US3501247A - Blade fixing arrangement - Google Patents
Blade fixing arrangement Download PDFInfo
- Publication number
- US3501247A US3501247A US742658A US3501247DA US3501247A US 3501247 A US3501247 A US 3501247A US 742658 A US742658 A US 742658A US 3501247D A US3501247D A US 3501247DA US 3501247 A US3501247 A US 3501247A
- Authority
- US
- United States
- Prior art keywords
- blades
- blade
- wall
- keeper
- casing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
- C04B35/82—Asbestos; Glass; Fused silica
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
Definitions
- This invention relates to the fixing of at least one set of blades, each of said blades having a root portion, to a wall delimiting an annular duct through which the working fluid of a machine, such as a compressor or a turbine, is to fiow, and relates more particularly to an arrangement of the kind comprising, in said wall, a number of openings equal to the number of blades and intended on the one hand to enable the individual introduction of said blades into said duct in a direction transversely thereof (as well as the individual extraction of said blades therefrom), and on the other hand to locate the root portions of said blades.
- the invention applies in particular, but not exclusively, to the attachment of blades at their external extremities to a casing surrounding a rotor of the machine.
- the casing may be xed and constitute, along with the blading which it carries, a stator of the machine. Equally, however, it may be a moving component and thus may constitute an external rotor rotating in the opposite direction to an internal rotor, i.e. as inthe well-known technique of contra-rotating rotors.
- the usual blade fixing methods generally mean that, in order to replace a single defective blade, dismantling and reassembling is required of the whole of the blading set to which said single blade belongs. These are difiicult, lengthy and consequently costly operations and, in the case of contra-rotating turbines, the job-time is further increased because it is necessary to dismantle a fixed casing which in this instance surrounds the rotating casing.
- the invention applies to ordinary compressors and turbines, but is especially valuable in bladed machines having contra-rotating rotors.
- each of the blade roots and the surrounding openings in the wall are dimensioned so that a gap is left therebetween which is adapted to be closed ofi by a mounting insert for each blade which is slidable thereover, there being provided in common to the blades of one set a locking device for locking together the blades, the mounting inserts and the wall, which device permits the selective unlocking of any blade in the said set whilst the others are held locked.
- the device for locking together the iblades of the said set comprises a keeper adapted to slide through 3,501,247 Patented Mar. 17, 1970 passages formed through extensions of the blades and of the mounting inserts in the set, said passages being aligned, in the assembled position, with a groove formed in the wall, and the two extremities of the said keeper having between them, in the assembled position, a peripheral interval at least equivalent to the Width of one of the openings through which the blades are introduced.
- the keeper may then be fixedly located in relation to the casing by means of a detachable key or the like passing through the gap between the two keeper extremities.
- FIGURE 1 schematically illustrates, in longitudinal half-section, a compressor having blades adapted to be fixed by means of an arrangement in accordance with the invention
- FIGURE 2 is a partial, longitudinal half-section, on the line II-II of FIGURE 3, through the external casing of a compressor, showing one embodiment of the arrangement for fixing a blade to the casing in accordance with the invention;
- FIGURE 3 is a partial, transverse half-section, on the line III-III of FIGURE 2, through the casing and the blades it carries;
- FIGURE 4 is a partial, peripheral View, from the exterior, of the casing and the blades it carries;
- FIGURE 5 is a schematic pictorial view of part of the casing
- FIGURE 6 is a schematic pictorial View of an intermediate component (mounting insert) associated with each of the blades and assisting in its fixing;
- FIGURE 7 is a schematic pictorial view of one of the blades intended for fixing to the casing.
- FIGURE 1 schematically illustrates a machine, in the selected example an axial iiow compressor of the contrarotating type, with an external rotor and an internal rotor, having an annular duct delimited by at least one wall, through which a working fiuid liows.
- the external rotor comprises in particular the wall 1 which, in the example shown, constitutes an external casing carrying blades 2, fixed at their other ends to discs 3 located coaxially relative to the axis X-X of the machine. Means (not shown) are provided in order to drive this rotor.
- the internal rotor carries blades 4 mounted on discs 5 fixed to a drive shaft 6.
- FIGURES 2 to 7 relate more particularly to the fixing of the blades 2 to the wall 1.
- this wall is itself movable but it is obvious that the invention could equally well be applied to conventional machines not having contra-rotating rotors, the reference 1 in such case indicating the stator casing of the machine.
