US2869820A - Rotors for axial flow compressors or turbines - Google Patents
Rotors for axial flow compressors or turbines Download PDFInfo
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- US2869820A US2869820A US281958A US28195852A US2869820A US 2869820 A US2869820 A US 2869820A US 281958 A US281958 A US 281958A US 28195852 A US28195852 A US 28195852A US 2869820 A US2869820 A US 2869820A
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- disc
- carrying
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
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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 rotors for rotary power conversion machines such as axial flow compressors or turbines which rotors are of the kind comprising at least three blade-carrying discs joined at or near their rims to form a drum structure.
- a principal object of the invention is to provide such a structure which while being light in weight and readily assembled and dismantled shall be stiff against lateral defiections so a to provide a high critical whirling speed.
- Another object of'the invention is to provide such a structure in which, while maintaining a minimum overall length of the rotor and its supporting bearings, the end blade-carrying discs are substantially relieved of bending stresses associated with lateral deflection.
- an end blade-carrying disc has a frusto-conical disc attached at each side at a common intermediate radius one being convergent and carrying at its end of minimum diameter a stub shaft, and the other being divergent and forming part of another of the blade-carrying discs or being attached to another such disc at or near its
- the invention also includes a rotor of the kind described in which the disc carrying the lowest pressure blading is flat and has a frusto-conical disc attached at each side at a common intermediate radius, one being convergent and carrying at its end of minimum diameter a stub shaft, and the other being divergent and attached at its end of maximum diameter to the next adjacent blade-carrying disc at or, near its rim.
- an end blade-carrying disc has a central flat portion and an outer fr'usto-conical portion diverging axially and radially away from the transverse central plane of the rotor, a convergent frusto-conical disc carrying at its end of minimum diameter a stub shaft, being attached at its end of maximum diameter at the margin of the central fiat portion on one side and on the other side the next or next but one blade-carrying disc being of oppositely dished planoconical form and attached directly or with an interposed disc at the margin of said central flat portion.
- All the blade-carrying discs may be secured together at or near their rims with interposed spacing members by bolts extending from end to end of the drum structure assembly, or by bolts which are individual to the 'bladecarrying discs.
- Figure 1 illustrates an axial flow compressor having five stages (l-V) and intended for use as the low pressure compressor of a jet propulsion compound gas turbine
- Figure 2 illustrates an axial fiow compressor having seven stages (l-VII) intended to follow the compressor illustrated in Figure 1 as a high pressure compressor,
- Figure 3 illustrates an axial flow low pressure compressor having six stages (IVI), the compressor being of the constant root diameter type, and
- Figure 4 illustrates an axial flow highpressure compressor having eight stages (I-VIII), the compressor being' of the constant root diameter type.”
- the compressor illustrated in Figure l is of the type having blades 5 of constant mean radius x and a ratio of hub diameter to tip diameter at the first row of moving blades (a/ b) of about 0.45.
- the blades 5 are mounted around the rims of five discs 6, 7, 8a, 8b all of which are solid, i. e. have no central holes.
- the first three discs 6, 7 are fiat, that is to say they are symmetrical on each side of a fiat central transverse plane, while the last two discs 8a and 8b at the high pressure end are dished toward one another and comprise central flat portions 9 in abutting relation and outer frusto-conical parts or portions 10 diverging from one another.
- Discs 6 and 8b constitute the end blade-carrying discs. At their rims the discs are spaced from one another by members 11 de fining the inner conical surface of the annular air passage 12 and are connected to the said spacing members by rows of bolts 13 individual to each disc so as to form a frusto-conical drum structure.
- a short convergent frusto-conical disc 14 is bolted to the central flat portion of the end disc by bolts 15 which also pass through the fiat portion 9 of the discs so that these three parts are firmly connected"
- a similar short frusto-conical disc 19 carrying a stub shaft 51 at its end of minimum diameter is bolted to the flat first stage disc 6 by a ring of bolts 20 arranged about midway between its centre and rim.
- Disc 6 is advantageously made fiat since this is the best form for taking the centrifugal loads from the blading, which are highest for this stage, but it has the disadvantage with the arrangement as so far described that forces associated with lateral defiection of the rotor tend to bend the disc, against which form of distortion it is relatively weak.
- a frustoconical disc or stiffening member 21 is attached to disc 6 by the bolts 29 and extends within the drum structure divergently to the rim of the second stage disc 7, where its end of maximum diameter is sandwiched between the rim and its spacing member 11.
