US3849023A - Stator assembly - Google Patents
Stator assembly Download PDFInfo
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- US3849023A US3849023A US00374518A US37451873A US3849023A US 3849023 A US3849023 A US 3849023A US 00374518 A US00374518 A US 00374518A US 37451873 A US37451873 A US 37451873A US 3849023 A US3849023 A US 3849023A
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- Prior art keywords
- shroud
- sectors
- stator
- compressor
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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
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
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- 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
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
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- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- This invention relates to a stator vane assembly and, more particularly, to a stator vane assembly for an axial flow compressor wherein a plurality of axially spaced apart rows of stator vanes having inner shrouds are interdigitated between a plurality of axially spaced apart rows of rotor blades.
- ln axial flow compressors which may be of the type commonly utilized in gas turbine engines, there is generally included a rotor from which extend a number of axially spaced apart rows of rotor blades. Rows of axially spaced apart stator vanes are also provided and extend radially inward from the compressor casing between the rows of rotor blades.
- an inner shroud which is retained at the inner radial ends of each row of stator vanes. Each shroud is supported entirely by a row of stator vanes and may be arranged to sealingly engage a plurality of revolving teeth formed integral to the compressor rotor.
- Difficulty may arise as a direct result of the means utilized to fasten the inner shroud to the stator vanes. ln the past, it has often been necessary to use retaining bolts or clips which may loosen during engine operation and thereby enter the compressor flowpath, causing severe damage. In a gas turbine engine, the use of retaining bolts or clips further adds to the weight of the compressor and thereby reduces the overall thrust to weight ratio of the engine. Also, it has generally been necessary to make shrouds from metal which again unduly adds to the weight of the compressor.
- stator vane assembly wherein the inner shroud may be readily fastened to the inner radial ends of the stator vanes without the use of retaining bolts or clips.
- a stator assembly includes an outer casing longitudinally split into at least two sectors wherein each sector has a dovetail groove around the inside surface thereof. There is also included an inner segmented shroud longitudinally split into at least two sectors, each of which has a plurality of circumferentially spaced apart pockets in the outer surface thereof wherein each pocket is undercut at one end.
- a plurality of stator vanes extends radially between the shroud and casing with each vane having an inner root portion which includes an integral heel portion and an integrally extending toe portion for engaging the undercut end of a respective shroud pocket.
- Each vane also includes an outer platform from which extend forward and aft tangs which engage the dovetail groove.
- FIG. ll is a side view, partly in cross-section ⁇ of a gas turbine engine embodying the stator assembly of this invention.
- FIG. 2 is a crossasectional view of a portion of a com pressor embodying the stator assembly of this invention.
- FIG. 3 is a crossesectional view taken along the line 3-3 in FIG. 2.
- FIG. 4 is an enlarged cross-sectional view taken along the line 4-4 in FIG. 3.
- FIG. 5 is a cross-sectional View taken along the line 5 5 of FIG. 2.
- FIG. l there is shown a gas turbine engine 10 having an outer casing l2 open at one end to provide an inlet 14. Ambient air enters the inlet 14 and is compressed by a compressor 16 which may be of the axial flow type. Compressor 16 includes a rotor 18 from which extend a number of axially spaced apart rows of rotor blades 20 interdigitated between rows of axially spaced apart stator vanes 22. Pressurized air is discharged from the compressor 16 through a plurality of circumferentially spaced apart outlet guide vanes 24 whereupon the compressed air is diffused prior to entering a combustion chamber 26.
- Combustion chamber 26 is defined by a combustion liner 28 and receives an inlet flow of fuel through a plurality of circumferentially spaced apart fuel nozzles 30.
- the high pressure air and fuel mixture is ignited to produce a high energy gas stream which exits from the combustion chamber 26 through a nozzle diaphragm 32.
- High energy gas from the nozzle diaphragm 32 drives a turbine 34 which connects to the compressor rotor 18 through a shaft 36.
- the gas turbine engine 10 so far described could be utilized as a gas generator in combination with a power turbine (not shown) to form either a turboprop, turbofan or a turboshaft engine in a manner well known to the gas turbine art.
- Within the engine 1() there is also disclosed a frame 38 within which the shaft 36 is journalled for rotation by a forward bearing 40 and aft bearing 40'.
- casing 12 is longitudinally split along two sectors which are con nected by a plurality of axially spaced apart locking bolts 13.
- Locking bolts 13 pass through aligned holes in two pairs of integral flanges ll5, 15 and 17, 17' which are spaced 180 apart around the compressor casing l2.
- Lock nuts 13' may be provided to threadably engage lock bolts 13.
- FIG. 2 there is shown a portion of the compressor 16 including a forward rotor disc 42 and an aft rotor disc 44, both of which are interconnected to simultaneously rotate as an integral part of the compressor rotor 18.
- the compressor rotor 18 may include more or less rotor discs depending upon the specific design requirements of the gas turbine engine l0.
- a plurality of crcumferentially spaced apart blades are disposed about the periphery of the forward rotor disc 42 wherein each blade 20 includes a root portion 46 for attachment to the rotor disc 42 as is well known to the compressor art.
- a plurality of circumferentially spaced apart blades 20' are also disposed about the periphery of the aft rotor disc 44 wherein each blade includes a root portion 48 for attachment to the rotor disc 44.
- the outer tips of the blades are respectively circumscribed by shrouds 50 and 52, which may be of the honeycomb type.
- stator vanes 22 Intermediate the forward rotor disc 42 and aft rotor disc 44, there is provided a row of crcumferentially spaced apart stator vanes 22, each of which includes an outer platform 66, from which extend forward and aft tangs 68, 68', which engage a dovetail groove 70 around the inner surface of the casing 12.
- an inner segmented shroud 56 which may operate as the stator member of a labyrinth type seal by engaging a plurality of revolving teeth 57 formed integral to the compressor rotor 18.
- Each stator vane 22 includes a root portion S4 formed in the manner of a foot so as to have an integral heel portion 58 together with an integrally extending toe or tang portion 60.
- Shroud 56 includes a plurality of circumferentially spaced apart pockets 62 which are undercut on one end 64 to accommodate insertion of the individual root portions 54.
- each stator vane 22 is first tipped or rotated in relation to the center axis of the shroud in order to insert the tang portion 64 of the root 54 into the pocket 62 so as to engage the undercut surface 64 as illustrated by the phantom lines.
- Each stator vane 22 is then rotated about the undercut surface 64 so as to bring the heel portion 58 of the root 54 into engagement with the pocket 62.
- the fit between the root S4 and pocket 62 may have a controlled clearance upon full engagement of the root within the pocket.