- the Wall 1 (contra-rotating or fixed) carries, at its periphery, a number of circular grooves 1c equal in number to the number of blading rings or blading sets, said grooves being formed in shoulders 1b.
- a number of circular grooves 1c equal in number to the number of blading rings or blading sets, said grooves being formed in shoulders 1b.
- the groove and shoulder are interrupted by substantially oblong openings 1a made in the casing 1. It will be seen that the two parts of the shoulder, located at either side of the groove, contain a hole 1d, the purpose of which will be explained hereinafter.
- the blades 2 each comprise a root 2a above which there projects a shoulder 2b; the latter is traversed by a passage 2c which can be seen particularly clearly in FIG- URE 7.
- Each of the blades 2 is associated with an intermediate component 7, or mounting insert, by means of which, in a manner to be explained later, it is fixed to the casing, Said mounting insert being shown separately in FIG- URE 6.
- the mounting insert 7 is for this purpose provided with a substantially oblong base 7a adapted to fit in the opening 1a and flanked peripherally by a flange 7e fwhich serves to locate the insert in a corresponding countersink 1e formed in the casing around the opening 1a.
- the base 7a is pierced by an opening 7d whose dimensions correspond to those of the root 2a of the blade, and carries two cheeks 7b located at either side of the opening.
- the cheeks themselves contain holes 7c.
- the intermediate component or mounting insert 7 is inserted into the substantially oblong opening 1a, the fiange 7e abutting against the undercut 1e in the casing, and the blade 2 is fitted with its root portion 2a into the opening 7d in the insert so that its shoulder 2b is located between the cheeks 7b of the insert.
- the circular groove 1c in the casing, the passages 2c in the blades and the holes 7c in the insert, are now all aligned.
- a keeper 8 can now be inserted through the aligned passage system 1c, 2c, 7c thus defined.
- the purpose of this keeper is simply to lock the set of blades.
- the expansion forces due to centrifugal action are taken, not by the keeper 8, but by the disc 3 to the periphery of which the blades are fixed in a known manner, for example by the conventional fir-tree formation 2d shown in FIGURES 2 and 3.
- the keeper 8 does not have its extremities Srl-8b flush with one another; as FIGURES 3 and 4 show, there is a free space between these ends, the width e of 'which is slightly greater than the width e1 of a mounting insert 7.
- the keeper In order to lock the set of blades, the keeper is slid circumferentiaily until its two extremities 8a, 8b, are l0- cated at either side of the hole 1d lvisible in FIGURES 3, 4 and 5. Then, there is inserted into the hole a locking device 9 (See FIGURE 5) of some kind, such as a pin, screw or key etc., in order to prevent any further circumferential movement of the keeper.
- a locking device 9 See FIGURE 5 of some kind, such as a pin, screw or key etc.
- the procedure is as follows: the first operation is to remove the locking device 9 in order to release the keeper 8. Then, the keeper is slid around until its two extremities 8a, 8b occupy the position shown in FIGURES 3 and 4 in which they surround the mounting insert 7 of the blade 2 which is to be dismantled. This mounting insert being thus unlocked, it can be moved radially towards the axis of the machine, to bring it into a position shown in broken line in FIG- URES 2 and 3.
- the formation 2d of the blade is disengaged axially from the disc 3, giving the mounting insert 7 this same axial movement.
- the blade root then passes through the substantially oblong opening 1a in the casing.
- FIGURE 2 shows, this axial disengagement is rendered possible by appropriately dimensioning the mounting inserts so that the distance l, separating the edge of the opening 7d from the front or rear edge of the base 7a of the insert, is greater than the width l1 of the formation 2d by which the blade is fixed to the dise 3.
- the blade 2 is removed radially outside through the opening 7d in the insert and the substantially oblong opening 1a in the casing.
- the width IJ, of the opening 791 must be greater (as 4 FIGURE 3 indicates) than the width b1 of the blade formation 2d.
- a replacement blade can be inserted by carrying out the operations, outlined hereinbefore, in the reverse order.
