US3338508A - Axial-flow compressor - Google Patents
Axial-flow compressor Download PDFInfo
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- US3338508A US3338508A US481842A US48184265A US3338508A US 3338508 A US3338508 A US 3338508A US 481842 A US481842 A US 481842A US 48184265 A US48184265 A US 48184265A US 3338508 A US3338508 A US 3338508A
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- rings
- case
- compressor
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
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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
- F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
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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
- the rotor shrouds fit the interior of the case and the vane rings are spigotted onto the rotor shrounds.
- a set of pull rods provides for removal of this structure from the case.
- the vanes are cantilevered from the vane rings and are reinforced by a wire welded to the ring between the vanes and to the outer ends of the vanes which project through the ring.
- Our invention is directed to improvements in the stationary structure of axial-flow compressors.
- the principal purpose of our invention is to provide lightweight structures of rather large size particularly adapted for such uses as the compressors of lift jet engines.
- a compressor according to our invention preferably embodies a lightweight case and lightweight stator vane stages piloted in the case with vanes cantilevered from the outer shroud ring. Special provisions are made for reinforcing the attachment of the vanes to the shroud ring without adding any significant weight and for installing and removing the stator vane stages and rotor shrouds from a circumferentially unbroken compressor case.
- FIGURE 1 is a side view, with parts cut away, of a lift jet engine.
- FIGURE 2 is a partial sectional view of the compressor of the engine taken on a plane containing the axis of the engine.
- FIGURE 3 is a fragmentary sectional view taken on the plane indicated by the line 3'3 in FIGURE 2.
- FIGURE 4 is a fragmentary axonometric view of a stator stage.
- FIGURE 5 is a view to a larger scale of a section similar to FIGURE 2.
- FIGURE 6 is a view similar to FIGURE 5 taken on a different plane containing the axis.
- FIGURE 1 illustrates the preferred environment, a lift jet engine comprising a compressor 9 supplying compressed air to combustion apparatus and a turbine (not illustrated) within a case 10, the turbine driving the compressor and discharging propulsive gas through an exhaust nozzle 11.
- the compressor includes a rotor 13 having a forward bearing within a fairing 14 supported by struts 15 extending across the air inlet of the compressor.
- the compressor rotor forms a unitary rotating structure with the turbine wheel which has a bearing near the exhaust end of the engine (not shown).
- Fuel is supplied to the combustion apparatus of the engine from a manifold 17 through branch pipes 18. Since the structure of the engine is immaterial to the compressor structure, it will not be further described.
- the compressor 9 comprises a substantially cylindrical sheet metal case 19 which has a forward flange to which a cylindrical air inlet frame 21 is bolted.
- the air inlet frame mounts the struts 15 which in turn support the fairing 14.
- the cornpressor rotor 13 includes a number of lightweight disks 22 which bear rings of rotor blades 23 pinned to them. Seal rings 24 are disposed between the disks.
- the successive stages of stator vanes 25 are mounted between the stages of rotor blades. These vanes extend radially inward from the case 19 which is bounded by the inlet frame 21 and, so far as the compressor rotor is concerned, at the rear end by an inwardly directed flange 26.
- stator vanes 25 are cantilevered from stator vane outer shroud rings 27 which are spaced apart axially by stationary shroud rings 29 for the rotor stages.
- the rings of each of these ets are of shallow channel section, as appears most clearly in FIGURES 5 and 6.
- the rings 27 and 29 are supported and centered in the case 19 by flanges defined by rings 31 brazed to the interior of the light sheet metal case 19. These rings 31 have cylindrical internal surfaces which provide a pilot for the rear flange 33 of each rotor shroud ring 29 except the final shroud ring, which is identified as 34.
- the rear flange of ring 34 bears against the abutment 26 of the case.
- the channel section stator vane shrouds 27 are disposed between and in contact with the adjacent rotor shroud rings and are supported through a number of pin and slot connections from these rings. The rings 27 thus do not directly engage the outer case but are held centered within the case by their connection to the adjacent rotor shrouds.
- This connection is provided by a number of headed pins 35 welded to and extending from the flange 33 into slots 37 in the outwardly extending flanges at the edges of the shroud ring 27.