- the v frusto-conical disc 19, frusto-conical stifiening member 21, spacing members 11 between the discs 7, 8a of stages 11, III and IV, disc 8a of stage IV and frusto-conical disc 14 form a strength drum of generally peg top form from which the discs 6 and 8b project and are stabilised by the first and last spacing members 11.
- blade-carrying discs 25a, 25b, 26 and 27a, 27b are all provided with central holes for the passage of the shaft 17 driving the low pressure compressor.
- the high pressure compressor has a constant tip diameter, so that the rotor drum has a conical outer surface 'as in the construction of Figure 1, in this case however the hub-tip ratio is very much smaller, being about 0.69, and this has permitted the first and second stage discs 25a, 25b to be dished towards one another to form a construction as described for the high pressure end of the construction of Figure l, a frusto-conical disc 31 carrying a stub shaft 53 being bolted to the discs 25a, 25b.
- the high pressure end is also constructed in a similar manner but has an additional frusto-conical disc 28 carry ing at its end of maximum diameter part of a labyrinth seal 29.
- the additional disc 28 has its end of minimum Patented Jan.
- the first row of moving blades has a hub tip ratio of about 0.6
- the first and second and the fifth and sixth blade-carrying discs 35a, 35b, 36a, 36b respectively i. e. at the ends of the rotor
- the bladecarrying discs are bolted together with interposed spacing members 37 defining the inner cylindrical surface of the air passage between the blades by a ring of bolts 38 extending from end to end of the rotor.
- each of the bolted joints is preferably provided with a locating peg or dowel (not shown) and similar provision may be made in the other constructions described.
- the compressor rotor has a hub-tip ratio at the first row of moving blades of about 0.75 and is constructed as described with reference to Figure 3 except that at the low pressure end, instead of the first and second discs being dished towards one another, the second disc 46 is fiat and clamped at an intermediate radius between the first and third discs 41a, 41b, which are dished towards the disc 40, a frustoconical disc 42 carrying a stub shaft 56 at its end of minimum diameter being also attached at the same clamping radius.
- the other discs in this construction all have central holes for the passage of a shaft for driving an adjacent low pressure compressor, the discs being suitably increased in thickness around the holes to provide the necessary reinforcement as described with reference to Figure 2.
- All the discs except the second extend inwardly to a tube held between the stub shafts, the second projecting only a short distance inwardly of the clamping radius and being provided around the central hole with a thickened rim 43 spigotting into recesses 44 in the disc 41a, 41b so that these latter provide an anchorage for the inner rim.
- the discs are held together with interposed spacing members 45 by bolts (at 46) extending from end to end of the rotor as in the third construction.
- the invention is also applicable to rotor constructions in which the blades are held between adjacent discs instead of being mounted around the disc rims.
- the blades take the place of the spacing members previously referred to, while the rims of the discs form the inner surface of the annular air passage between the blade rows.
- a lightweight rotor for an axial flow rotary power conversion machine said rotor comprising at least two end blade-carrying discs, an intermediate blade-carrying disc, and means joining said discs together and connected thereto adjacent their rims to form a rigid drum structure: a first frusto-conical disc bolted at an intermediate radius to the side of one of said end blade-carrying discs forming an end face of said drum structure, said frustoconical disc being of a lesser maximum diameter than said end blade-carrying disc and being carried by said end blade-carrying disc so as to be concentric therewith'and convergent away therefrom, a stub shaft for 4.
- a blade carrying disc having at least a frusto-conical part bolted to said one end bladecarrying disc at said intermediate radius on the side thereof remote from said first frusto-conical disc so as to be concentric with said one end blade-carrying disc, said frusto-conical part being divergent away from said one end blade carrying disc; and bolts attaching said rusto-conical part at its end of maximum diameter to the outer periphery of an adjacent part of said drum structure.
- a rotor as claimed in claim 1 wherein said means to join said blade-carrying discs together adjacent their rims comprises a plurality of bolts and interposed spacing members, between each adjacent pair of discs.