- a machine having at least one bladed component consisting of a wall carrying at least one set of blades, wherein the root of each blade of the set is detachably fixed in an opening in the said wall, the improvement wherein the blade roots and their associated openings in the -wall are mutually sized so that gaps are left surroundingsaid blade roots received in said wall openings, and wherein a fixing arrangement is provided comprising:
- a keeper common to the blades of the one set and adapted to hold in fixed relationship the blades, the inserts and the wall, said keeper being movable to permit release of any blade of the set from the wall said keeper being movable to permit release of any blade of the set from the wall while maintaining its hold'on the remaining blades of the set;
- keeper is adapted to slide through passages formed in extensions of the blades and of the mounting inserts in one and the same set, said passages being aligned, in the assembled position, with a groove formed in the wall, the two extremities of said keeper, in the assembled position, having a gap between them whose width is at least equal to the width of the openings through which the blades are introduced.
- a machine according to claim 2, wherein the releasable means for the keeper comprises means for iixedly locating the keeper in relation to the wall.
- the locating means is constituted by a detachable key adapted to occupy the gap left between the two extremities of the said keeper.
- a machine having at least one bladed component consisting of a wall carrying at least one set of blades, wherein the root of each blade of the set is detachably fixed in an opening in the said wall, the blade roots and their associated openings in the wall being mutually sized so that gaps are left surrounding said blade roots when these are received in the said wall openings, and the xing of the blades lbeing completed by a fixing arrangement which comprises a plurality of inserts, one for each blade, adapted to close the said gaps around the blade roots with the blade roots extending slidably therethrough, and a locking device, common to the blades of the one set, for locking together the blades, the inserts and the wall, said locking device being adapted to permit selective unlocking of any blade of the set while the others are held locked.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Manufacturing & Machinery (AREA)
- Structural Engineering (AREA)
- Organic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
March 17, 1970 M. J. ToURNERE BLADE FIXING ARRANGEMENT Filed July 5. 1968 Zb Za United States Patent Office 3,501,247 BLADE FIXING ARRANGEMENT Marcel Joseph Tournere, Paris, France, assignor to Societe Nationale dEtude et de Construction de Moteurs dAviation, Paris, France, a company of France Filed July 5, 1968, Ser. No. 742,658 Claims priority, application France, July 7, 1967,
Int. Cl. F01d 9/02 U.S. Cl. 415--189 5 Claims ABSTRACT OF THE DISCLOSURE A device for fixing a set of blades to the wall of a turbine, openings being provided in said wall to permit the individual introduction or extraction of the blades, said device comprising mounting inserts which close ofi the spaces formed between the blade roots and the peripheries of the openings, and a keeper which locks together the blades, the mounting inserts and the wall.
This invention relates to the fixing of at least one set of blades, each of said blades having a root portion, to a wall delimiting an annular duct through which the working fluid of a machine, such as a compressor or a turbine, is to fiow, and relates more particularly to an arrangement of the kind comprising, in said wall, a number of openings equal to the number of blades and intended on the one hand to enable the individual introduction of said blades into said duct in a direction transversely thereof (as well as the individual extraction of said blades therefrom), and on the other hand to locate the root portions of said blades.
The invention applies in particular, but not exclusively, to the attachment of blades at their external extremities to a casing surrounding a rotor of the machine. The casing may be xed and constitute, along with the blading which it carries, a stator of the machine. Equally, however, it may be a moving component and thus may constitute an external rotor rotating in the opposite direction to an internal rotor, i.e. as inthe well-known technique of contra-rotating rotors.
The usual blade fixing methods generally mean that, in order to replace a single defective blade, dismantling and reassembling is required of the whole of the blading set to which said single blade belongs. These are difiicult, lengthy and consequently costly operations and, in the case of contra-rotating turbines, the job-time is further increased because it is necessary to dismantle a fixed casing which in this instance surrounds the rotating casing.
It is the object of the invention to achieve a method of fixing by which it is possible in an economical manner to dismantle and reassemble a single blade rapidly, without any need to remove from the body of the machine the whole of the blading set in which the particular blade is located. The invention applies to ordinary compressors and turbines, but is especially valuable in bladed machines having contra-rotating rotors.
According to the invention, in a blade fixing arrangement of the kind set forth, each of the blade roots and the surrounding openings in the wall are dimensioned so that a gap is left therebetween which is adapted to be closed ofi by a mounting insert for each blade which is slidable thereover, there being provided in common to the blades of one set a locking device for locking together the blades, the mounting inserts and the wall, which device permits the selective unlocking of any blade in the said set whilst the others are held locked.