- the stator vane ring 27 immediately forward of the last rotor stage is thus supported at its forward edge by the adjacent shroud ring 29 and in turn supports from its rear edge, by the same sort of connection, the final rotor shroud ring 34.
- the flanges on the shroud ring 27 are spaced from the pilot rings 31 and this, with the radially expansible connection afforded by the freedom of pins 35 in slots 37, allows for relative expansion of the stator vane stages with re-- spect to the rotor shrouds and accurately centers the vane stages in the case.
- the first rotor stage shroud ring 29 is held in place by a shroud 39 mounted within the inlet frame 21 which in turn is held in place when the inlet frame is bolted to the compressor case 19.
- a shroud 39 mounted within the inlet frame 21 which in turn is held in place when the inlet frame is bolted to the compressor case 19.
- the pilot rings 31 are of slightly decreasing diameter from the front to the rear of the case and, as a practical example, the difference in diameters between successive pilot rings 31 may be about to of an inch.
- the diameter step between successive rings could be much larger.
- a number of pull rods 41 (preferably four) extending axially of the case are distributed around the circumference. These rods are guided in notches 42 (FIGURE 3) in the pilots 31 and notches 43 in the flanges of the vane hrouds 27.
- An expanding ring 44 (FIGURE 2) is fitted to the rear ends of these rods radially outward of the final rotor shroud ring 34. The forward ends of the pull rods are threaded as indicated at 45.
- the rods 41 can be pulled slightly forward so that ring 44 abuts the forward flange of shroud 34.
- the stator structure may be pulled forwardly from the case, the rotor, of course, moving with it.
- stator structure so far described may be quite light because no great forces tend to distort the structure and the effect of air pressure in the compressor is to even out any departures from exact circular cross section.
- the shroud rings of both sets are lightweight and flexible and are piloted in or supported from the case so that they are held truly circular by the case.
- the stator shroud rings 27 carry the vanes 25 which are subjected to substantial dynamic loading from the air flowing through the compressor.
- FIG- URES 3 and 4- The structure for this is most clearly shown in FIG- URES 3 and 4-, and also in FIGURES 5 and 6.
- Each vane 25 is inserted through a suitable opening, shaped to conform to the vane, in the cylindrical web '50 of the shroud ring 27.
- These blades are brazed in place and project slightly through the outer shroud; as a practical example, perhaps a quarter of an inch.
- a notch 51 is provided across the end of each blade and zigzag bracing wire 52 extending around the shroud ring is spot-welded to the outer end of the blade at the notch 51 and to the outer surface of the shroud ring midway between each adjacent pair of blades.
- Wire 52 preferably is in a number of segments or sections for convenience in assembly.
- the sections of wire 52 between the points of attachment to the shroud ring and of attachment to the vane brace the vane against any movement due to the aerodynamic lift on the vane.
- This arrangement contributes a great deal to the rigidity of the assembly and adds substantially no weight. It eliminates the need for thick or doublelayered outer shrouds to provide suflicient anchorage for the blades.
- a lightweight multi-stage axial-flow compressor stator comprising, in combination,
- bracing wires each bonded to the outer end of a plural number of vanes and bonded to the said portion intermediate the vanes
- a lightweight multi-stage axial-flow compressor stator comprising, in combination,
- a lightweight multi-stage axial-flow compressor stator comprising, in combination,
- compressor stator vanes fixed on the vane shroud rings extending through the rings and projecting outwardly from a portion of the outer surface of the ring
- bracing wires each bonded to the outer end of a plural number of vanes and bonded to the said portion intermediate the vanes.
- a lightweight multi-stage axial-flow compressor stator comprising, in combination,
- a turbomachine stator vane stage comprising, in
- vanes fixed 0n and cantilevered inwardly from the shroud ring
- the shroud ring having holes configured to fit the vanes
- vanes extending radially through the holes and projecting outwardly therefrom, the vanes being bonded to the ring, and
- bracing wire means extending circumferentially of the shroud ring bonded to the outer ends of said vanes at a point on each vane spaced outwardly from the ring and bonded to the outer surface of the ring at points circumferentially between the vanes so as to provide braces between the outer ends of said vanes and the ring.
