818825B1 (en) | 2008-04-01 |
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