US2431249A - Securing projections to rotors - Google Patents
Securing projections to rotors Download PDFInfo
- Publication number
- US2431249A US2431249A US544436A US54443644A US2431249A US 2431249 A US2431249 A US 2431249A US 544436 A US544436 A US 544436A US 54443644 A US54443644 A US 54443644A US 2431249 A US2431249 A US 2431249A
- Authority
- US
- United States
- Prior art keywords
- rotor
- roots
- groove
- blade
- spiral
- 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
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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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
Definitions
- This invention relates to drums, wheels or other rotors such as carry a ring of projections, for example, blades, arms, buckets, cutters or the like, and, although not limited in this respect, the invention is particularly applicable to a turbine and especially to an internal-combustion turbine plant for jet-propulsion purposes.
- U. S. patent specification No. 2,240,742 in the name of Allen discloses a turbine rotor having a peripheral groove in which is secureda ring of turbine blades, the groove having, on one radial face at least, a spiral screw-thread struck about the axis of the rotor, and the roots of the blades have corresponding spirally-formed teeth such that the blades can be" screwed into the groove until they bottom on the groove, thus to be located radially and circumferentially.
- the groove may be in the roots of the blades.
- a method of securing projections against one another round the periphery of a rotor involves providing a screwthread on one face at least of a peripheral groove provided either in the rotor or in the roots of the projections (when properly assembled), such screw-thread being in the form of a spiral struck about the axis of the rotor, providing a corresponding screw-thread either on the roots of the projections (when properly assembled) or on a peripheral flange of the rotor, as the case may be, the roots being adapted to be received in the groove of the rotor or the flange being adapted to be received in the groove of the roots, as the case may be, and screwing the roots to the rotor with the projections circumferentially spaced from one another until they abut one another with a relatively-large pressure in a circumferential direction, whereby they are positioned in a radial direction solely by the interaction of the two spiral threads, being positioned circumferentially by friction resulting from
- the final screwing of the roots to pressure will the rotor iseffected while the grooved element (i. e., the rotor or the roots, as the case may be) is at a materially highertemperature than the coacting element (1. e., the roots or the rotor, as the case may be) so that the circumferential pressure will be reached when the parts are at substantially the same temperature.
- the grooved element i. e., the rotor or the roots, as the case may be
- the coacting element (1. e., the roots or the rotor, as the case may be
- the coacting spiral threads have axial clearance from one another, axial location being elsewhere provided.
- the terms axial clearance and "axial location are applied to the blade roots with respect to the axis of the rotor.
- the relatively-large circumferential pressure may be of the order of from 5 to 10 tons per square inch, and higher for an internal-combustion turbine, for example, up to 20 tons per square inch.
- the circumferential 11 to something like half its value at very high speeds, due to deformation of the rotor under the centrifugal forces.
- location is effected by the tensional and compressive deformations of the two spiral threads, respectively-i. e., by an elastic deformation which is large compared with the irregularities of the machined teeth of the blade roots, whereas in the U. S. specification aforesaid, or in other constructions where the blade roots are let into individual shaped recesses in the rotor, the elastic deformation of the locating surfaces is small compared with the irregularities of the machined root surfaces.
- Figure 1 is a fragmentary section, taken in a plane in which the axis of the rotor lies, of a turbine blade secured to the rotor according to the invention
- Figure 2 is a similar but smaller fragmentary view, and to a larger scale
- Figure 3 is a fragmentary view in cross-section through the rotor, with the blades removed;
- Figure 4 is a fragmentary elevational and partcross-sectional View showing one blade in elevation and the next in section;
- Figure 5 is a view, similar to Figure 1, showing a blade having a root of slightly different form
- Figure 6 is a view, also similar to Figure '1, showing an inverse method of securing a blade to a rotor
- Figure 7 which is an axial elevation of a complete turbine disc but with only some of the blades fully shown, is a diagram showing the stresses.
- the rotor 12 has a peripheral groove l3 with parallel radial faces in which fine-pitch, spiral screw-threads I 4 are cut, and opposite faces of the root I5 of a blade l6 have corresponding spiral teeth I'Iv cut therein.