- a lightweight'rotor for an axial flow rotary power conversion machine said rotor comprising at least two end blade-carrying discs, an intermediate blade carrying disc, and means joining said discs together and connected thereto adjacent their rims to form a rigid drum structure: a first frusto-conical disc bolted at an intermediate radius to the side of one of said end blade-carrying discs forming an end face of said drum structure, which end blade-carrying disc is fiat, said frusto-conical disc being of a lesser maximum diameter than said one end bladecarrying disc and being carried by said one end bladecarrying disc so as to be concentric therewith and convergent away therefrom, a stub shaft for said rotor on said first frusto-conical disc; and a second frusto-conical disc bolted to said one end blade carrying disc at said intermediate radius on the side thereof remote from said first frusto-conical disc so as to be concentric with said one end blade-carrying
- a lightweight rotor for an axial flow rotary power conversion machine said rotor comprising at least two end blade-carrying discs, an intermediate blade-carrying disc, and means joining said discs together and connected thereto adjacent their rims to form a rigid drum structure: a first frusto-conical disc bolted at an intermediate radius to the side of one of said end blade-carrying discs forming an end face of said drum structure, said frustoconical disc being of a lesser maximum diameter than said one end blade-carrying disc and being carried by said one end blade-carrying disc so as to be concentric therewith and convergent away therefrom, a stub shaft for said rotor on said first frusto-c'onical disc; and a second frusto-conical disc bolted to said one end blade-carrying disc at said intermediate radius on the side thereof remote from said first frusto-conical disc so as to be concentric with said one end blade-carrying disc, said
- a rotor as claimed in claim 2 further comprising spacing means between said frusto-conical part and said one of said end blade carrying discs, the frusto-conical part being bolted to said one of said end blade carrying discs through said spacing means.
- a lightweight rotor for an axial flow rotary power conversion machine comprising a plurality of blade carrying discs including at least two endblade carrying discs and means joining said discs together and connected thereto adjacent their rims to form a rigid drum structure; a first frusto-conical disc bolted at an intermediate radius to the side of the end blade carrying disc at the low pressure end of the rotor which forms an end face of said drum structure, said first frusto-conical disc being of a lesser maximum diameter than said low pressure end blade carrying disc, and being carried by said low pressure end blade-carrying disc so as to be concentric therewith and convergent away therefrom; a first stub shaft for said rotor on said first frusto-conical disc at its end of minimum diameter; a second frusto-conical disc bolted to said low pressure end blade carrying disc at said intermediate radius on the side thereof remote from said first frusto-conical disc so as to be concentric with said low pressure end
Description
Jan. 20, 1959 F. 3. l. MARCHANT ETAL 2,869,320
ROTORS FOR AXIAL FLOW goMPREssoRs 0R TURBINES s Sheets-Sheet 1 Filed April 12, 1952 Jan. 20, 1959 F. c. MARCHANT ETAL 2,369,320
ROTORS FOR AXIAL FLOW COMPRESSORS OR TURBINES I Filed April 12, 1952 3 Sheets-Shet 2- 1 L I U I I I 26 12g 2% J 5": \,2% g E 5 2i 51 I 50 J3 v f a? w my? 53 llV/E/WWIS F6. 1. MAHCH/I/VT W. J MORLEY 5* E. BRIGGS United States Patent ROTORS FOR AXIAL FLOW COMPRESSORS 0R TURBINES Francis Charles Ivor Marcllant, William James Morley, and Ernest Briggs, Bristol, England, assignors, by mesne assignments, to Bristol Aero=Engines Limited, Bristol, England, a British company Appiication April 12, 1952, Serial No. 281,958 Claims priority, application Great Britain April 18, 1951 Claims. (Cl. 253-69) This invention relates to rotors for rotary power conversion machines such as axial flow compressors or turbines which rotors are of the kind comprising at least three blade-carrying discs joined at or near their rims to form a drum structure.
A principal object of the invention is to provide such a structure which while being light in weight and readily assembled and dismantled shall be stiff against lateral defiections so a to provide a high critical whirling speed.
Another object of'the invention is to provide such a structure in which, while maintaining a minimum overall length of the rotor and its supporting bearings, the end blade-carrying discs are substantially relieved of bending stresses associated with lateral deflection.
According to the invention, in a rotor of the kind described, an end blade-carrying disc has a frusto-conical disc attached at each side at a common intermediate radius one being convergent and carrying at its end of minimum diameter a stub shaft, and the other being divergent and forming part of another of the blade-carrying discs or being attached to another such disc at or near its The invention also includes a rotor of the kind described in which the disc carrying the lowest pressure blading is flat and has a frusto-conical disc attached at each side at a common intermediate radius, one being convergent and carrying at its end of minimum diameter a stub shaft, and the other being divergent and attached at its end of maximum diameter to the next adjacent blade-carrying disc at or, near its rim. t
In another arrangement according to the invention an end blade-carrying disc has a central flat portion and an outer fr'usto-conical portion diverging axially and radially away from the transverse central plane of the rotor, a convergent frusto-conical disc carrying at its end of minimum diameter a stub shaft, being attached at its end of maximum diameter at the margin of the central fiat portion on one side and on the other side the next or next but one blade-carrying disc being of oppositely dished planoconical form and attached directly or with an interposed disc at the margin of said central flat portion.