In accordance with an advantageous embodiment of the invention, the device for locking together the iblades of the said set comprises a keeper adapted to slide through 3,501,247 Patented Mar. 17, 1970 passages formed through extensions of the blades and of the mounting inserts in the set, said passages being aligned, in the assembled position, with a groove formed in the wall, and the two extremities of the said keeper having between them, in the assembled position, a peripheral interval at least equivalent to the Width of one of the openings through which the blades are introduced. The keeper may then be fixedly located in relation to the casing by means of a detachable key or the like passing through the gap between the two keeper extremities.
It will be seen that the release of a blade can be effected in a very simple way. All that is necessary is to remove the key and then slide round the keeper until its two extremities embrace the mounting insert of the blade which is to be dismantled.
The description which now follows in relation to the accompanying drawing will indicate by way of a nonlimitative example how the invention may be put into effect,
In the drawing:
FIGURE 1 schematically illustrates, in longitudinal half-section, a compressor having blades adapted to be fixed by means of an arrangement in accordance with the invention;
FIGURE 2 is a partial, longitudinal half-section, on the line II-II of FIGURE 3, through the external casing of a compressor, showing one embodiment of the arrangement for fixing a blade to the casing in accordance with the invention;
FIGURE 3 is a partial, transverse half-section, on the line III-III of FIGURE 2, through the casing and the blades it carries;
FIGURE 4 is a partial, peripheral View, from the exterior, of the casing and the blades it carries;
FIGURE 5 is a schematic pictorial view of part of the casing;
FIGURE 6 is a schematic pictorial View of an intermediate component (mounting insert) associated with each of the blades and assisting in its fixing; and
FIGURE 7 is a schematic pictorial view of one of the blades intended for fixing to the casing.
FIGURE 1 schematically illustrates a machine, in the selected example an axial iiow compressor of the contrarotating type, with an external rotor and an internal rotor, having an annular duct delimited by at least one wall, through which a working fiuid liows. The external rotor comprises in particular the wall 1 which, in the example shown, constitutes an external casing carrying blades 2, fixed at their other ends to discs 3 located coaxially relative to the axis X-X of the machine. Means (not shown) are provided in order to drive this rotor. The internal rotor carries blades 4 mounted on discs 5 fixed to a drive shaft 6.
One embodiment of the invention which will now be described in relation to FIGURES 2 to 7, relates more particularly to the fixing of the blades 2 to the wall 1. In the selected example, which corresponds to a preferred application, this wall is itself movable but it is obvious that the invention could equally well be applied to conventional machines not having contra-rotating rotors, the reference 1 in such case indicating the stator casing of the machine.
The Wall 1 (contra-rotating or fixed) carries, at its periphery, a number of circular grooves 1c equal in number to the number of blading rings or blading sets, said grooves being formed in shoulders 1b. One of these shoulders and its corresponding groove are clearly visible in FIGURE 5. At intervals, the groove and shoulder are interrupted by substantially oblong openings 1a made in the casing 1. It will be seen that the two parts of the shoulder, located at either side of the groove, contain a hole 1d, the purpose of which will be explained hereinafter.
The blades 2 each comprise a root 2a above which there projects a shoulder 2b; the latter is traversed by a passage 2c which can be seen particularly clearly in FIG- URE 7.
Each of the blades 2 is associated with an intermediate component 7, or mounting insert, by means of which, in a manner to be explained later, it is fixed to the casing, Said mounting insert being shown separately in FIG- URE 6.
The mounting insert 7 is for this purpose provided with a substantially oblong base 7a adapted to fit in the opening 1a and flanked peripherally by a flange 7e fwhich serves to locate the insert in a corresponding countersink 1e formed in the casing around the opening 1a. The base 7a is pierced by an opening 7d whose dimensions correspond to those of the root 2a of the blade, and carries two cheeks 7b located at either side of the opening. The cheeks themselves contain holes 7c.
In the assembled position, shown in FIGURES 2, 3, and 4, the intermediate component or mounting insert 7 is inserted into the substantially oblong opening 1a, the fiange 7e abutting against the undercut 1e in the casing, and the blade 2 is fitted with its root portion 2a into the opening 7d in the insert so that its shoulder 2b is located between the cheeks 7b of the insert. The circular groove 1c in the casing, the passages 2c in the blades and the holes 7c in the insert, are now all aligned.