- the inner shroud S6 has also been longitudinally split into two 180 sectors.
- individual stator vanes 22 are first inserted into respective pockets 62 in the inner shroud segments 56. Once the stator vanes 22 have been arranged in crcumferentially spaced apart relation by insertion within respective pockets 62 in shroud segments 56, each shroud segment, together with its associated stator vanes, is then slid crcumferentially into engagement with the dovetail groove 70 in casing l2.
- splitting the casing l2 provides access to the dovetail groove 70, thereby permitting circumferential insertion of the individual stator vane outer platforms 66 within the dovetail groove.
- the inner segmented shroud 56 is positively restrained from detaching from the stator vane root portions 54.
- the dovetail groove 70 prohibits simultaneous rotation of the stator vane outer platforms 66 and thereby positively precludes detachment of the inner shroud segments 56 from the stator vanes 22 after insertion within the dovetail groove '70.
- the shroud 56 may be made relatively thin and lightweight and still remain radially constrained for close clearance with the rotor 18.
- the shroud S6 positively engages the inner radial ends of the stator vanes 22 constraining the stator vanes from rotating or flexing about their radial axes.
- the engine l0 may be disassembled by reversing the above described process. First the connecting bolts 13 are loosened in order to separate the two sectors of the engine casing 12. Then the stator vane outer platforms 66 are crcumferentially slid out of engagement with the dovetail groove 70, after which each stator vane 22 may be rotated out of engagement with its respective shroud pocket 62.
- the inner shroud 56 has been illustrated in two segments, it is to be understood that the arc length of each shroud is not so limited and may, in fact, be less than 180.
- the segmented shroud S6 which may be fastened to the stator vanes 22 without additional hardware such as locking bolts and nuts. Such hardware unduly adds to the weight of the engine and may loosen during engine operation, damaging other compressor components.
- the segmented shroud 56 may also be produced economically by injection molding wherein the molded segments may be formed of lightweight plastic.
- a stator assembly comprising:
- an inner segmented shroud longitudinally split into at least two sectors, each of which has a plurality of crcumferentially spaced apart pockets in the outer surface thereof wherein each pocket is undercut at one end, and
- each vane having:
- an inner root portion which includes an integral heel portion and an integrally extending toe portion for engaging the undercut end of a respective shroud pocket, and an outer platform from which extend forward and aft tangs which engage the dovetail groove.
- stator assembly of claim 1 wherein the casing is longitudinally split along two 180 sectors and the sectors are connected by a plurality of axially spaced apart locking bolts which pass through aligned holes in two pairs of integral flanges which are spaced 180 apart around the casing.
- each stator vane may be individually inserted into a respective pocket in the shroud by first rotating the stator vane in relation to the center axis of the shoud in order to insert the tang portion of the root into the pocket so as to engage the undercut surface whereupon the stator vane may be rotated about the undercut surface so as to bring the heel portion of the root into engagement with the pocket.
- a compressor comprising: an outer casing longitudinally split into at least two sectors and having at least one dovetail groove around the inside surface thereof; a rotor from which extend at least two axially spaced apart rows of rotor blades; at least one inner segmented shroud longitudinally split into at least two sectors which are interposed between two rows of rotor blades wherein the sectors each include a plurality of circumferentially spaced apart pockets in the outer surface thereof, each of which is undercut at one end, and a plurality of stator varies extending radially between the shroud and casing with each vane having: an inner root portion including an integral heel portion and an integrally extending toe portion for en gaging the undercut end of a respective shroud pocket, and an outer platform from which extend forward and aft tangs which engage the dovetail groove.
- each stator vane may be individually inserted into a respective pocket in the shroud by first rotating the stator vane in relation to the center axis of the shroud in order to insert the tang portion of the root into the pocket so as to engage the undercut surface whereupon the stator vane may be rotated about the undercut surface so as to bring the heel portion of the root into engagement with the pocket.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Rotary Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A stator assembly for a compressor includes a plurality of circumferentially spaced apart vanes positively retained at the outer radial ends by engagement within a split casing wherein the vanes further include root portions at their inner radial ends for respective engagement within pocket formed around an inner segmented shroud member.
Description
niteii States ateiit 119i ii i1 3,849,23 llompas [45] Nov. 19, M74
[54] STAT/OR ASSEMBLY 2,812,159 11/1957 Krebs 415/172 A 3,501,246 3/1970 Hickey 415/170 R Inventor. Nlcholas Klompas, Lyl'lneld, Mass. Steinack et all R [73] Assignee: General Electric Company, Lynn, 3,547,455 12/1970 Daum 415/174 Mass- FOREIGN PATENTS OR APPLICATIONS [22] Filed: June 28, 1973 474,361 3/1929 Germany 415/174 [21] AppL NO': 374518 Primary Examne-Henry F. Raduazo [52] US. Cl. 4l5/l70, 415/217 [57] ABSTRACT [51] Int. Cl. F0411 29/08 [58] riem i1 Search 415/169, 171, 172 A, 173, .A Stato'. assembly ff a Compressor "Cudes a P'lfa 415/174 170 R 217 R. H6/215 ity of circumferentially spaced apart vanes positively retained at the outer radial ends by engagement within [56] References Cited a split casinghvi/herein thed'vnesdfuither include root portions at t eir inner ra 1a en s or respective en- UNITED STATES PATENTS gagement within pocket formed around an inner seg- LapaC al. mented Shroud member. 1,273,634 7/1918 London 415/170 R 1,534,415 4/1925 schmidi 4115/215 9 Claims, 5 Drawing Figures sTAToR ASSEMBLY The invention herein described was made in the course of or under a contract or subcontract thereunder (or grant) with the Department of the Air Force.
BACKGROUND OF THE INVENTION This invention relates to a stator vane assembly and, more particularly, to a stator vane assembly for an axial flow compressor wherein a plurality of axially spaced apart rows of stator vanes having inner shrouds are interdigitated between a plurality of axially spaced apart rows of rotor blades. l
ln axial flow compressors, which may be of the type commonly utilized in gas turbine engines, there is generally included a rotor from which extend a number of axially spaced apart rows of rotor blades. Rows of axially spaced apart stator vanes are also provided and extend radially inward from the compressor casing between the rows of rotor blades. In order to prevent airflow leakage around each row of stator vanes, there is generally included an inner shroud which is retained at the inner radial ends of each row of stator vanes. Each shroud is supported entirely by a row of stator vanes and may be arranged to sealingly engage a plurality of revolving teeth formed integral to the compressor rotor.