All the blade-carrying discs may be secured together at or near their rims with interposed spacing members by bolts extending from end to end of the drum structure assembly, or by bolts which are individual to the 'bladecarrying discs.
Figure 1 illustrates an axial flow compressor having five stages (l-V) and intended for use as the low pressure compressor of a jet propulsion compound gas turbine,
Figure 2 illustrates an axial fiow compressor having seven stages (l-VII) intended to follow the compressor illustrated in Figure 1 as a high pressure compressor,
Figure 3 illustrates an axial flow low pressure compressor having six stages (IVI), the compressor being of the constant root diameter type, and
Figure 4 illustrates an axial flow highpressure compressor having eight stages (I-VIII), the compressor being' of the constant root diameter type." I
The compressor illustrated in Figure l is of the type having blades 5 of constant mean radius x and a ratio of hub diameter to tip diameter at the first row of moving blades (a/ b) of about 0.45. The blades 5 are mounted around the rims of five discs 6, 7, 8a, 8b all of which are solid, i. e. have no central holes. The first three discs 6, 7 are fiat, that is to say they are symmetrical on each side of a fiat central transverse plane, while the last two discs 8a and 8b at the high pressure end are dished toward one another and comprise central flat portions 9 in abutting relation and outer frusto-conical parts or portions 10 diverging from one another. Discs 6 and 8b constitute the end blade-carrying discs. At their rims the discs are spaced from one another by members 11 de fining the inner conical surface of the annular air passage 12 and are connected to the said spacing members by rows of bolts 13 individual to each disc so as to form a frusto-conical drum structure. At the high pressure end of the drum structure a short convergent frusto-conical disc 14 is bolted to the central flat portion of the end disc by bolts 15 which also pass through the fiat portion 9 of the discs so that these three parts are firmly connected" At the low pressure end of the rotor a similar short frusto-conical disc 19 carrying a stub shaft 51 at its end of minimum diameter is bolted to the flat first stage disc 6 by a ring of bolts 20 arranged about midway between its centre and rim. Disc 6 is advantageously made fiat since this is the best form for taking the centrifugal loads from the blading, which are highest for this stage, but it has the disadvantage with the arrangement as so far described that forces associated with lateral defiection of the rotor tend to bend the disc, against which form of distortion it is relatively weak.
the conical disc 19, and therefore its projection, a frustoconical disc or stiffening member 21 is attached to disc 6 by the bolts 29 and extends within the drum structure divergently to the rim of the second stage disc 7, where its end of maximum diameter is sandwiched between the rim and its spacing member 11.
Considering the rotor construction in'axial section, the v frusto-conical disc 19, frusto-conical stifiening member 21, spacing members 11 between the discs 7, 8a of stages 11, III and IV, disc 8a of stage IV and frusto-conical disc 14 form a strength drum of generally peg top form from which the discs 6 and 8b project and are stabilised by the first and last spacing members 11.
Referringto Figure 2, in this case the blade-carrying discs 25a, 25b, 26 and 27a, 27b are all provided with central holes for the passage of the shaft 17 driving the low pressure compressor.
The high pressure compressor has a constant tip diameter, so that the rotor drum has a conical outer surface 'as in the construction of Figure 1, in this case however the hub-tip ratio is very much smaller, being about 0.69, and this has permitted the first and second stage discs 25a, 25b to be dished towards one another to form a construction as described for the high pressure end of the construction of Figure l, a frusto-conical disc 31 carrying a stub shaft 53 being bolted to the discs 25a, 25b. The high pressure end is also constructed in a similar manner but has an additional frusto-conical disc 28 carry ing at its end of maximum diameter part of a labyrinth seal 29. The additional disc 28 has its end of minimum Patented Jan. 20, 1959 To overcome this objection without increasing the maximum diameter and taper of diameter sandwiched betweenthe disc 27b and the frustoconical disc 38 which carries a stub shaft 54. The two stub shafts 53, 54 also retain between them a tubular member 32 passing through the central holes of the discs. The discs 26 of stages Eli and V bear on the outside of this tubular member, as at 33, for steadying purposes, the remaining discs being provided with clearance holes.