- a turhomachine stator vane stage comprising, in
- vanes fixed on and cantilevered inwardly from the shroud ring
- the shroud ring having holes configured to fit the vanes
- vanes extending radially through the holes and projecting outwardly therefrom, the vanes being bonded to the ring,
- vanes having notches in their radially outer ends spaced outwardly from the ring
- bracing wire means extending circumferentally of the shroud ring bonded to said vanes within the notches thereof and bonded to the outer surface of the ring at points circumferentially between the vanes so as to provide braces between the outer ends of said vanes and the ring.
- a turbomachine stator vane stage comprising, in
- outer shroud ring having a generally cylindrical portion and flanges projecting radially outward at the edges of the said portion
- vanes fixed on and cantilevered inwardly from the shroud ring
- the shroud ring having holes configured to fit the vanes
- vanes extending radially through the holes and projecting outwardly therefrom between the flanges, the vanes being bonded to the ring, and
- bracing wire means extending circumferentially of the shroud ring bonded to the outer ends of said vanes at a point on each vane spaced outwardly from the ring and bonded to the outer surface of the cylindrical portion of the ring at points circumferentially between the vanes so as to provide braces between the outer ends of said vanes and the ring.
- a turbomachine stator vane stage comprising, in
- outer shroud ring having a generally cylindrical portion and flanges projecting radially outward at the edges of the said portion
- vanes fixed on and cantilevered inwardly from the shroud ring
- the shroud ring having holes configured to fit the vanes
- vanes extending radially through the holes and projecting outwardly therefrom between the flanges, the vanes being bonded to the ring,
- vanes having notches in their radially outer ends spaced outwardly from the ring
- bracing wire means extending circumferentially of the shroud ring bonded to said vanes within the notches thereof and bonded to the outer surface of the cylindrical portion of the ring at points circumferentially between the vanes so as to provide braces between the outer ends of said vanes and the ring.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
1967 w. s. CASTLE ETAL 3,338,508
AXIAL-FLOW COMPRESSOR Filed Aug. 23, 1965 2 Sheets-Sheet 1 I N VEN TORS 1957 w. s. CASTLE ETAL 3,338,508
AXIAL'FLIOW COMPRESSOR Filed Aug. 23, 1965 2 Sheets-Sheet 2 United States Patent Ofiice 3,338,568 Patented Aug. 29, 1967 3,338,508 AXIAL-FLOW COMPRESSOR William S. Castle, Speedway, and Henry Ming Mar and Douglas K. Thompson, Indianapolis, Ind., assigiors to General Motors Corporation, Detroit, Mich., a corporation of Delaware Filed Aug. 23, 1965, Ser. No. 481,842 8 Claims. (Cl. 230133) ABSTRACT OF THE DISCLOSURE The stator structure of an axial-flow compressor includes a full cylindrical case into which circular vane rings and stationary rotor shroud rings are inserted in alternating relation. The rotor shrouds fit the interior of the case and the vane rings are spigotted onto the rotor shrounds. A set of pull rods provides for removal of this structure from the case. The vanes are cantilevered from the vane rings and are reinforced by a wire welded to the ring between the vanes and to the outer ends of the vanes which project through the ring.
Our invention is directed to improvements in the stationary structure of axial-flow compressors. The principal purpose of our invention is to provide lightweight structures of rather large size particularly adapted for such uses as the compressors of lift jet engines. A compressor according to our invention preferably embodies a lightweight case and lightweight stator vane stages piloted in the case with vanes cantilevered from the outer shroud ring. Special provisions are made for reinforcing the attachment of the vanes to the shroud ring without adding any significant weight and for installing and removing the stator vane stages and rotor shrouds from a circumferentially unbroken compressor case.
The nature of the invention and the advantages thereof will be clear to those skilled in the art from the succeeding detailed description of the preferred embodiment of the invention and the accompanying drawings thereof.
FIGURE 1 is a side view, with parts cut away, of a lift jet engine.
FIGURE 2 is a partial sectional view of the compressor of the engine taken on a plane containing the axis of the engine.