A keeper 8 can now be inserted through the aligned passage system 1c, 2c, 7c thus defined. The purpose of this keeper is simply to lock the set of blades. In the case that the machine is of the contra-rotating type, the expansion forces due to centrifugal action are taken, not by the keeper 8, but by the disc 3 to the periphery of which the blades are fixed in a known manner, for example by the conventional fir-tree formation 2d shown in FIGURES 2 and 3.
The keeper 8 does not have its extremities Srl-8b flush with one another; as FIGURES 3 and 4 show, there is a free space between these ends, the width e of 'which is slightly greater than the width e1 of a mounting insert 7.
In order to lock the set of blades, the keeper is slid circumferentiaily until its two extremities 8a, 8b, are l0- cated at either side of the hole 1d lvisible in FIGURES 3, 4 and 5. Then, there is inserted into the hole a locking device 9 (See FIGURE 5) of some kind, such as a pin, screw or key etc., in order to prevent any further circumferential movement of the keeper.
In order to replace a blade, the procedure is as follows: the first operation is to remove the locking device 9 in order to release the keeper 8. Then, the keeper is slid around until its two extremities 8a, 8b occupy the position shown in FIGURES 3 and 4 in which they surround the mounting insert 7 of the blade 2 which is to be dismantled. This mounting insert being thus unlocked, it can be moved radially towards the axis of the machine, to bring it into a position shown in broken line in FIG- URES 2 and 3.
Then, the formation 2d of the blade is disengaged axially from the disc 3, giving the mounting insert 7 this same axial movement. The blade root then passes through the substantially oblong opening 1a in the casing. As FIGURE 2 shows, this axial disengagement is rendered possible by appropriately dimensioning the mounting inserts so that the distance l, separating the edge of the opening 7d from the front or rear edge of the base 7a of the insert, is greater than the width l1 of the formation 2d by which the blade is fixed to the dise 3.
Finally, the blade 2 is removed radially outside through the opening 7d in the insert and the substantially oblong opening 1a in the casing. Obviously, for this to be possible the width IJ, of the opening 791 must be greater (as 4 FIGURE 3 indicates) than the width b1 of the blade formation 2d.
When this has been done, a replacement blade can be inserted by carrying out the operations, outlined hereinbefore, in the reverse order.
I claim:
1. In a machine having at least one bladed component consisting of a wall carrying at least one set of blades, wherein the root of each blade of the set is detachably fixed in an opening in the said wall, the improvement wherein the blade roots and their associated openings in the -wall are mutually sized so that gaps are left surroundingsaid blade roots received in said wall openings, and wherein a fixing arrangement is provided comprising:
a plurality of inserts, one for each blade, adapted to close the said gaps around the blade roots with the blade roots extending slidably therethrough;
a keeper common to the blades of the one set and adapted to hold in fixed relationship the blades, the inserts and the wall, said keeper being movable to permit release of any blade of the set from the wall said keeper being movable to permit release of any blade of the set from the wall while maintaining its hold'on the remaining blades of the set;
and releasable means for locking said keeper in the position in which all the lblades are fixed.
2. A machine according to claim 1, wherein the keeper is adapted to slide through passages formed in extensions of the blades and of the mounting inserts in one and the same set, said passages being aligned, in the assembled position, with a groove formed in the wall, the two extremities of said keeper, in the assembled position, having a gap between them whose width is at least equal to the width of the openings through which the blades are introduced.
3. A machine according to claim 2, wherein the releasable means for the keeper comprises means for iixedly locating the keeper in relation to the wall.
4. A machine according to claim 3, wherein the locating means is constituted by a detachable key adapted to occupy the gap left between the two extremities of the said keeper.
5. A machine having at least one bladed component consisting of a wall carrying at least one set of blades, wherein the root of each blade of the set is detachably fixed in an opening in the said wall, the blade roots and their associated openings in the wall being mutually sized so that gaps are left surrounding said blade roots when these are received in the said wall openings, and the xing of the blades lbeing completed by a fixing arrangement which comprises a plurality of inserts, one for each blade, adapted to close the said gaps around the blade roots with the blade roots extending slidably therethrough, and a locking device, common to the blades of the one set, for locking together the blades, the inserts and the wall, said locking device being adapted to permit selective unlocking of any blade of the set while the others are held locked.
References Cited UNITED STATES PATENTS 764,451 7/ 1904 Geisenhner. 1,720,754 7/1929 Baumann.