Referring to Figure 3, in the compressor rotor illustrated the first row of moving blades has a hub tip ratio of about 0.6, the first and second and the fifth and sixth blade-carrying discs 35a, 35b, 36a, 36b respectively (i. e. at the ends of the rotor) are dished towards one another and provided with frusto-conical discs 39 carrying stub shafts as described above for the high pressure end in the construction of Figure 1. At their rims all the bladecarrying discs are bolted together with interposed spacing members 37 defining the inner cylindrical surface of the air passage between the blades by a ring of bolts 38 extending from end to end of the rotor. To ensure correct re-assembly after dismantling, each of the bolted joints is preferably provided with a locating peg or dowel (not shown) and similar provision may be made in the other constructions described.
In the construction shown in Figure 4 the compressor rotor has a hub-tip ratio at the first row of moving blades of about 0.75 and is constructed as described with reference to Figure 3 except that at the low pressure end, instead of the first and second discs being dished towards one another, the second disc 46 is fiat and clamped at an intermediate radius between the first and third discs 41a, 41b, which are dished towards the disc 40, a frustoconical disc 42 carrying a stub shaft 56 at its end of minimum diameter being also attached at the same clamping radius. The other discs in this construction all have central holes for the passage of a shaft for driving an adjacent low pressure compressor, the discs being suitably increased in thickness around the holes to provide the necessary reinforcement as described with reference to Figure 2. All the discs except the second extend inwardly to a tube held between the stub shafts, the second projecting only a short distance inwardly of the clamping radius and being provided around the central hole with a thickened rim 43 spigotting into recesses 44 in the disc 41a, 41b so that these latter provide an anchorage for the inner rim. At their outer rims the discs are held together with interposed spacing members 45 by bolts (at 46) extending from end to end of the rotor as in the third construction.
The several constructions described with reference to the accompanying drawings are given by way of example only.
The invention is also applicable to rotor constructions in which the blades are held between adjacent discs instead of being mounted around the disc rims. In such constructions the blades take the place of the spacing members previously referred to, while the rims of the discs form the inner surface of the annular air passage between the blade rows.
Although the invention has been particularly described as applied to compressors it will be clear that the same principles can apply in the case of multi-stage axial flow turbines.
We claim:
1. In a lightweight rotor for an axial flow rotary power conversion machine said rotor comprising at least two end blade-carrying discs, an intermediate blade-carrying disc, and means joining said discs together and connected thereto adjacent their rims to form a rigid drum structure: a first frusto-conical disc bolted at an intermediate radius to the side of one of said end blade-carrying discs forming an end face of said drum structure, said frustoconical disc being of a lesser maximum diameter than said end blade-carrying disc and being carried by said end blade-carrying disc so as to be concentric therewith'and convergent away therefrom, a stub shaft for 4. said rotor on said first frusto-conical disc at its end of minimum diameter; a blade carrying disc having at least a frusto-conical part bolted to said one end bladecarrying disc at said intermediate radius on the side thereof remote from said first frusto-conical disc so as to be concentric with said one end blade-carrying disc, said frusto-conical part being divergent away from said one end blade carrying disc; and bolts attaching said rusto-conical part at its end of maximum diameter to the outer periphery of an adjacent part of said drum structure.
2. A rotor as claimed in claim 1 wherein said one of said end blade-carrying discs has a central flat portion and an outer frusto-conical portion diverging axially and radially away from the transverse central plane of the rotor, and said first frusto-conical disc is bolted to said one end blade-carrying disc at the margin of said central fiat portion, and said blade-carrying disc having the frusto-conical part is next adjacent to said one end bladecarrying disc and said frusto-conical part is bolted to said one of said end blade-carrying discs at the margin of said central flat portion.
3. A rotor as claimed in claim 1 wherein said means to join said blade-carrying discs together adjacent their rims comprises a plurality of bolts and interposed spacing members, between each adjacent pair of discs.
4. In a lightweight'rotor for an axial flow rotary power conversion machine said rotor comprising at least two end blade-carrying discs, an intermediate blade carrying disc, and means joining said discs together and connected thereto adjacent their rims to form a rigid drum structure: a first frusto-conical disc bolted at an intermediate radius to the side of one of said end blade-carrying discs forming an end face of said drum structure, which end blade-carrying disc is fiat, said frusto-conical disc being of a lesser maximum diameter than said one end bladecarrying disc and being carried by said one end bladecarrying disc so as to be concentric therewith and convergent away therefrom, a stub shaft for said rotor on said first frusto-conical disc; and a second frusto-conical disc bolted to said one end blade carrying disc at said intermediate radius on the side thereof remote from said first frusto-conical disc so as to be concentric with said one end blade-carrying disc, said second frusto-conical disc being divergent away from said one end blade-carrying disc and being bolted to said intermediate bladecarrying disc.