- the blades In machining the teeth of the roots, the blades should be assembled in a ring, the blades extending radially with their roots abutting one another, and the spiral screw-thread machined whilst they are in this position. Care should be taken to number or otherwise mark each blade as the spiral teeth on different blades will be different, and it is only by arranging the roots in the correct order that they can subsequently be correctly screwed into the groove l3 of the rotor.
- the screw-threads have axial clearance, and I provide axial location (with respect to the rotor) in the construction of Figures 1 to 4 solely at the places marked I8, l8, 1. e., internally of the flange of the blade root.
- Figure 5 differs from that of Figures 1 to 4 mainly in that axial location is provided at l9, H! at the outer end of the rotor groove.
- a locating dowel 20 ( Figure 1) may be inserted as a safety precaution after assembly, but in our opinion it will not be required.
- the grooved element i. e., the rotor in this case, may be heated to a predetermined temperature, for example, 70 C. or 100 C., when the blade roots are to be screwed into it; and if the latter be screwed up tightly (i.
- Figures 3 and 4 show a multi-start spiral.
- the spiral is intended to be a singlestart one.
- a method of securing a built-up ring element to a rotor element, said ring element comprising a number of radially extending projections to be mounted against one another with their roots abutting one another in a circumferential direction which involves providing a groove in one of said elements and a flange on the other element to be received in said groove with the groove so relatively deep that its bottom will not be reached by the inner end of the root when the root is in the home position in the groove, providing at least one of the faces of said flange and the adjacent face of the wall of said groove with corresponding spiral screw-threads struck about the axis of the rotor, screwing the roots to the rotor, with the projections circumferentially spaced from one another, until they abut one another with a relatively-large pressure in a circumferential direction, and with the inner ends of the roots spaced from the bottom of the groove to provide radial clearance between said elements except for the engagement of saidspiral screwthreads whereby said projections are
Description
Nov. 18, 1947;
A Home Nov. 18, 1947. F, A, M. HEPPNER 2,431,249
SECURING PROJECTIONS TO ROTORS Filed July 11, 1944 2 Sheets-Sheet 2 RADlALLY/ frwenZZr Patented Nov. 18, 1947 SECURING PROJECTIONS TO RQTORS Fritz Albert Max Heppner, Leamington Spa,
assignor to Armstrong Siddeley Motors land,
Eng-
Limited, Coventry, England Application July 11, 1944, Serial No. 544,436 In Great Britain April 18, 1944 1 Claim. (Cl. 29-1563) This invention relates to drums, wheels or other rotors such as carry a ring of projections, for example, blades, arms, buckets, cutters or the like, and, although not limited in this respect, the invention is particularly applicable to a turbine and especially to an internal-combustion turbine plant for jet-propulsion purposes.
U. S. patent specification No. 2,240,742 in the name of Allen, discloses a turbine rotor having a peripheral groove in which is secureda ring of turbine blades, the groove having, on one radial face at least, a spiral screw-thread struck about the axis of the rotor, and the roots of the blades have corresponding spirally-formed teeth such that the blades can be" screwed into the groove until they bottom on the groove, thus to be located radially and circumferentially. Alternatively, the groove may be in the roots of the blades.
I have found, in practice, that it is an extremely difficult production operation to arrange for the respective spiral screw-threads to be accurate as well as the radially-inner ends of the blade roots relatively to the bottom of the groove, so much so that the proposed method of assembly is in my opinion without utility, or impracticable. It is the main object of the present invention to obviate this defect whilst using the spiral screwthread idea, which has undoubted advantages.
According to the invention, a method of securing projections against one another round the periphery of a rotor involves providing a screwthread on one face at least of a peripheral groove provided either in the rotor or in the roots of the projections (when properly assembled), such screw-thread being in the form of a spiral struck about the axis of the rotor, providing a corresponding screw-thread either on the roots of the projections (when properly assembled) or on a peripheral flange of the rotor, as the case may be, the roots being adapted to be received in the groove of the rotor or the flange being adapted to be received in the groove of the roots, as the case may be, and screwing the roots to the rotor with the projections circumferentially spaced from one another until they abut one another with a relatively-large pressure in a circumferential direction, whereby they are positioned in a radial direction solely by the interaction of the two spiral threads, being positioned circumferentially by friction resulting from the deformation of the coacting threads when the roots engage one another with the relatively-large circumferential pressure.