Difficulty may arise as a direct result of the means utilized to fasten the inner shroud to the stator vanes. ln the past, it has often been necessary to use retaining bolts or clips which may loosen during engine operation and thereby enter the compressor flowpath, causing severe damage. In a gas turbine engine, the use of retaining bolts or clips further adds to the weight of the compressor and thereby reduces the overall thrust to weight ratio of the engine. Also, it has generally been necessary to make shrouds from metal which again unduly adds to the weight of the compressor.
Therefore, it is a primary object of this invention to provide a stator vane assembly wherein the inner shroud may be readily fastened to the inner radial ends of the stator vanes without the use of retaining bolts or clips.
It is a further object of this invention to provide a stator vane assembly wherein the inner shroud may be molded from a lightweight plastic in order to reduce the overall weight of the compressor.
SUMMARY OF THE INVENTION A stator assembly includes an outer casing longitudinally split into at least two sectors wherein each sector has a dovetail groove around the inside surface thereof. There is also included an inner segmented shroud longitudinally split into at least two sectors, each of which has a plurality of circumferentially spaced apart pockets in the outer surface thereof wherein each pocket is undercut at one end. A plurality of stator vanes extends radially between the shroud and casing with each vane having an inner root portion which includes an integral heel portion and an integrally extending toe portion for engaging the undercut end of a respective shroud pocket. Each vane also includes an outer platform from which extend forward and aft tangs which engage the dovetail groove.
DESCRIPTION OF THE DRAWINGS While the specification concludes with claims distinctly claiming and particularly pointing out the invention described herein, it is believed that the invention will be more readily understood by reference to the discussion below and the accompanying drawings in which:
FIG. ll is a side view, partly in cross-section` of a gas turbine engine embodying the stator assembly of this invention.
FIG. 2 is a crossasectional view of a portion of a com pressor embodying the stator assembly of this invention.
FIG. 3 is a crossesectional view taken along the line 3-3 in FIG. 2.
FIG. 4 is an enlarged cross-sectional view taken along the line 4-4 in FIG. 3.
FIG. 5 is a cross-sectional View taken along the line 5 5 of FIG. 2.
DESCRIPTION OF THE PREFERRED EMBODIMENT Referring to FIG. l, there is shown a gas turbine engine 10 having an outer casing l2 open at one end to provide an inlet 14. Ambient air enters the inlet 14 and is compressed by a compressor 16 which may be of the axial flow type. Compressor 16 includes a rotor 18 from which extend a number of axially spaced apart rows of rotor blades 20 interdigitated between rows of axially spaced apart stator vanes 22. Pressurized air is discharged from the compressor 16 through a plurality of circumferentially spaced apart outlet guide vanes 24 whereupon the compressed air is diffused prior to entering a combustion chamber 26. Combustion chamber 26 is defined by a combustion liner 28 and receives an inlet flow of fuel through a plurality of circumferentially spaced apart fuel nozzles 30. The high pressure air and fuel mixture is ignited to produce a high energy gas stream which exits from the combustion chamber 26 through a nozzle diaphragm 32. High energy gas from the nozzle diaphragm 32 drives a turbine 34 which connects to the compressor rotor 18 through a shaft 36. It will thus be appreciated that the gas turbine engine 10 so far described could be utilized as a gas generator in combination with a power turbine (not shown) to form either a turboprop, turbofan or a turboshaft engine in a manner well known to the gas turbine art. Within the engine 1() there is also disclosed a frame 38 within which the shaft 36 is journalled for rotation by a forward bearing 40 and aft bearing 40'.
As best seen by referring to FIG. 5, casing 12 is longitudinally split along two sectors which are con nected by a plurality of axially spaced apart locking bolts 13. Locking bolts 13 pass through aligned holes in two pairs of integral flanges ll5, 15 and 17, 17' which are spaced 180 apart around the compressor casing l2. Lock nuts 13' may be provided to threadably engage lock bolts 13.
Referring now to FIG. 2, there is shown a portion of the compressor 16 including a forward rotor disc 42 and an aft rotor disc 44, both of which are interconnected to simultaneously rotate as an integral part of the compressor rotor 18. It should be readily appreciated that the compressor rotor 18 may include more or less rotor discs depending upon the specific design requirements of the gas turbine engine l0. A plurality of crcumferentially spaced apart blades are disposed about the periphery of the forward rotor disc 42 wherein each blade 20 includes a root portion 46 for attachment to the rotor disc 42 as is well known to the compressor art. In like manner, a plurality of circumferentially spaced apart blades 20' are also disposed about the periphery of the aft rotor disc 44 wherein each blade includes a root portion 48 for attachment to the rotor disc 44. ln order to prevent air flow leakage around the blades 20 and 20', the outer tips of the blades are respectively circumscribed by shrouds 50 and 52, which may be of the honeycomb type.
Intermediate the forward rotor disc 42 and aft rotor disc 44, there is provided a row of crcumferentially spaced apart stator vanes 22, each of which includes an outer platform 66, from which extend forward and aft tangs 68, 68', which engage a dovetail groove 70 around the inner surface of the casing 12. In order to prevent air flow leakage around the stator vanes 22, there is provided an inner segmented shroud 56 which may operate as the stator member of a labyrinth type seal by engaging a plurality of revolving teeth 57 formed integral to the compressor rotor 18. Each stator vane 22 includes a root portion S4 formed in the manner of a foot so as to have an integral heel portion 58 together with an integrally extending toe or tang portion 60. Shroud 56 includes a plurality of circumferentially spaced apart pockets 62 which are undercut on one end 64 to accommodate insertion of the individual root portions 54.
Referring now to FIG. 4, the manner of insertion for each individual root portion 54 within a corresponding pocket 62 may be more readily understood. Each stator vane 22 is first tipped or rotated in relation to the center axis of the shroud in order to insert the tang portion 64 of the root 54 into the pocket 62 so as to engage the undercut surface 64 as illustrated by the phantom lines. Each stator vane 22 is then rotated about the undercut surface 64 so as to bring the heel portion 58 of the root 54 into engagement with the pocket 62. The fit between the root S4 and pocket 62 may have a controlled clearance upon full engagement of the root within the pocket.