5. In a lightweight rotor for an axial flow rotary power conversion machine said rotor comprising at least two end blade-carrying discs, an intermediate blade-carrying disc, and means joining said discs together and connected thereto adjacent their rims to form a rigid drum structure: a first frusto-conical disc bolted at an intermediate radius to the side of one of said end blade-carrying discs forming an end face of said drum structure, said frustoconical disc being of a lesser maximum diameter than said one end blade-carrying disc and being carried by said one end blade-carrying disc so as to be concentric therewith and convergent away therefrom, a stub shaft for said rotor on said first frusto-c'onical disc; and a second frusto-conical disc bolted to said one end blade-carrying disc at said intermediate radius on the side thereof remote from said first frusto-conical disc so as to be concentric with said one end blade-carrying disc, said second frusto-conical disc being divergent away from said one end blade-carrying disc and being bolted at its end of maximum diameter to said intermediate blade-carrying disc. I
6. A rotor as claimed in claim 1, wherein said one of said end blade carrying discs is an unpcrforated disc, and said blade carrying disc having at least a frusto-conical part is an unperforated disc, the frusto-conical part forming an outer peripheral portion of the disc.
7. A rotor as claimed in claim 2, wherein the cone angle of the outer frusto conical portion of said one end blade carrying disc is substantially equal to the cone angle of said frusto-conical part.
8. A rotor as claimed in claim 2, wherein said central flat portion of said one of said end blade carrying discs is unperforated, and said next adjacent blade carrying disc has a central unperforated flat portion.
9. A rotor as claimed in claim 2, further comprising spacing means between said frusto-conical part and said one of said end blade carrying discs, the frusto-conical part being bolted to said one of said end blade carrying discs through said spacing means.
10. In a lightweight rotor for an axial flow rotary power conversion machine, said rotor comprising a plurality of blade carrying discs including at least two endblade carrying discs and means joining said discs together and connected thereto adjacent their rims to form a rigid drum structure; a first frusto-conical disc bolted at an intermediate radius to the side of the end blade carrying disc at the low pressure end of the rotor which forms an end face of said drum structure, said first frusto-conical disc being of a lesser maximum diameter than said low pressure end blade carrying disc, and being carried by said low pressure end blade-carrying disc so as to be concentric therewith and convergent away therefrom; a first stub shaft for said rotor on said first frusto-conical disc at its end of minimum diameter; a second frusto-conical disc bolted to said low pressure end blade carrying disc at said intermediate radius on the side thereof remote from said first frusto-conical disc so as to be concentric with said low pressure end blade carrying disc, said second frusto-conical disc being divergent away from said low pressure end blade carrying disc and being bolted at its end of maximum diameter to said drum structure at the outer periphery of the drum structure; a third frusto conical disc bolted at an intermediate radius to the side of the end blade carrying disc at the high pressure end of the rotor which forms the other end face of said drum structure, said third frusto-conical disc being of lesser maximum diameter than said high pressure end bladecarrying disc and being carried by said high pressure end blade-carrying disc so as to be concentric therewith and convergent away therefrom; a second stub shaft for said rotor on said third frusto-conical disc at its end of minimum diameter; a blade carrying disc having at least a frusto-conical part bolted to said high pressure end blade carrying disc at said intermediate radius of the high pressure end blade carrying disc on the side thereof remote from said third frusto-conical disc so as to be concentric with said high pressure end blade carrying disc, said frusto-conical part being divergent away from said high pressure end blade carrying disc; and bolts attaching said frusto-conical part at its end of maximum diameter to the outer periphery of said drum structure.