FIGURE 3 is a fragmentary sectional view taken on the plane indicated by the line 3'3 in FIGURE 2.
FIGURE 4 is a fragmentary axonometric view of a stator stage.
, FIGURE 5 is a view to a larger scale of a section similar to FIGURE 2.
FIGURE 6 is a view similar to FIGURE 5 taken on a different plane containing the axis.
FIGURE 1 illustrates the preferred environment, a lift jet engine comprising a compressor 9 supplying compressed air to combustion apparatus and a turbine (not illustrated) within a case 10, the turbine driving the compressor and discharging propulsive gas through an exhaust nozzle 11. The compressor includes a rotor 13 having a forward bearing within a fairing 14 supported by struts 15 extending across the air inlet of the compressor. The compressor rotor forms a unitary rotating structure with the turbine wheel which has a bearing near the exhaust end of the engine (not shown). Fuel is supplied to the combustion apparatus of the engine from a manifold 17 through branch pipes 18. Since the structure of the engine is immaterial to the compressor structure, it will not be further described.
, Referring to FIGURES 2, 5, and 6, the compressor 9 comprises a substantially cylindrical sheet metal case 19 which has a forward flange to which a cylindrical air inlet frame 21 is bolted. The air inlet frame mounts the struts 15 which in turn support the fairing 14. The cornpressor rotor 13 includes a number of lightweight disks 22 which bear rings of rotor blades 23 pinned to them. Seal rings 24 are disposed between the disks. The successive stages of stator vanes 25 are mounted between the stages of rotor blades. These vanes extend radially inward from the case 19 which is bounded by the inlet frame 21 and, so far as the compressor rotor is concerned, at the rear end by an inwardly directed flange 26. The stator vanes 25 are cantilevered from stator vane outer shroud rings 27 which are spaced apart axially by stationary shroud rings 29 for the rotor stages. The rings of each of these ets are of shallow channel section, as appears most clearly in FIGURES 5 and 6.
The rings 27 and 29 are supported and centered in the case 19 by flanges defined by rings 31 brazed to the interior of the light sheet metal case 19. These rings 31 have cylindrical internal surfaces which provide a pilot for the rear flange 33 of each rotor shroud ring 29 except the final shroud ring, which is identified as 34. The rear flange of ring 34 bears against the abutment 26 of the case. The channel section stator vane shrouds 27 are disposed between and in contact with the adjacent rotor shroud rings and are supported through a number of pin and slot connections from these rings. The rings 27 thus do not directly engage the outer case but are held centered within the case by their connection to the adjacent rotor shrouds. This connection is provided by a number of headed pins 35 welded to and extending from the flange 33 into slots 37 in the outwardly extending flanges at the edges of the shroud ring 27. The stator vane ring 27 immediately forward of the last rotor stage is thus supported at its forward edge by the adjacent shroud ring 29 and in turn supports from its rear edge, by the same sort of connection, the final rotor shroud ring 34. The flanges on the shroud ring 27 are spaced from the pilot rings 31 and this, with the radially expansible connection afforded by the freedom of pins 35 in slots 37, allows for relative expansion of the stator vane stages with re-- spect to the rotor shrouds and accurately centers the vane stages in the case.
The first rotor stage shroud ring 29 is held in place by a shroud 39 mounted within the inlet frame 21 which in turn is held in place when the inlet frame is bolted to the compressor case 19. When this is accomplished all of the shrouds, which may be considered to be the lining of the compressor case, are held in a stack between the inlet frame 21 and the flange 26 of the case.
To facilitate assembly of the rings 27 and 29 in th case, the pilot rings 31 are of slightly decreasing diameter from the front to the rear of the case and, as a practical example, the difference in diameters between successive pilot rings 31 may be about to of an inch. Of course, if a converging compressor case is used, the diameter step between successive rings could be much larger. With the case vertical, the rotor can be lowered into the compressor case at the same time as the vane rings and rotor shrouds, and the shrouds and vane rings will automatically align with the axi of the case. After this is done the air inlet housing is fitted to complete the assembly.