Preferably, the final screwing of the roots to pressure will the rotor iseffected while the grooved element (i. e., the rotor or the roots, as the case may be) is at a materially highertemperature than the coacting element (1. e., the roots or the rotor, as the case may be) so that the circumferential pressure will be reached when the parts are at substantially the same temperature.
Preferably, too, the coacting spiral threads have axial clearance from one another, axial location being elsewhere provided. The terms axial clearance and "axial location are applied to the blade roots with respect to the axis of the rotor.
For a steam turbine the relatively-large circumferential pressure may be of the order of from 5 to 10 tons per square inch, and higher for an internal-combustion turbine, for example, up to 20 tons per square inch. The circumferential 11 to something like half its value at very high speeds, due to deformation of the rotor under the centrifugal forces.
Thus, with the invention, location is effected by the tensional and compressive deformations of the two spiral threads, respectively-i. e., by an elastic deformation which is large compared with the irregularities of the machined teeth of the blade roots, whereas in the U. S. specification aforesaid, or in other constructions where the blade roots are let into individual shaped recesses in the rotor, the elastic deformation of the locating surfaces is small compared with the irregularities of the machined root surfaces.
In the accompanying drawings:
Figure 1 is a fragmentary section, taken in a plane in which the axis of the rotor lies, of a turbine blade secured to the rotor according to the invention;
Figure 2 is a similar but smaller fragmentary view, and to a larger scale;
Figure 3 is a fragmentary view in cross-section through the rotor, with the blades removed;
Figure 4 is a fragmentary elevational and partcross-sectional View showing one blade in elevation and the next in section;
Figure 5 is a view, similar to Figure 1, showing a blade having a root of slightly different form;
Figure 6 is a view, also similar to Figure '1, showing an inverse method of securing a blade to a rotor; and
Figure 7, which is an axial elevation of a complete turbine disc but with only some of the blades fully shown, is a diagram showing the stresses.
In the construction of Figures 1 to 4, and also in that of Figure 5, the rotor 12 has a peripheral groove l3 with parallel radial faces in which fine-pitch, spiral screw-threads I 4 are cut, and opposite faces of the root I5 of a blade l6 have corresponding spiral teeth I'Iv cut therein. In machining the teeth of the roots, the blades should be assembled in a ring, the blades extending radially with their roots abutting one another, and the spiral screw-thread machined whilst they are in this position. Care should be taken to number or otherwise mark each blade as the spiral teeth on different blades will be different, and it is only by arranging the roots in the correct order that they can subsequently be correctly screwed into the groove l3 of the rotor.
As shown by Figure 2, the screw-threads have axial clearance, and I provide axial location (with respect to the rotor) in the construction of Figures 1 to 4 solely at the places marked I8, l8, 1. e., internally of the flange of the blade root.
' The construction of Figure 5 differs from that of Figures 1 to 4 mainly in that axial location is provided at l9, H! at the outer end of the rotor groove. A locating dowel 20 (Figure 1) may be inserted as a safety precaution after assembly, but in our opinion it will not be required.
It will be seen from Figures 1 to 5 that the only radial engagement effected between the blade roots and the rotor is through the interacting spiral screw-thread. As stated, the grooved element, i. e., the rotor in this case, may be heated to a predetermined temperature, for example, 70 C. or 100 C., when the blade roots are to be screwed into it; and if the latter be screwed up tightly (i. e., to abut one another), when the parts have again reached the same temperature the radial contraction of the spiral screw-thread of the rotor acting on the spiral screw-thread of the roots of the blades will draw the latter radially inwardly to an extent in which each blade root bears on the adjacent blade roots with a predetermined circumferential pressure.