References Cited in the file of this patent UNITED STATES PATENTS 770,207 Wilkinson Sept. 13, 1904 1,030,153 Barbezat June 18, 1912 2,213,940 Jendrassik Sept. 3, 1940 2,445,661 Constant et a1. July 20, 1948 2,579,745 Lombard Dec. 25, 1951 2,662,685 Blane Dec. 15, 1953 FOREIGN PATENTS 223,615 Switzerland Dec. 16, 1942 543,985 Great Britain Mar. 23, 1942
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9110/51A GB706563A (en) | 1951-04-18 | 1951-04-18 | Improvements in or relating to rotors for axial flow compressors or turbines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2869820A true US2869820A (en) | 1959-01-20 |
Family
ID=9865550
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US281958A Expired - Lifetime US2869820A (en) | 1951-04-18 | 1952-04-12 | Rotors for axial flow compressors or turbines |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US2869820A (en) |
| FR (1) | FR1057171A (en) |
| GB (1) | GB706563A (en) |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2951677A (en) * | 1956-03-12 | 1960-09-06 | Curtiss Wright Corp | Turbine rotor construction |
| US3038652A (en) * | 1959-10-21 | 1962-06-12 | United Aircraft Corp | Intermediate compressor case |
| US3056579A (en) * | 1959-04-13 | 1962-10-02 | Gen Electric | Rotor construction |
| US3083947A (en) * | 1960-03-03 | 1963-04-02 | United Aircraft Corp | Compressor spacer |
| US3597109A (en) * | 1968-05-31 | 1971-08-03 | Rolls Royce | Gas turbine engine axial flow multistage compressor |
| US3976399A (en) * | 1970-07-09 | 1976-08-24 | Kraftwerk Union Aktiengesellschaft | Rotor of disc construction for single-shaft gas turbine |
| FR2456835A1 (en) * | 1979-05-17 | 1980-12-12 | United Technologies Corp | ROTOR ASSEMBLY HAVING MULTI-STAGE DISC |
| FR2481379A1 (en) * | 1980-04-28 | 1981-10-30 | United Technologies Corp | COMPRESSION SECTION FOR A ROTARY FLOW AXIAL MACHINE |
| US4460309A (en) * | 1980-04-28 | 1984-07-17 | United Technologies Corporation | Compression section for an axial flow rotary machine |
| US4737076A (en) * | 1986-10-20 | 1988-04-12 | United Technologies Corporation | Means for maintaining concentricity of rotating components |
| US5397215A (en) * | 1993-06-14 | 1995-03-14 | United Technologies Corporation | Flow directing assembly for the compression section of a rotary machine |
| US5579644A (en) * | 1993-10-13 | 1996-12-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbo-jet equipped with inclined balancing disks within the rotor of the high pressure compressor and process for producing such disks |
| US6260349B1 (en) | 2000-03-17 | 2001-07-17 | Kenneth F. Griffiths | Multi-stage turbo-machines with specific blade dimension ratios |
| US6378287B2 (en) | 2000-03-17 | 2002-04-30 | Kenneth F. Griffiths | Multi-stage turbomachine and design method |
| US20030133803A1 (en) * | 2002-01-17 | 2003-07-17 | Snecma Moteurs | Turbomachine rotor arrangement |
| US20140069101A1 (en) * | 2012-09-13 | 2014-03-13 | General Electric Company | Compressor fairing segment |
| US20150292401A1 (en) * | 2012-12-31 | 2015-10-15 | Rolls-Royce Corporation | Systems, Methods and Apparatuses for Interconnection of Rotating Components |
| US11286779B2 (en) | 2020-06-03 | 2022-03-29 | Honeywell International Inc. | Characteristic distribution for rotor blade of booster rotor |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1072351B (en) * | 1955-12-23 | |||
| US3451653A (en) * | 1967-03-22 | 1969-06-24 | Gen Electric | Turbomachinery rotors |
| US11519363B2 (en) * | 2020-03-26 | 2022-12-06 | Rolls-Royce Plc | High pressure ratio gas turbine engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US770207A (en) * | 1904-07-12 | 1904-09-13 | Wilkinson Steam Turbine Company | Elastic-fluid turbine-wheel. |
| US1030153A (en) * | 1911-07-10 | 1912-06-18 | Alfred Barbezat | Device to balance thrust in turbines. |
| US2213940A (en) * | 1937-07-07 | 1940-09-03 | Jendrassik George | Rotor for gas turbines and rotary compressors |
| GB543985A (en) * | 1939-09-25 | 1942-03-23 | Sulzer Ag | Improvements in or relating to rotors for turbines |
| CH223615A (en) * | 1939-11-21 | 1942-09-30 | Sulzer Ag | Turbine, especially for high temperature propellants. |
| US2445661A (en) * | 1941-09-22 | 1948-07-20 | Vickers Electrical Co Ltd | Axial flow turbine, compressor and the like |