Referring now to FIG. 5, it can be seen that the inner shroud S6 has also been longitudinally split into two 180 sectors. In order to assemble engine 10, individual stator vanes 22 are first inserted into respective pockets 62 in the inner shroud segments 56. Once the stator vanes 22 have been arranged in crcumferentially spaced apart relation by insertion within respective pockets 62 in shroud segments 56, each shroud segment, together with its associated stator vanes, is then slid crcumferentially into engagement with the dovetail groove 70 in casing l2. As is readily apparent, splitting the casing l2 provides access to the dovetail groove 70, thereby permitting circumferential insertion of the individual stator vane outer platforms 66 within the dovetail groove. Once all the stator vane outer platforms 66 have been inserted within the dovetail groove 70, it will be appreciated that the inner segmented shroud 56 is positively restrained from detaching from the stator vane root portions 54. In order for the shroud 56 to detach from the stator vane root portions 54 it would be necessary for all the stator vanes 22 to simultaneously rotate about a plane normal to the center axis of the shroud 56. As is readily apparent, however, the dovetail groove 70 prohibits simultaneous rotation of the stator vane outer platforms 66 and thereby positively precludes detachment of the inner shroud segments 56 from the stator vanes 22 after insertion within the dovetail groove '70. As is readily apparent, the shroud 56 may be made relatively thin and lightweight and still remain radially constrained for close clearance with the rotor 18. In addition, the shroud S6 positively engages the inner radial ends of the stator vanes 22 constraining the stator vanes from rotating or flexing about their radial axes. Once the individual sectors have been assembled, as shown in FIG. 5, it is a simple matter to insert locking bolts 13 through flanges l5, l5' and 17, 17' respectively in order to connect the two casing sectors.
The engine l0 may be disassembled by reversing the above described process. First the connecting bolts 13 are loosened in order to separate the two sectors of the engine casing 12. Then the stator vane outer platforms 66 are crcumferentially slid out of engagement with the dovetail groove 70, after which each stator vane 22 may be rotated out of engagement with its respective shroud pocket 62. Although the inner shroud 56 has been illustrated in two segments, it is to be understood that the arc length of each shroud is not so limited and may, in fact, be less than 180. Of particular advantage is the ease of assembly for the segmented shroud S6 which may be fastened to the stator vanes 22 without additional hardware such as locking bolts and nuts. Such hardware unduly adds to the weight of the engine and may loosen during engine operation, damaging other compressor components. The segmented shroud 56 may also be produced economically by injection molding wherein the molded segments may be formed of lightweight plastic.
Thus having described a preferred embodiment of the invention, though not exhaustive of all possible equivalents, what is desired to be secured by Letters Patent is claimed below.
What is claimed is:
1. A stator assembly comprising:
an outer Casing longitudinally split into at least two sectors and having a dovetail groove around the inside surface thereof;
an inner segmented shroud longitudinally split into at least two sectors, each of which has a plurality of crcumferentially spaced apart pockets in the outer surface thereof wherein each pocket is undercut at one end, and
a plurality of stator vanes extending radially between the shroud and casing with each vane having:
an inner root portion which includes an integral heel portion and an integrally extending toe portion for engaging the undercut end of a respective shroud pocket, and an outer platform from which extend forward and aft tangs which engage the dovetail groove.
2. The stator assembly of claim l wherein the shroud is plastic.
3. The stator assembly of claim 1 wherein the casing is longitudinally split along two 180 sectors and the sectors are connected by a plurality of axially spaced apart locking bolts which pass through aligned holes in two pairs of integral flanges which are spaced 180 apart around the casing.
4. The stator assembly of claim 1 wherein each stator vane may be individually inserted into a respective pocket in the shroud by first rotating the stator vane in relation to the center axis of the shoud in order to insert the tang portion of the root into the pocket so as to engage the undercut surface whereupon the stator vane may be rotated about the undercut surface so as to bring the heel portion of the root into engagement with the pocket.
5. A compressor comprising: an outer casing longitudinally split into at least two sectors and having at least one dovetail groove around the inside surface thereof; a rotor from which extend at least two axially spaced apart rows of rotor blades; at least one inner segmented shroud longitudinally split into at least two sectors which are interposed between two rows of rotor blades wherein the sectors each include a plurality of circumferentially spaced apart pockets in the outer surface thereof, each of which is undercut at one end, and a plurality of stator varies extending radially between the shroud and casing with each vane having: an inner root portion including an integral heel portion and an integrally extending toe portion for en gaging the undercut end of a respective shroud pocket, and an outer platform from which extend forward and aft tangs which engage the dovetail groove.
6. The compressor of claim 5 wherein the shroud in plastic.
7. The compressor of claim 5 wherein the casing is longitudinally split along two sectors and the sectors are connected by a plurality of axially spaced apart locking bolts which pass through aligned holes in two pairs of integral flanges which are spaced 180 apart around the compressor casing.
8. The compressor of claim 5 wherein each stator vane may be individually inserted into a respective pocket in the shroud by first rotating the stator vane in relation to the center axis of the shroud in order to insert the tang portion of the root into the pocket so as to engage the undercut surface whereupon the stator vane may be rotated about the undercut surface so as to bring the heel portion of the root into engagement with the pocket.
9. The compressor of claim 5 wherein the inner shroud operates as the stator member of a labyrinth type seal by engaging a plurality of revolving teeth formed integral to the compressor rotor.
=l l =l= l ek vUNITED STATES PATENT OFFICE CERTIFICATE OF CORRECTION patent No, 3,849,023 Dated November' 19, 1974 `Inventor-(S) NlChOlaS Klompas It is certified that error appears in the above-identified patent and that said Letters Patent are hereby corrected as shown below:
Column 6, line 3, "in" should read is Signed and sealed this 21st day of January 1975.
{SEAL} Attest:
MCCOY 4M. GIBSON JR. C. MARSHALL DANN Attestng Officer Commissionei` ofPatents F ORM PO-I OSO 10-69) USCOMM-DC 80376-9369 U.S. GOVERNHENT PRINTING OFFICE: 86g 930
Claims (9)
1. A stator assembly comprising: an outer casing longitudinally split into at least two sectors and having a dovetail groove around the inside surface thereof; an inner segmented shroud longitudinally split into at least two sectors, each of which has a plurality of circumferentially spaced apart pockets in the outer surface thereof wherein each pocket is undercut at one end, and a plurality of stator vanes extending radially between the shroud and casing with each vane having: an inner root portion which includes an integral heel portion and an integrally extending toe portion for engaging the undercut end of a respective shroud pocket, and an outer platform from which extend forward and aft tangs which engage the dovetail groove.
2. The stator assembly of claim 1 wherein the shroud is plastic.
3. The stator assembly of claim 1 wherein the casing is longitudinally split along two 180* sectors and the sectors are connected by a plurality of axially spaced apart locking bolts which pass through aligned holes in two pairs of integral flanges which are spaced 180* apart around the casing.
4. The stator assembly of claim 1 wherein each stator vane may be individually inserted into a respective pocket in the shroud by first rotating the stator vane in relation to the center axis of the shoud in order to insert the tang portion of the root into the pocket so as to engage the undercut surface whereupon the stator vane may be rotated about the undercut surface so as to bring the heel portion of the root into engagement with the pocket.