That is to say, the rotor will be placed in tension,
both circumferentially and radially and the ring of blade roots in compression circumferentially, as shown by Figure 7. Otherwise complicated machinery may be necessary to screw up the blade roots to a suflicient circumferential pressurei. e., if heat is not used. Initially heating the rotor to 200 C. will produce a circumferential pressure of about 20 tons per square inch when the parts are at the same temperature.
In this way the blade roots are radially located and it is impossible for them to work loose, assuming that they are never subsequently at temperatures materially lower than that of the rotor.
In the modification of Figure 6 it will be observ ed that the groove 22 is provided in the blade roots [5, the groove receiving the flange 23 of the rotor l2, and, as before, radial location is provided solely by the interaction of the two spiral screw- threads 25, 26.
Figures 3 and 4 show a multi-start spiral. In Figure 7 the spiral is intended to be a singlestart one.
What I claim as my invention and desire to secure by Letters Patent of the United States is:
A method of securing a built-up ring element to a rotor element, said ring element comprising a number of radially extending projections to be mounted against one another with their roots abutting one another in a circumferential direction, which involves providing a groove in one of said elements and a flange on the other element to be received in said groove with the groove so relatively deep that its bottom will not be reached by the inner end of the root when the root is in the home position in the groove, providing at least one of the faces of said flange and the adjacent face of the wall of said groove with corresponding spiral screw-threads struck about the axis of the rotor, screwing the roots to the rotor, with the projections circumferentially spaced from one another, until they abut one another with a relatively-large pressure in a circumferential direction, and with the inner ends of the roots spaced from the bottom of the groove to provide radial clearance between said elements except for the engagement of saidspiral screwthreads whereby said projections are positioned in a radial direction solely by interaction of the two spiral threads, the step of screwing the roots to the rotor being carried so far as to deform the coacting threads incident to the relatively great circumferential pressure of the roots upon one another.
FRITZ ALBERT MAX HEPPNER.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 1,318,091 Ljungstrom Oct. 7, 1919 1,366,605 Steenstrup Jan. 25, 1921 1,371,768 Sullivan Mar. 15, 1921 2,240,742 Allen May 6, 1941 2,240,743 Allen May 6, 1941 FOREIGN PATENTS Number Country Date 348,993 Great Britain May 21, 1931 703,602 France May 4, 1931
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB7142/44A GB572916A (en) | 1944-04-18 | 1944-04-18 | Securing projections to a rotor |
Publications (1)
Publication Number | Publication Date |
---|---|
US2431249A true US2431249A (en) | 1947-11-18 |
Family
ID=9827415
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US544436A Expired - Lifetime US2431249A (en) | 1944-04-18 | 1944-07-11 | Securing projections to rotors |
Country Status (2)
Country | Link |
---|---|
US (1) | US2431249A (en) |
GB (1) | GB572916A (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2769611A (en) * | 1951-08-15 | 1956-11-06 | Schwarzkopf Dev Co | Gas turbine rotors and their production |
US2773169A (en) * | 1951-02-26 | 1956-12-04 | Power Jets Res & Dev Ltd | Welding of bladed rotors for turbines, compressors, etc. |
US2798438A (en) * | 1953-05-11 | 1957-07-09 | Mack Trucks | Means for securing a pump impeller to a shaft |
US2830357A (en) * | 1955-05-27 | 1958-04-15 | Bristol Aero Engines Ltd | Blades for gas turbines |