FOREIGN PATENTS 267,405 3/ 1927 Great Britain. 281,032 12/1927 Great Britain. 599,391 3/ 1948 Great Britain.
E-VERETTE A. POWELL, IR., Primary Examinep US. Cl. XR.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR113959 | 1967-07-07 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3501247A true US3501247A (en) | 1970-03-17 |
Family
ID=8634946
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US742658A Expired - Lifetime US3501247A (en) | 1967-07-07 | 1968-07-05 | Blade fixing arrangement |
Country Status (3)
Country | Link |
---|---|
US (1) | US3501247A (en) |
FR (1) | FR1542561A (en) |
GB (1) | GB1208507A (en) |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3985465A (en) * | 1975-06-25 | 1976-10-12 | United Technologies Corporation | Turbomachine with removable stator vane |
US4492517A (en) * | 1983-01-06 | 1985-01-08 | General Electric Company | Segmented inlet nozzle for gas turbine, and methods of installation |
US4632634A (en) * | 1983-10-03 | 1986-12-30 | Nuova Pignone S.P.A. | System for fixing the stator nozzles to a power turbine casing |
FR2585069A1 (en) * | 1985-07-16 | 1987-01-23 | Snecma | DEVICE FOR LIMITING THE ANGULAR DEBATMENT OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK |
US4699569A (en) * | 1985-07-05 | 1987-10-13 | Bbc Brown, Boveri & Company, Limited | Rotor blade ring of an axial flow turbomachine |
US4767273A (en) * | 1987-02-24 | 1988-08-30 | Westinghouse Electric Corp. | Apparatus and method for reducing blade flop in steam turbine |
US4820124A (en) * | 1987-04-13 | 1989-04-11 | Bbc Brown Boveri Ag | Method of manufacturing rotating thermal machine blading consisting of an airfoil, a root and a shroud plate or a shroud by fastening a shroud plate, and a blade manufactured by this method |
US20070059169A1 (en) * | 2005-09-12 | 2007-03-15 | Barry Barnett | Foreign object damage resistant vane assembly |
US20070098557A1 (en) * | 2005-09-12 | 2007-05-03 | Barry Barnett | Vane assembly with outer grommets |
US20070237633A1 (en) * | 2005-09-12 | 2007-10-11 | Barry Barnett | Vane assembly with grommet |
US7628578B2 (en) | 2005-09-12 | 2009-12-08 | Pratt & Whitney Canada Corp. | Vane assembly with improved vane roots |
US20140079552A1 (en) * | 2012-09-11 | 2014-03-20 | Techspace Aero S.A. | Attaching The Blades To The Drum Of An Axial Turbocompressor |
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 |
US20150003989A1 (en) * | 2013-03-08 | 2015-01-01 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine composite vane assembly and method for making same |
US9840929B2 (en) | 2013-05-28 | 2017-12-12 | Pratt & Whitney Canada Corp. | Gas turbine engine vane assembly and method of mounting same |
CN103671251B (en) * | 2012-09-11 | 2018-02-09 | 赛峰航空助推器股份有限公司 | Blade is connected on the cylindrical rotor of axial flow turbo compressor |
US20190234222A1 (en) * | 2018-01-30 | 2019-08-01 | United Technologies Corporation | Angled vane slot |
US10767502B2 (en) | 2016-12-23 | 2020-09-08 | Rolls-Royce Corporation | Composite turbine vane with three-dimensional fiber reinforcements |
CN112324520A (en) * | 2020-10-27 | 2021-02-05 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2697285B1 (en) * | 1992-10-28 | 1994-11-25 | Snecma | Blade end locking system. |
EP1548233B1 (en) * | 2003-12-18 | 2006-08-02 | Techspace Aero S.A. | Fastening device for stator blades and compressor stator stage comprising such a fastening device |
DE602005024425D1 (en) | 2005-12-22 | 2010-12-09 | Techspace Aero Milmort | Bucket ring of a turbomachine, turbomachine with such a guide ring and vane |
FR2995934B1 (en) * | 2012-09-24 | 2018-06-01 | Safran Aircraft Engines | AUBE FOR TURBOMACHINE RECTIFIER |
US20140255194A1 (en) * | 2012-12-21 | 2014-09-11 | General Electric Company | Tip shrouds of turbine rotor blades and methods of manufacture related thereto |