5. A compressor comprising: an outer casing longitudinally split into at least two sectors and having at least one dovetail groove around the inside surface thereof; a rotor from which extend at least two axially spaced apart rows of rotor blades; at least one inner segmented shroud longitudinally split into at least two sectors which are interposed between two rows of rotor blades wherein the sectors each include a plurality of circumferentially spaced apart pockets in the outer surface thereof, each of which is undercut at one end, and a plurality of stator vanes extending radially between the shroud and casing with each vane having: an inner root portion including an integral heel portion and an integrally extending toe portion for engaging the undercut end of a respective shroud pocket, and an outer platform from which extend forward and aft tangs which engage the dovetail groove.
6. The compressor of claim 5 wherein the shroud in plastic.
7. The compressor of claim 5 wherein the casing is longitudinally split along two 180* sectors and the sectors are connected by a plurality of axially spaced apart locking bolts which pass through aligned holes in two pairs of integral flanges which are spaced 180* apart around the compressor casing.
8. The compressor of claim 5 wherein each stator vane may be individually inserted into a respective pocket in the shroud by first rotating the stator vane in relation to the center axis of the shroud in order to insert the tang portion of the root into the pocket so as to engage the undercut surface whereupon the stator vane may be rotated about the undercut surface so as to bring the heel portion of the root into engagement with the pocket.
9. The compressor of claim 5 wherein the inner shroud operates as the stator member of a labyrinth type seal by engaging a plurality of revolving teeth formed integral to the compressor rotor.
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US00374518A US3849023A (en) | 1973-06-28 | 1973-06-28 | Stator assembly |
CA197,271A CA1000206A (en) | 1973-06-28 | 1974-04-10 | Stator assembly |
GB2671274A GB1461958A (en) | 1973-06-28 | 1974-06-17 | Vaned stator assemblies particularly in or for compressors |
DE2430579A DE2430579A1 (en) | 1973-06-28 | 1974-06-26 | VANE ARRANGEMENT |
JP49072897A JPS5069413A (en) | 1973-06-28 | 1974-06-27 | |
IT24512/74A IT1015474B (en) | 1973-06-28 | 1974-06-28 | STATOR COMPLEX FOR AXIAL FLOW INCLUDING |
FR7422581A FR2235298B1 (en) | 1973-06-28 | 1974-06-28 | |
BE146002A BE817004A (en) | 1973-06-28 | 1974-06-28 | COMPRESSOR STATOR |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US00374518A US3849023A (en) | 1973-06-28 | 1973-06-28 | Stator assembly |
Publications (1)
Publication Number | Publication Date |
---|---|
US3849023A true US3849023A (en) | 1974-11-19 |
Family
ID=23477187
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US00374518A Expired - Lifetime US3849023A (en) | 1973-06-28 | 1973-06-28 | Stator assembly |
Country Status (8)
Country | Link |
---|---|
US (1) | US3849023A (en) |
JP (1) | JPS5069413A (en) |
BE (1) | BE817004A (en) |
CA (1) | CA1000206A (en) |
DE (1) | DE2430579A1 (en) |
FR (1) | FR2235298B1 (en) |
GB (1) | GB1461958A (en) |
IT (1) | IT1015474B (en) |
Cited By (48)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4142827A (en) * | 1976-06-15 | 1979-03-06 | Nuovo Pignone S.P.A. | System for locking the blades in position on the stator case of an axial compressor |
US4232996A (en) * | 1978-10-06 | 1980-11-11 | The United States Of America As Represented By The Secretary Of The Air Force | Light weight fan assembly |
US4655682A (en) * | 1985-09-30 | 1987-04-07 | United Technologies Corporation | Compressor stator assembly having a composite inner diameter shroud |
US4792277A (en) * | 1987-07-08 | 1988-12-20 | United Technologies Corporation | Split shroud compressor |
US4889470A (en) * | 1988-08-01 | 1989-12-26 | Westinghouse Electric Corp. | Compressor diaphragm assembly |
US4907944A (en) * | 1984-10-01 | 1990-03-13 | General Electric Company | Turbomachinery blade mounting arrangement |
US4940386A (en) * | 1987-02-05 | 1990-07-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Multiple flow turbojet engine with an outer ring of the fan outlet shrunk onto the case |
US4990056A (en) * | 1989-11-16 | 1991-02-05 | General Motors Corporation | Stator vane stage in axial flow compressor |
US5174715A (en) * | 1990-12-13 | 1992-12-29 | General Electric Company | Turbine nozzle |
US5411368A (en) * | 1993-11-08 | 1995-05-02 | Allied-Signal Inc. | Ceramic-to-metal stator vane assembly with braze |
US5584654A (en) * | 1995-12-22 | 1996-12-17 | General Electric Company | Gas turbine engine fan stator |
US5636659A (en) * | 1995-10-17 | 1997-06-10 | Westinghouse Electric Corporation | Variable area compensation valve |
US5639212A (en) * | 1996-03-29 | 1997-06-17 | General Electric Company | Cavity sealed compressor |
EP0804995A1 (en) * | 1996-05-02 | 1997-11-05 | SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma | Tool for assembling a stator ring of a turbomachine |
US5704762A (en) * | 1993-11-08 | 1998-01-06 | Alliedsignal Inc. | Ceramic-to-metal stator vane assembly |
US5984633A (en) * | 1995-12-20 | 1999-11-16 | Abb Patent Gmbh | Guide device for a turbine with a guide-blade carrier and method for producing the guide device |
US6000906A (en) * | 1997-09-12 | 1999-12-14 | Alliedsignal Inc. | Ceramic airfoil |
US6409472B1 (en) | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
US6478539B1 (en) | 1999-08-30 | 2002-11-12 | Mtu Aero Engines Gmbh | Blade structure for a gas turbine engine |
SG92823A1 (en) * | 2000-12-27 | 2002-11-19 | United Technologies Corp | Pneumatic press vane lift installation tool |