In order to facilitate removal of the shrouds from the interior of the case, a number of pull rods 41 (preferably four) extending axially of the case are distributed around the circumference. These rods are guided in notches 42 (FIGURE 3) in the pilots 31 and notches 43 in the flanges of the vane hrouds 27. An expanding ring 44 (FIGURE 2) is fitted to the rear ends of these rods radially outward of the final rotor shroud ring 34. The forward ends of the pull rods are threaded as indicated at 45.
3 When the inlet frame 21 has been removed, the rods 41 can be pulled slightly forward so that ring 44 abuts the forward flange of shroud 34. By applying a suitable tool to the threaded end of the pull rods, the stator structure may be pulled forwardly from the case, the rotor, of course, moving with it.
The stator structure so far described may be quite light because no great forces tend to distort the structure and the effect of air pressure in the compressor is to even out any departures from exact circular cross section. The shroud rings of both sets are lightweight and flexible and are piloted in or supported from the case so that they are held truly circular by the case. There is no significant load on the rotor shrouds, but the stator shroud rings 27 carry the vanes 25 which are subjected to substantial dynamic loading from the air flowing through the compressor. By eliminating an inner shroud on these vanes, an element of structure having considerable weight is eliminated; but, with the cantilevered vanes, the entire resistance to loads on the blades must be taken through the outer shroud. It is one of the principal objects of our invention to provide a structure capable of resisting these loads without any more weight than is absolutely necessary and to simplify the fabrication of the stator rings.
The structure for this is most clearly shown in FIG- URES 3 and 4-, and also in FIGURES 5 and 6. Each vane 25 is inserted through a suitable opening, shaped to conform to the vane, in the cylindrical web '50 of the shroud ring 27. These blades are brazed in place and project slightly through the outer shroud; as a practical example, perhaps a quarter of an inch. A notch 51 is provided across the end of each blade and zigzag bracing wire 52 extending around the shroud ring is spot-welded to the outer end of the blade at the notch 51 and to the outer surface of the shroud ring midway between each adjacent pair of blades. Wire 52 preferably is in a number of segments or sections for convenience in assembly. The sections of wire 52 between the points of attachment to the shroud ring and of attachment to the vane brace the vane against any movement due to the aerodynamic lift on the vane. This arrangement contributes a great deal to the rigidity of the assembly and adds substantially no weight. It eliminates the need for thick or doublelayered outer shrouds to provide suflicient anchorage for the blades.
It should be clear to those skilled in the art that the structural features of the compressor stator described herein are adapted to promote strength and reduce weight, as well as facilitate assembly and disassembly of the compressor. It will be understood that some features of the invention may be dispensed with while others are retained in response to the requirements of other compress01 structures.
The detailed description of the preferred embodiment of the invention for the purpose of explaining the principles thereof is not to be considered as limiting or restricting the invention, since many modifications may be made by the exercise of skill in the art.
We claim:
1. A lightweight multi-stage axial-flow compressor stator comprising, in combination,
a generally cylindrical case,
a plural number of flanges extending inwardly from the case providing cylindrical internal pilot surfaces successively decreasing slightly in diameter in one direction axially of the case,
a set of stator vane outer shroud rings,
a set of rotor stage stationary shroud rings,
the rings of the two sets alternating axially of the case,
the rings of one set being piloted in said pilot surfaces,
means on the rings supporting the rings of the other set on the rings of the said one set providing for relative radial expansion of the rings and locating the other set axially and radially of the compressor,
a plural number of pull rods extending axially of the compressor past the rings and adapted to engage the ring at one end of the compressor so that the rings may be disassembled from the case by pulling on the rods,
5 compressor stator vanes fixed on the vane shroud rings extending through the rings and projecting outwardly from a portion of the outer surface of the ring, and
bracing wires each bonded to the outer end of a plural number of vanes and bonded to the said portion intermediate the vanes,
2;. A lightweight multi-stage axial-flow compressor stator comprising, in combination,
a generally cylindrical case,
a plural number of flanges extending inwardly from the case providing cylindrical internal pilot surfaces successively decreasing slightly in diameter in one direction axially of the case,
a set of stator vane outer shroud rings,
a set of rotor stage stationary shroud rings,
the rings of the two sets alternating axially of the case,
the rings of one set being piloted in said pilot surfaces,
means on the rings supporting the rings of the other set on the rings of the said one set providing for relative radial expansion of the rings and locating the other set axially and radially of the compressor,
a plural number of pull rods extending axially of the compressor past the rings and adapted to engage the ring at one end of the compressor so that the rings may be disassembled from the case by pulling on the rods, and
compressor stator vanes fixed on the vane shroud rings.