WO2015147821A1 (en) * | 2014-03-27 | 2015-10-01 | Siemens Aktiengesellschaft | Stator vane support system within a gas turbine engine |
FR3051825B1 (en) * | 2016-05-27 | 2020-02-28 | Safran Aircraft Engines | TURBOMACHINE RECTIFIER, AND METHOD FOR CHANGING THE BLADE SETTING |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US764451A (en) * | 1903-12-19 | 1904-07-05 | Gen Electric | Bucket construction for turbines. |
GB267405A (en) * | 1926-09-09 | 1927-03-17 | Charles Oliver | Improvements in or relating to shrouding for turbine blades and the like |
GB281032A (en) * | 1926-09-09 | 1927-12-01 | Karl Baumann | Improvements relating to elastic fluid turbines |
US1720754A (en) * | 1926-09-09 | 1929-07-16 | Westinghouse Electric & Mfg Co | Turbine-blade shrouding |
GB599391A (en) * | 1945-05-25 | 1948-03-11 | Power Jets Res & Dev Ltd | Improvements in and relating to axial flow compressors, turbines and the like machines |
-
0
- FR FR1542561D patent/FR1542561A/en active Active
-
1968
- 1968-07-01 GB GB31338/68A patent/GB1208507A/en not_active Expired
- 1968-07-05 US US742658A patent/US3501247A/en not_active Expired - Lifetime
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US764451A (en) * | 1903-12-19 | 1904-07-05 | Gen Electric | Bucket construction for turbines. |
GB267405A (en) * | 1926-09-09 | 1927-03-17 | Charles Oliver | Improvements in or relating to shrouding for turbine blades and the like |
GB281032A (en) * | 1926-09-09 | 1927-12-01 | Karl Baumann | Improvements relating to elastic fluid turbines |
US1720754A (en) * | 1926-09-09 | 1929-07-16 | Westinghouse Electric & Mfg Co | Turbine-blade shrouding |
GB599391A (en) * | 1945-05-25 | 1948-03-11 | Power Jets Res & Dev Ltd | Improvements in and relating to axial flow compressors, turbines and the like machines |
Cited By (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3985465A (en) * | 1975-06-25 | 1976-10-12 | United Technologies Corporation | Turbomachine with removable stator vane |
US4492517A (en) * | 1983-01-06 | 1985-01-08 | General Electric Company | Segmented inlet nozzle for gas turbine, and methods of installation |
US4632634A (en) * | 1983-10-03 | 1986-12-30 | Nuova Pignone S.P.A. | System for fixing the stator nozzles to a power turbine casing |
US4699569A (en) * | 1985-07-05 | 1987-10-13 | Bbc Brown, Boveri & Company, Limited | Rotor blade ring of an axial flow turbomachine |
FR2585069A1 (en) * | 1985-07-16 | 1987-01-23 | Snecma | DEVICE FOR LIMITING THE ANGULAR DEBATMENT OF AUBES MOUNTED ON A TURBOMACHINE ROTOR DISK |
EP0214875A1 (en) * | 1985-07-16 | 1987-03-18 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Damping element limiting the angular deflection of turbo machine rotor vanes |
US4723889A (en) * | 1985-07-16 | 1988-02-09 | Societe Nationale D'etude Et De Constructions De Moteur D'aviation "S.N.E.C.M.A." | Fan or compressor angular clearance limiting device |
US4767273A (en) * | 1987-02-24 | 1988-08-30 | Westinghouse Electric Corp. | Apparatus and method for reducing blade flop in steam turbine |
US4820124A (en) * | 1987-04-13 | 1989-04-11 | Bbc Brown Boveri Ag | Method of manufacturing rotating thermal machine blading consisting of an airfoil, a root and a shroud plate or a shroud by fastening a shroud plate, and a blade manufactured by this method |
US7494316B2 (en) | 2005-09-12 | 2009-02-24 | Pratt & Whitney Canada Corp. | Foreign object damage resistant vane assembly |
US20070098557A1 (en) * | 2005-09-12 | 2007-05-03 | Barry Barnett | Vane assembly with outer grommets |
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 |
US7413400B2 (en) | 2005-09-12 | 2008-08-19 | Pratt & Whitney Canada Corp. | Vane assembly with grommet |
US20070059169A1 (en) * | 2005-09-12 | 2007-03-15 | Barry Barnett | Foreign object damage resistant vane assembly |