EP1531234A1 (en) * | 2003-11-17 | 2005-05-18 | Rolls-Royce Deutschland Ltd & Co KG | Inner shroud for the stator vanes of a gas turbine compressor |
US20060153673A1 (en) * | 2004-11-17 | 2006-07-13 | Volker Guemmer | Turbomachine exerting dynamic influence on the flow |
US20060222485A1 (en) * | 2004-09-30 | 2006-10-05 | Snecma | Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor |
US20070059169A1 (en) * | 2005-09-12 | 2007-03-15 | Barry Barnett | Foreign object damage resistant vane assembly |
US20070079506A1 (en) * | 2005-10-06 | 2007-04-12 | General Electric Company | Method of providing non-uniform stator vane spacing in a compressor |
US20070098557A1 (en) * | 2005-09-12 | 2007-05-03 | Barry Barnett | Vane assembly with outer grommets |
US20070166151A1 (en) * | 2006-01-13 | 2007-07-19 | General Electric Company | Welded nozzle assembly for a steam turbine and methods of assembly |
US20070237633A1 (en) * | 2005-09-12 | 2007-10-11 | Barry Barnett | Vane assembly with grommet |
US20070237629A1 (en) * | 2006-04-05 | 2007-10-11 | General Electric Company | Gas turbine compressor casing flowpath rings |
US20080193290A1 (en) * | 2007-02-14 | 2008-08-14 | Power Systems Manufacturing, Llc | Hook Ring Segment For A Compressor Vane |
US20090041576A1 (en) * | 2007-08-10 | 2009-02-12 | Volker Guemmer | Fluid flow machine featuring an annulus duct wall recess |
US20090246007A1 (en) * | 2008-02-28 | 2009-10-01 | Erik Johann | Casing treatment for axial compressors in a hub area |
US7628578B2 (en) | 2005-09-12 | 2009-12-08 | Pratt & Whitney Canada Corp. | Vane assembly with improved vane roots |
US20100014956A1 (en) * | 2008-07-07 | 2010-01-21 | Rolls-Royce Deutschland Ltd & Co Kg | Fluid flow machine featuring a groove on a running gap of a blade end |
US20100150708A1 (en) * | 2008-12-11 | 2010-06-17 | Cortequisse Jean-Francois | Segmented Composite Inner Ferrule and Segment of Diffuser of Axial Compressor |
US20110211946A1 (en) * | 2006-01-13 | 2011-09-01 | General Electric Company | Welded nozzle assembly for a steam turbine and assembly fixtures |
US8087885B2 (en) * | 2004-12-01 | 2012-01-03 | United Technologies Corporation | Stacked annular components for turbine engines |
US8382422B2 (en) | 2008-08-08 | 2013-02-26 | Rolls-Royce Deutschland Ltd & Co Kg | Fluid flow machine |
US8696311B2 (en) | 2011-03-29 | 2014-04-15 | Pratt & Whitney Canada Corp. | Apparatus and method for gas turbine engine vane retention |
US20140147262A1 (en) * | 2012-11-27 | 2014-05-29 | Techspace Aero S.A. | Axial Turbomachine Stator with Segmented Inner Shell |
RU2601069C2 (en) * | 2010-12-13 | 2016-10-27 | Дженерал Электрик Компани | Turbine nozzle assembly, method for blade installation in nozzle assembly and steam turbine |
US20170009596A1 (en) * | 2015-07-08 | 2017-01-12 | United Technologies Corporation | Non-contact seal assembly for rotational equipment with linkage between adjacent rotors |
US10006301B2 (en) | 2013-06-04 | 2018-06-26 | United Technologies Corporation | Vane assembly including two- and three-dimensional arrangements of continuous fibers |
US10215192B2 (en) | 2014-07-24 | 2019-02-26 | Siemens Aktiengesellschaft | Stator vane system usable within a gas turbine engine |
US20200088049A1 (en) * | 2018-09-18 | 2020-03-19 | General Electric Company | Airfoil shroud assembly using tenon with externally threaded stud and nut |
US20220381150A1 (en) * | 2021-05-26 | 2022-12-01 | General Electric Company | Split-line stator vane assembly |
US11643969B2 (en) * | 2021-04-16 | 2023-05-09 | General Electric Company | Split casings and methods of forming and cooling casings |
US20240044258A1 (en) * | 2022-08-05 | 2024-02-08 | Raytheon Technologies Corporation | Vane multiplet with conjoined singlet vanes |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2112878B (en) * | 1981-12-28 | 1985-12-04 | United Technologies Corp | Air seal for compressor stator |
FR2535795B1 (en) * | 1982-11-08 | 1987-04-10 | Snecma | DEVICE FOR SUSPENSION OF STATOR BLADES OF AXIAL COMPRESSOR FOR ACTIVE CONTROL OF GAMES BETWEEN ROTOR AND STATOR |
US4957412A (en) * | 1988-09-06 | 1990-09-18 | Westinghouse Electric Corp. | Apparatus and method for supporting the torque load on a gas turbine vane |
DE19507673C2 (en) * | 1995-03-06 | 1997-07-03 | Mtu Muenchen Gmbh | Guide wheel for turbomachinery |
CN105033532B (en) * | 2015-06-01 | 2017-03-01 | 深圳市联赢激光股份有限公司 | A kind of weld jig of motor stator |
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US1273634A (en) * | 1917-09-13 | 1918-07-23 | Gen Electric | Shaft-packing. |
US1534415A (en) * | 1924-07-07 | 1925-04-21 | Westinghouse Electric & Mfg Co | Turbine blade |
DE474361C (en) * | 1926-11-07 | 1929-03-30 | Bergmann Elek Citaets Werke Ak | Device for sealing rotating parts, in particular the shafts of steam or gas turbines |
US2812159A (en) * | 1952-08-19 | 1957-11-05 | Gen Electric | Securing means for turbo-machine blading |
US3501246A (en) * | 1967-12-29 | 1970-03-17 | Westinghouse Electric Corp | Axial fluid-flow machine |
US3525575A (en) * | 1967-05-16 | 1970-08-25 | Licentia Gmbh | Turbine |
US3547455A (en) * | 1969-05-02 | 1970-12-15 | Gen Electric | Rotary seal including organic abradable material |
US3575427A (en) * | 1969-11-03 | 1971-04-20 | United Aircraft Corp | Composite abradable seal |
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DE2152365C3 (en) * | 1971-02-03 | 1973-12-06 | Carrier Corp., Syracuse, N.Y. (V.St.A.) | Device for supporting the inner ends of rotatably mounted guide vanes of an axial flow machine |
-
1973
- 1973-06-28 US US00374518A patent/US3849023A/en not_active Expired - Lifetime
-
1974
- 1974-04-10 CA CA197,271A patent/CA1000206A/en not_active Expired
- 1974-06-17 GB GB2671274A patent/GB1461958A/en not_active Expired
- 1974-06-26 DE DE2430579A patent/DE2430579A1/en active Pending