3. A lightweight multi-stage axial-flow compressor stator comprising, in combination,
a generally cylindrical case,
a plural number of flanges extending inwardly from the case providing cylindrical internal pilot surfaces successively decreasing slightly in diameter in one direction axially of the case,
a set of stator vane outer shroud rings,
a set of rotor stage stationary shroud rings,
the rings of the two sets alternating axially of the case,
the rings of one set being piloted in said pilot surfaces,
means on the rings supporting the rings of the other set on the rings of the said one set providing for relative radial expansion of the rings and locating the other set axially and radially of the compressor,
compressor stator vanes fixed on the vane shroud rings extending through the rings and projecting outwardly from a portion of the outer surface of the ring, and
bracing wires each bonded to the outer end of a plural number of vanes and bonded to the said portion intermediate the vanes.
4. A lightweight multi-stage axial-flow compressor stator comprising, in combination,
a generally cylindrical case,
a plural number of flanges extending inwardly from the case providing cylindrical internal pilot surfaces successively decreasing slightly in diameter in one direction axially of the case,
a set of stator vane outer shroud rings,
a set of rotor stage stationary shroud rings,
the rings of the two sets alternating axially of the case,
the rings of one set being piloted in said pilot surfaces,
means on the rings supporting the rings of the other set on the rings of the said one set providing for relative radial expansion of the rings and locating the other set axially and radially of the compressor, and
compressor stator vanes fixed on the vane shroud rings.
5. A turbomachine stator vane stage comprising, in
75 combination,
an outer shroud ring,
vanes fixed 0n and cantilevered inwardly from the shroud ring,
the shroud ring having holes configured to fit the vanes,
the vanes extending radially through the holes and projecting outwardly therefrom, the vanes being bonded to the ring, and
bracing wire means extending circumferentially of the shroud ring bonded to the outer ends of said vanes at a point on each vane spaced outwardly from the ring and bonded to the outer surface of the ring at points circumferentially between the vanes so as to provide braces between the outer ends of said vanes and the ring.
6. A turhomachine stator vane stage comprising, in
combination,
an outer shroud ring,
vanes fixed on and cantilevered inwardly from the shroud ring,
the shroud ring having holes configured to fit the vanes,
the vanes extending radially through the holes and projecting outwardly therefrom, the vanes being bonded to the ring,
the vanes having notches in their radially outer ends spaced outwardly from the ring, and
bracing wire means extending circumferentally of the shroud ring bonded to said vanes within the notches thereof and bonded to the outer surface of the ring at points circumferentially between the vanes so as to provide braces between the outer ends of said vanes and the ring.
7. A turbomachine stator vane stage comprising, in
combination,
a outer shroud ring having a generally cylindrical portion and flanges projecting radially outward at the edges of the said portion,
vanes fixed on and cantilevered inwardly from the shroud ring,
the shroud ring having holes configured to fit the vanes,
the vanes extending radially through the holes and projecting outwardly therefrom between the flanges, the vanes being bonded to the ring, and
bracing wire means extending circumferentially of the shroud ring bonded to the outer ends of said vanes at a point on each vane spaced outwardly from the ring and bonded to the outer surface of the cylindrical portion of the ring at points circumferentially between the vanes so as to provide braces between the outer ends of said vanes and the ring.
8. A turbomachine stator vane stage comprising, in
combination,
a outer shroud ring having a generally cylindrical portion and flanges projecting radially outward at the edges of the said portion,
vanes fixed on and cantilevered inwardly from the shroud ring,
the shroud ring having holes configured to fit the vanes,
the vanes extending radially through the holes and projecting outwardly therefrom between the flanges, the vanes being bonded to the ring,
the vanes having notches in their radially outer ends spaced outwardly from the ring, and
bracing wire means extending circumferentially of the shroud ring bonded to said vanes within the notches thereof and bonded to the outer surface of the cylindrical portion of the ring at points circumferentially between the vanes so as to provide braces between the outer ends of said vanes and the ring.