| US2579745A (en) * | 1947-02-17 | 1951-12-25 | Rolls Royce | Axial-flow compressor or turbine |
| US2662685A (en) * | 1949-07-13 | 1953-12-15 | Materiels Hispano Suiza S A So | Rotor for fluid machines |
-
1951
- 1951-04-18 GB GB9110/51A patent/GB706563A/en not_active Expired
-
1952
- 1952-04-12 US US281958A patent/US2869820A/en not_active Expired - Lifetime
- 1952-04-16 FR FR1057171D patent/FR1057171A/en not_active Expired
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US770207A (en) * | 1904-07-12 | 1904-09-13 | Wilkinson Steam Turbine Company | Elastic-fluid turbine-wheel. |
| US1030153A (en) * | 1911-07-10 | 1912-06-18 | Alfred Barbezat | Device to balance thrust in turbines. |
| US2213940A (en) * | 1937-07-07 | 1940-09-03 | Jendrassik George | Rotor for gas turbines and rotary compressors |
| GB543985A (en) * | 1939-09-25 | 1942-03-23 | Sulzer Ag | Improvements in or relating to rotors for turbines |
| CH223615A (en) * | 1939-11-21 | 1942-09-30 | Sulzer Ag | Turbine, especially for high temperature propellants. |
| US2445661A (en) * | 1941-09-22 | 1948-07-20 | Vickers Electrical Co Ltd | Axial flow turbine, compressor and the like |
| US2579745A (en) * | 1947-02-17 | 1951-12-25 | Rolls Royce | Axial-flow compressor or turbine |
| US2662685A (en) * | 1949-07-13 | 1953-12-15 | Materiels Hispano Suiza S A So | Rotor for fluid machines |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2951677A (en) * | 1956-03-12 | 1960-09-06 | Curtiss Wright Corp | Turbine rotor construction |
| US3056579A (en) * | 1959-04-13 | 1962-10-02 | Gen Electric | Rotor construction |
| US3038652A (en) * | 1959-10-21 | 1962-06-12 | United Aircraft Corp | Intermediate compressor case |
| US3083947A (en) * | 1960-03-03 | 1963-04-02 | United Aircraft Corp | Compressor spacer |
| US3597109A (en) * | 1968-05-31 | 1971-08-03 | Rolls Royce | Gas turbine engine axial flow multistage compressor |
| US3976399A (en) * | 1970-07-09 | 1976-08-24 | Kraftwerk Union Aktiengesellschaft | Rotor of disc construction for single-shaft gas turbine |
| FR2456835A1 (en) * | 1979-05-17 | 1980-12-12 | United Technologies Corp | ROTOR ASSEMBLY HAVING MULTI-STAGE DISC |
| FR2481379A1 (en) * | 1980-04-28 | 1981-10-30 | United Technologies Corp | COMPRESSION SECTION FOR A ROTARY FLOW AXIAL MACHINE |
| US4371311A (en) * | 1980-04-28 | 1983-02-01 | United Technologies Corporation | Compression section for an axial flow rotary machine |
| US4460309A (en) * | 1980-04-28 | 1984-07-17 | United Technologies Corporation | Compression section for an axial flow rotary machine |
| US4737076A (en) * | 1986-10-20 | 1988-04-12 | United Technologies Corporation | Means for maintaining concentricity of rotating components |
| US5397215A (en) * | 1993-06-14 | 1995-03-14 | United Technologies Corporation | Flow directing assembly for the compression section of a rotary machine |
| US5579644A (en) * | 1993-10-13 | 1996-12-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbo-jet equipped with inclined balancing disks within the rotor of the high pressure compressor and process for producing such disks |
| US6260349B1 (en) | 2000-03-17 | 2001-07-17 | Kenneth F. Griffiths | Multi-stage turbo-machines with specific blade dimension ratios |
| US6378287B2 (en) | 2000-03-17 | 2002-04-30 | Kenneth F. Griffiths | Multi-stage turbomachine and design method |
| US20030133803A1 (en) * | 2002-01-17 | 2003-07-17 | Snecma Moteurs | Turbomachine rotor arrangement |
| US7008190B2 (en) * | 2002-01-17 | 2006-03-07 | Snecma Moteurs | Turbomachine rotor arrangement |
| US20140069101A1 (en) * | 2012-09-13 | 2014-03-13 | General Electric Company | Compressor fairing segment |
| US9528376B2 (en) * | 2012-09-13 | 2016-12-27 | General Electric Company | Compressor fairing segment |
| US20150292401A1 (en) * | 2012-12-31 | 2015-10-15 | Rolls-Royce Corporation | Systems, Methods and Apparatuses for Interconnection of Rotating Components |
| US10060347B2 (en) * | 2012-12-31 | 2018-08-28 | Rolls-Royce Corporation | Systems, methods and apparatuses for interconnection of rotating components |
| US11286779B2 (en) | 2020-06-03 | 2022-03-29 | Honeywell International Inc. | Characteristic distribution for rotor blade of booster rotor |
Also Published As
| Publication number | Publication date |
|---|---|
| GB706563A (en) | 1954-03-31 |
| FR1057171A (en) | 1954-03-05 |
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