- 1974-06-27 JP JP49072897A patent/JPS5069413A/ja active Pending
- 1974-06-28 IT IT24512/74A patent/IT1015474B/en active
- 1974-06-28 FR FR7422581A patent/FR2235298B1/fr not_active Expired
- 1974-06-28 BE BE146002A patent/BE817004A/en unknown
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US1273634A (en) * | 1917-09-13 | 1918-07-23 | Gen Electric | Shaft-packing. |
US1534415A (en) * | 1924-07-07 | 1925-04-21 | Westinghouse Electric & Mfg Co | Turbine blade |
DE474361C (en) * | 1926-11-07 | 1929-03-30 | Bergmann Elek Citaets Werke Ak | Device for sealing rotating parts, in particular the shafts of steam or gas turbines |
US2812159A (en) * | 1952-08-19 | 1957-11-05 | Gen Electric | Securing means for turbo-machine blading |
US3525575A (en) * | 1967-05-16 | 1970-08-25 | Licentia Gmbh | Turbine |
US3501246A (en) * | 1967-12-29 | 1970-03-17 | Westinghouse Electric Corp | Axial fluid-flow machine |
US3547455A (en) * | 1969-05-02 | 1970-12-15 | Gen Electric | Rotary seal including organic abradable material |
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Cited By (77)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4142827A (en) * | 1976-06-15 | 1979-03-06 | Nuovo Pignone S.P.A. | System for locking the blades in position on the stator case of an axial compressor |
US4232996A (en) * | 1978-10-06 | 1980-11-11 | The United States Of America As Represented By The Secretary Of The Air Force | Light weight fan assembly |
US4907944A (en) * | 1984-10-01 | 1990-03-13 | General Electric Company | Turbomachinery blade mounting arrangement |
US4655682A (en) * | 1985-09-30 | 1987-04-07 | United Technologies Corporation | Compressor stator assembly having a composite inner diameter shroud |
US4940386A (en) * | 1987-02-05 | 1990-07-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Multiple flow turbojet engine with an outer ring of the fan outlet shrunk onto the case |
US4792277A (en) * | 1987-07-08 | 1988-12-20 | United Technologies Corporation | Split shroud compressor |
US4889470A (en) * | 1988-08-01 | 1989-12-26 | Westinghouse Electric Corp. | Compressor diaphragm assembly |
AU613214B2 (en) * | 1988-08-01 | 1991-07-25 | Westinghouse Electric Corporation | Compressor diaphragm assembly |
US4990056A (en) * | 1989-11-16 | 1991-02-05 | General Motors Corporation | Stator vane stage in axial flow compressor |
US5174715A (en) * | 1990-12-13 | 1992-12-29 | General Electric Company | Turbine nozzle |
US5411368A (en) * | 1993-11-08 | 1995-05-02 | Allied-Signal Inc. | Ceramic-to-metal stator vane assembly with braze |
US5704762A (en) * | 1993-11-08 | 1998-01-06 | Alliedsignal Inc. | Ceramic-to-metal stator vane assembly |
US5636659A (en) * | 1995-10-17 | 1997-06-10 | Westinghouse Electric Corporation | Variable area compensation valve |
US5993149A (en) * | 1995-10-17 | 1999-11-30 | Siemens Westinghouse Power Corporation | Variable area compensation valve |
US5984633A (en) * | 1995-12-20 | 1999-11-16 | Abb Patent Gmbh | Guide device for a turbine with a guide-blade carrier and method for producing the guide device |
US5584654A (en) * | 1995-12-22 | 1996-12-17 | General Electric Company | Gas turbine engine fan stator |
US5639212A (en) * | 1996-03-29 | 1997-06-17 | General Electric Company | Cavity sealed compressor |
EP0804995A1 (en) * | 1996-05-02 | 1997-11-05 | SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma | Tool for assembling a stator ring of a turbomachine |
FR2748224A1 (en) * | 1996-05-02 | 1997-11-07 | Snecma | TOOLS FOR MOUNTING A TURBOMACHINE DISTRIBUTOR |
US5918356A (en) * | 1996-05-02 | 1999-07-06 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Tools for mounting a turbo aero engine distributor |
US6000906A (en) * | 1997-09-12 | 1999-12-14 | Alliedsignal Inc. | Ceramic airfoil |
US6409472B1 (en) | 1999-08-09 | 2002-06-25 | United Technologies Corporation | Stator assembly for a rotary machine and clip member for a stator assembly |
US6478539B1 (en) | 1999-08-30 | 2002-11-12 | Mtu Aero Engines Gmbh | Blade structure for a gas turbine engine |
SG92823A1 (en) * | 2000-12-27 | 2002-11-19 | United Technologies Corp | Pneumatic press vane lift installation tool |
US6640437B2 (en) | 2000-12-27 | 2003-11-04 | United Technologies Corporation | Method for installing stator vanes |
EP1531234A1 (en) * | 2003-11-17 | 2005-05-18 | Rolls-Royce Deutschland Ltd & Co KG | Inner shroud for the stator vanes of a gas turbine compressor |
US20050220612A1 (en) * | 2003-11-17 | 2005-10-06 | Ingo Jahns | Inner shroud for the stator blades of the compressor of a gas turbine |
US7287957B2 (en) | 2003-11-17 | 2007-10-30 | Rolls-Royce Deutschland Ltd & Co Kg | Inner shroud for the stator blades of the compressor of a gas turbine |
US20060222485A1 (en) * | 2004-09-30 | 2006-10-05 | Snecma | Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor |
US7581920B2 (en) * | 2004-09-30 | 2009-09-01 | Snecma | Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor |
US20060153673A1 (en) * | 2004-11-17 | 2006-07-13 | Volker Guemmer | Turbomachine exerting dynamic influence on the flow |
US8262340B2 (en) | 2004-11-17 | 2012-09-11 | Rolls-Royce Deutschland Ltd Co KG | Turbomachine exerting dynamic influence on the flow |
US8087885B2 (en) * | 2004-12-01 | 2012-01-03 | United Technologies Corporation | Stacked annular components for turbine engines |
US20070237633A1 (en) * | 2005-09-12 | 2007-10-11 | Barry Barnett | Vane assembly with grommet |
US20070237632A1 (en) * | 2005-09-12 | 2007-10-11 | Barry Barnett | Foreign object damage resistant vane assembly |
US20070098557A1 (en) * | 2005-09-12 | 2007-05-03 | Barry Barnett | Vane assembly with outer grommets |
US7413400B2 (en) | 2005-09-12 | 2008-08-19 | Pratt & Whitney Canada Corp. | Vane assembly with grommet |
US7628578B2 (en) | 2005-09-12 | 2009-12-08 | Pratt & Whitney Canada Corp. | Vane assembly with improved vane roots |