References Cited UNITED STATES PATENTS 764,450 7/ 1904 Geisenhoner 253--77 1,720,754 7/1929 Baumann 25377 2,772,856 12/1956 Kent et a1 230133 2,885,768 5/1959 Shinn 230-133 2,942,844 6/1960 Neate 25378 FOREIGN PATENTS 267,405 3/ 1927 Great Britain.
622,895 5/ 1949 Great Britain.
661,178 11/1951 Great Britain.
748,912 5/1956 Great Britain.
779,056 7/ 1957 Great Britain.
DONLEY I. STOCKING, Primary Examiner.
HENRY F. RADUAZO, Examiner.
Claims (1)
1. A LIGHTWEIGHT MULTI-STAGE AXIAL-FLOW COMPRESSOR STATOR COMPRISING, IN COMBINATION, A GENERALLY CYLINDRICAL CASE, A PLURAL NUMBER OF FLANGES EXTENDING INWARDLY FROM THE CASE PROVIDING CYLINDRICAL INTERNAL PILOT SURFACES SUCCESSIVELY DECREASING SLIGHTLY IN DIAMETER IN ONE DIRECTION AXIALLY OF THE CASE, A SET OF STATOR VANE OUTER SHROUD RINGS, A SET OF ROTOR STAGE STATIONARY SHROUD RINGS, THE RINGS OF THE TWO SETS ALTERNATING AXIALLY OF THE CASE, THE RINGS OF ONE SET BEING PILOTED IN SAID PILOT SURFACES, MEANS ON THE RINGS SUPPORTING THE RINGS OF THE OTHER SET ON THE RINGS OF THE SAID ONE SET PROVIDING FOR RELATIVE RADIAL EXPANSION OF THE RINGS AND LOCATING THE OTHER SET AXIALLY AND RADIALLY OF THE COMPRESSOR, A PLURAL NUMBER OF PULL RODS EXTENDING AXIALLY OF THE COMPRESSOR PAST THE RINGS AND ADAPTED TO ENGAGE THE RING AT ONE END OF THE COMPRESSOR SO THAT THE RINGS MAY BE DISASSEMBLED FROM THE CASE BY PULLING ON THE RODS, COMPRESSOR STATOR VANES FIXED ON THE VANE SHROUD RINGS EXTENDING THROUGH THE RINGS AND PROJECTING OUTWARDLY FROM A PORTION OF THE OUTER SURFACE OF THE RING, AND BRACING WIRES EACH BONDED TO THE OUTER END OF A PLURAL NUMBER OF VANES AND BONDED TO THE SAID PORTION INTERMEDIATE THE VANES.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US481842A US3338508A (en) | 1965-08-23 | 1965-08-23 | Axial-flow compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US481842A US3338508A (en) | 1965-08-23 | 1965-08-23 | Axial-flow compressor |
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|---|---|
| US3338508A true US3338508A (en) | 1967-08-29 |
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| US481842A Expired - Lifetime US3338508A (en) | 1965-08-23 | 1965-08-23 | Axial-flow compressor |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5022818A (en) * | 1989-02-21 | 1991-06-11 | Westinghouse Electric Corp. | Compressor diaphragm assembly |
| US20090252610A1 (en) * | 2008-04-04 | 2009-10-08 | General Electric Company | Turbine blade retention system and method |
| EP2172620A1 (en) * | 2007-06-22 | 2010-04-07 | Mitsubishi Heavy Industries, Ltd. | Stator blade ring and axial flow compressor using the same |
| US20140255179A1 (en) * | 2013-03-08 | 2014-09-11 | Pratt & Whitney Canada Corp. | Low profile vane retention |
| DE102014119673A1 (en) * | 2014-12-29 | 2016-06-30 | Rolls-Royce Deutschland Ltd & Co Kg | Housing device for a compressor stage of a multi-stage compressor device and method for producing a housing device |
| US20170363090A1 (en) * | 2016-06-21 | 2017-12-21 | Rolls-Royce Corporation | Axial flow compressor assembly |
| US10344774B2 (en) * | 2015-09-29 | 2019-07-09 | Rolls-Royce Plc | Casing for a gas turbine engine and a method of manufacturing such a casing |
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| GB267405A (en) * | 1926-09-09 | 1927-03-17 | Charles Oliver | Improvements in or relating to shrouding for turbine blades and the like |