US7530782B2 (en) | 2005-09-12 | 2009-05-12 | Pratt & Whitney Canada Corp. | Foreign object damage resistant vane assembly |
US7628578B2 (en) | 2005-09-12 | 2009-12-08 | Pratt & Whitney Canada Corp. | Vane assembly with improved vane roots |
US7637718B2 (en) | 2005-09-12 | 2009-12-29 | Pratt & Whitney Canada Corp. | Vane assembly with outer grommets |
US8696311B2 (en) | 2011-03-29 | 2014-04-15 | Pratt & Whitney Canada Corp. | Apparatus and method for gas turbine engine vane retention |
CN103671251A (en) * | 2012-09-11 | 2014-03-26 | 航空技术空间股份有限公司 | Attaching the blades to the drum of an axial turbocompressor |
US20140079552A1 (en) * | 2012-09-11 | 2014-03-20 | Techspace Aero S.A. | Attaching The Blades To The Drum Of An Axial Turbocompressor |
US9598968B2 (en) * | 2012-09-11 | 2017-03-21 | Safran Aero Boosters Sa | Attaching the blades to the drum of an axial turbocompressor |
CN103671251B (en) * | 2012-09-11 | 2018-02-09 | 赛峰航空助推器股份有限公司 | Blade is connected on the cylindrical rotor of axial flow turbo compressor |
US20140147262A1 (en) * | 2012-11-27 | 2014-05-29 | Techspace Aero S.A. | Axial Turbomachine Stator with Segmented Inner Shell |
US20150003989A1 (en) * | 2013-03-08 | 2015-01-01 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine composite vane assembly and method for making same |
US10174619B2 (en) * | 2013-03-08 | 2019-01-08 | Rolls-Royce North American Technologies Inc. | Gas turbine engine composite vane assembly and method for making same |
US11053801B2 (en) | 2013-03-08 | 2021-07-06 | Rolls-Royce Corporation | Gas turbine engine composite vane assembly and method for making the same |
US9840929B2 (en) | 2013-05-28 | 2017-12-12 | Pratt & Whitney Canada Corp. | Gas turbine engine vane assembly and method of mounting same |
US10767502B2 (en) | 2016-12-23 | 2020-09-08 | Rolls-Royce Corporation | Composite turbine vane with three-dimensional fiber reinforcements |
US20190234222A1 (en) * | 2018-01-30 | 2019-08-01 | United Technologies Corporation | Angled vane slot |
CN112324520A (en) * | 2020-10-27 | 2021-02-05 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
Also Published As
Publication number | Publication date |
---|---|
FR1542561A (en) | |
GB1208507A (en) | 1970-10-14 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3501247A (en) | Blade fixing arrangement | |
US3393862A (en) | Bladed rotors | |
US3088708A (en) | Compressor blade locking device | |
US3395891A (en) | Lock for turbomachinery blades | |
US3023998A (en) | Rotor blade retaining device | |
CA2715271C (en) | Gas turbine engine balancing | |
DE102005017148B4 (en) | Rotary sealing arrangement for cooling circuits of turbine blades | |
EP3064717B1 (en) | Turbine shroud with axially separated pressure compartments | |
US5007800A (en) | Rotor blade fixing for turbomachine rotors | |
US3104091A (en) | Turbines | |
US4701105A (en) | Anti-rotation feature for a turbine rotor faceplate | |
US3689177A (en) | Blade constraining structure | |
DE2627702A1 (en) | AXIAL FLOW MACHINE | |
GB779059A (en) | Improvements in or relating to axial-flow fluid machines, for example compressors orturbines of gas-turbine engines | |
US2931623A (en) | Gas turbine rotor assembly | |
EP1694943B1 (en) | Turbomachine | |
US3397865A (en) | Bladed rotor for a fluid flow machine such as a gas turbine engine | |
US9376926B2 (en) | Gas turbine engine fan blade lock assembly | |
US20070022738A1 (en) | Reinforcement rings for a tip turbine engine fan-turbine rotor assembly | |
GB2401655A (en) | A rotor blade arrangement | |
GB1575500A (en) | Device for securing blades of a turbine rotor | |
US2848190A (en) | Radial flow turbo-machines | |
US2935296A (en) | Blade retaining means | |
DE2833220A1 (en) | DEVICE FOR COOLING GAS TURBINES | |
US5611669A (en) | Turbines with platforms between stages |