US7494316B2 (en) * | 2005-09-12 | 2009-02-24 | Pratt & Whitney Canada Corp. | Foreign object damage resistant vane assembly |
US7530782B2 (en) | 2005-09-12 | 2009-05-12 | Pratt & Whitney Canada Corp. | Foreign object damage resistant vane assembly |
US20070059169A1 (en) * | 2005-09-12 | 2007-03-15 | Barry Barnett | Foreign object damage resistant vane assembly |
US7637718B2 (en) | 2005-09-12 | 2009-12-29 | Pratt & Whitney Canada Corp. | Vane assembly with outer grommets |
CN103982434A (en) * | 2005-10-06 | 2014-08-13 | 通用电气公司 | Method of providing non-uniform stator vane spacing in a compressor |
US20070079506A1 (en) * | 2005-10-06 | 2007-04-12 | General Electric Company | Method of providing non-uniform stator vane spacing in a compressor |
US7743497B2 (en) | 2005-10-06 | 2010-06-29 | General Electric Company | Method of providing non-uniform stator vane spacing in a compressor |
US7427187B2 (en) * | 2006-01-13 | 2008-09-23 | General Electric Company | Welded nozzle assembly for a steam turbine and methods of assembly |
US20070166151A1 (en) * | 2006-01-13 | 2007-07-19 | General Electric Company | Welded nozzle assembly for a steam turbine and methods of assembly |
US8702385B2 (en) | 2006-01-13 | 2014-04-22 | General Electric Company | Welded nozzle assembly for a steam turbine and assembly fixtures |
US20110211946A1 (en) * | 2006-01-13 | 2011-09-01 | General Electric Company | Welded nozzle assembly for a steam turbine and assembly fixtures |
US20070237629A1 (en) * | 2006-04-05 | 2007-10-11 | General Electric Company | Gas turbine compressor casing flowpath rings |
US20080193290A1 (en) * | 2007-02-14 | 2008-08-14 | Power Systems Manufacturing, Llc | Hook Ring Segment For A Compressor Vane |
US7618234B2 (en) * | 2007-02-14 | 2009-11-17 | Power System Manufacturing, LLC | Hook ring segment for a compressor vane |
US8419355B2 (en) | 2007-08-10 | 2013-04-16 | Rolls-Royce Deutschland Ltd & Co Kg | Fluid flow machine featuring an annulus duct wall recess |
US20090041576A1 (en) * | 2007-08-10 | 2009-02-12 | Volker Guemmer | Fluid flow machine featuring an annulus duct wall recess |
US8251648B2 (en) | 2008-02-28 | 2012-08-28 | Rolls-Royce Deutschland Ltd & Co Kg | Casing treatment for axial compressors in a hub area |
US20090246007A1 (en) * | 2008-02-28 | 2009-10-01 | Erik Johann | Casing treatment for axial compressors in a hub area |
US8257022B2 (en) | 2008-07-07 | 2012-09-04 | Rolls-Royce Deutschland Ltd Co KG | Fluid flow machine featuring a groove on a running gap of a blade end |
US20100014956A1 (en) * | 2008-07-07 | 2010-01-21 | Rolls-Royce Deutschland Ltd & Co Kg | Fluid flow machine featuring a groove on a running gap of a blade end |
US8382422B2 (en) | 2008-08-08 | 2013-02-26 | Rolls-Royce Deutschland Ltd & Co Kg | Fluid flow machine |
US20100150708A1 (en) * | 2008-12-11 | 2010-06-17 | Cortequisse Jean-Francois | Segmented Composite Inner Ferrule and Segment of Diffuser of Axial Compressor |
US8636466B2 (en) * | 2008-12-11 | 2014-01-28 | Techspace Aero S.A. | Segmented composite inner ferrule and segment of diffuser of axial compressor |
US20140140826A1 (en) * | 2008-12-11 | 2014-05-22 | Jean-Francois Cortequisse | Segmented Composite Inner Ferrule and Segment of Diffuser of Axial Compressor |
US9062687B2 (en) * | 2008-12-11 | 2015-06-23 | Techspace Aero S.A. | Segmented composite inner ferrule and segment of diffuser of axial compressor |
RU2601069C2 (en) * | 2010-12-13 | 2016-10-27 | Дженерал Электрик Компани | Turbine nozzle assembly, method for blade installation in nozzle assembly and steam turbine |
US8696311B2 (en) | 2011-03-29 | 2014-04-15 | Pratt & Whitney Canada Corp. | Apparatus and method for gas turbine engine vane retention |
US20140147262A1 (en) * | 2012-11-27 | 2014-05-29 | Techspace Aero S.A. | Axial Turbomachine Stator with Segmented Inner Shell |
US10006301B2 (en) | 2013-06-04 | 2018-06-26 | United Technologies Corporation | Vane assembly including two- and three-dimensional arrangements of continuous fibers |
US10215192B2 (en) | 2014-07-24 | 2019-02-26 | Siemens Aktiengesellschaft | Stator vane system usable within a gas turbine engine |
US10794208B2 (en) * | 2015-07-08 | 2020-10-06 | Raytheon Technologies Corporation | Non-contact seal assembly for rotational equipment with linkage between adjacent rotors |
US20170009596A1 (en) * | 2015-07-08 | 2017-01-12 | United Technologies Corporation | Non-contact seal assembly for rotational equipment with linkage between adjacent rotors |
US20200088049A1 (en) * | 2018-09-18 | 2020-03-19 | General Electric Company | Airfoil shroud assembly using tenon with externally threaded stud and nut |
US11028709B2 (en) * | 2018-09-18 | 2021-06-08 | General Electric Company | Airfoil shroud assembly using tenon with externally threaded stud and nut |
US11643969B2 (en) * | 2021-04-16 | 2023-05-09 | General Electric Company | Split casings and methods of forming and cooling casings |
US20220381150A1 (en) * | 2021-05-26 | 2022-12-01 | General Electric Company | Split-line stator vane assembly |
US11629606B2 (en) * | 2021-05-26 | 2023-04-18 | General Electric Company | Split-line stator vane assembly |
US20240044258A1 (en) * | 2022-08-05 | 2024-02-08 | Raytheon Technologies Corporation | Vane multiplet with conjoined singlet vanes |
US11952917B2 (en) * | 2022-08-05 | 2024-04-09 | Rtx Corporation | Vane multiplet with conjoined singlet vanes |
Also Published As
Publication number | Publication date |
---|---|
IT1015474B (en) | 1977-05-10 |
BE817004A (en) | 1974-12-30 |
FR2235298B1 (en) | 1978-03-24 |
FR2235298A1 (en) | 1975-01-24 |
CA1000206A (en) | 1976-11-23 |
GB1461958A (en) | 1977-01-19 |
JPS5069413A (en) | 1975-06-10 |
DE2430579A1 (en) | 1975-01-16 |
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