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| GB622895A (en) * | 1947-04-16 | 1949-05-09 | Frederick William Walton Morle | Improvements relating to axial flow compressors |
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| GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
| GB779056A (en) * | 1954-02-12 | 1957-07-17 | Rolls Royce | Improvements in or relating to bladed or vaned structures for guiding the flow of a fluid |
| US2885768A (en) * | 1951-02-27 | 1959-05-12 | United Aircraft Corp | Stator construction for compressors |
| US2942844A (en) * | 1952-12-22 | 1960-06-28 | Gen Motors Corp | Turbine nozzle |
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| US764450A (en) * | 1903-12-19 | 1904-07-05 | Gen Electric | Turbine-bucket cover. |
| GB267405A (en) * | 1926-09-09 | 1927-03-17 | Charles Oliver | Improvements in or relating to shrouding for turbine blades and the like |
| US1720754A (en) * | 1926-09-09 | 1929-07-16 | Westinghouse Electric & Mfg Co | Turbine-blade shrouding |
| GB622895A (en) * | 1947-04-16 | 1949-05-09 | Frederick William Walton Morle | Improvements relating to axial flow compressors |
| GB661178A (en) * | 1947-12-31 | 1951-11-21 | Karl Ludwig Georg Meurer Von I | Nozzle bodies for turbines |
| GB748912A (en) * | 1950-08-01 | 1956-05-16 | Rolls Royce | Improvements in or relating to blade assemblies of compressors and turbines and likemachines |
| US2772856A (en) * | 1950-08-01 | 1956-12-04 | Rolls Royce | Structural elements for turbo-machines such as compressors or turbines of gasturbineengines |
| US2885768A (en) * | 1951-02-27 | 1959-05-12 | United Aircraft Corp | Stator construction for compressors |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5022818A (en) * | 1989-02-21 | 1991-06-11 | Westinghouse Electric Corp. | Compressor diaphragm assembly |
| EP2172620A1 (en) * | 2007-06-22 | 2010-04-07 | Mitsubishi Heavy Industries, Ltd. | Stator blade ring and axial flow compressor using the same |
| EP2172620A4 (en) * | 2007-06-22 | 2014-08-06 | Mitsubishi Heavy Ind Ltd | Stator blade ring and axial flow compressor using the same |
| US20090252610A1 (en) * | 2008-04-04 | 2009-10-08 | General Electric Company | Turbine blade retention system and method |
| US8894370B2 (en) * | 2008-04-04 | 2014-11-25 | General Electric Company | Turbine blade retention system and method |
| US20140255179A1 (en) * | 2013-03-08 | 2014-09-11 | Pratt & Whitney Canada Corp. | Low profile vane retention |
| US9506361B2 (en) * | 2013-03-08 | 2016-11-29 | Pratt & Whitney Canada Corp. | Low profile vane retention |
| DE102014119673A1 (en) * | 2014-12-29 | 2016-06-30 | Rolls-Royce Deutschland Ltd & Co Kg | Housing device for a compressor stage of a multi-stage compressor device and method for producing a housing device |
| US10119547B2 (en) | 2014-12-29 | 2018-11-06 | Rolls-Royce Deutschland Ltd & Co Kg | Housing device for a compressor stage of a compressor device that is embodied with multiple stages and method for manufacturing a housing device |
| US10344774B2 (en) * | 2015-09-29 | 2019-07-09 | Rolls-Royce Plc | Casing for a gas turbine engine and a method of manufacturing such a casing |
| US20170363090A1 (en) * | 2016-06-21 | 2017-12-21 | Rolls-Royce Corporation | Axial flow compressor assembly |
| US10808720B2 (en) * | 2016-06-21 | 2020-10-20 | Rolls-Royce Corporation | Axial flow compressor assembly |
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