US2857132A (en) * | 1952-02-19 | 1958-10-21 | Gen Motors Corp | Turbine wheel |
US2921769A (en) * | 1953-06-08 | 1960-01-19 | Peerless Turbine Corp | Turbine rotor |
US2953348A (en) * | 1952-12-30 | 1960-09-20 | Gen Motors Corp | Blade fastenings |
US3306577A (en) * | 1964-08-25 | 1967-02-28 | Sagara Hideo | Turbine device |
US3749514A (en) * | 1971-09-30 | 1973-07-31 | United Aircraft Corp | Blade attachment |
US4767275A (en) * | 1986-07-11 | 1988-08-30 | Westinghouse Electric Corp. | Locking pin system for turbine curved root side entry closing blades |
US4885829A (en) * | 1989-02-16 | 1989-12-12 | Fatigue Technology, Incorporated | Fatigue life enhancement of dovetail connector slots and noncircular openings |
US7841834B1 (en) * | 2006-01-27 | 2010-11-30 | Florida Turbine Technologies, Inc. | Method and leading edge replacement insert for repairing a turbine engine blade |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1036739A (en) * | 1965-04-02 | 1966-07-20 | Rolls Royce | Rotor and blade assemblies |
GB2265671A (en) * | 1992-03-24 | 1993-10-06 | Rolls Royce Plc | Bladed rotor for a gas turbine engine |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1318091A (en) * | 1919-10-07 | Hredrik ljtjngstrsm | ||
US1366605A (en) * | 1919-06-27 | 1921-01-25 | Gen Electric | Blade-securing means and method of making the same |
US1371768A (en) * | 1918-11-08 | 1921-03-15 | Bethlehem Shipbuilding Corp Lt | Method of setting turbine-blades |
FR703602A (en) * | 1929-10-18 | 1931-05-04 | Brown | Method for installing the fins on the rotor of steam or gas turbines |
US2240742A (en) * | 1937-11-26 | 1941-05-06 | Allis Chalmers Mfg Co | Turbine blade attachment and method and apparatus therefor |
US2240743A (en) * | 1937-11-26 | 1941-05-06 | Allis Chalmers Mfg Co | Apparatus for attaching turbine blades |
-
1944
- 1944-04-18 GB GB7142/44A patent/GB572916A/en not_active Expired
- 1944-07-11 US US544436A patent/US2431249A/en not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1318091A (en) * | 1919-10-07 | Hredrik ljtjngstrsm | ||
US1371768A (en) * | 1918-11-08 | 1921-03-15 | Bethlehem Shipbuilding Corp Lt | Method of setting turbine-blades |
US1366605A (en) * | 1919-06-27 | 1921-01-25 | Gen Electric | Blade-securing means and method of making the same |
FR703602A (en) * | 1929-10-18 | 1931-05-04 | Brown | Method for installing the fins on the rotor of steam or gas turbines |
GB348993A (en) * | 1929-10-18 | 1931-05-21 | Bbc Brown Boveri & Cie | Improvements in and relating to steam and gas turbines |
US2240742A (en) * | 1937-11-26 | 1941-05-06 | Allis Chalmers Mfg Co | Turbine blade attachment and method and apparatus therefor |
US2240743A (en) * | 1937-11-26 | 1941-05-06 | Allis Chalmers Mfg Co | Apparatus for attaching turbine blades |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2773169A (en) * | 1951-02-26 | 1956-12-04 | Power Jets Res & Dev Ltd | Welding of bladed rotors for turbines, compressors, etc. |
US2769611A (en) * | 1951-08-15 | 1956-11-06 | Schwarzkopf Dev Co | Gas turbine rotors and their production |
US2857132A (en) * | 1952-02-19 | 1958-10-21 | Gen Motors Corp | Turbine wheel |
US2953348A (en) * | 1952-12-30 | 1960-09-20 | Gen Motors Corp | Blade fastenings |
US2798438A (en) * | 1953-05-11 | 1957-07-09 | Mack Trucks | Means for securing a pump impeller to a shaft |
US2921769A (en) * | 1953-06-08 | 1960-01-19 | Peerless Turbine Corp | Turbine rotor |
US2830357A (en) * | 1955-05-27 | 1958-04-15 | Bristol Aero Engines Ltd | Blades for gas turbines |
US3306577A (en) * | 1964-08-25 | 1967-02-28 | Sagara Hideo | Turbine device |
US3749514A (en) * | 1971-09-30 | 1973-07-31 | United Aircraft Corp | Blade attachment |
US4767275A (en) * | 1986-07-11 | 1988-08-30 | Westinghouse Electric Corp. | Locking pin system for turbine curved root side entry closing blades |
US4885829A (en) * | 1989-02-16 | 1989-12-12 | Fatigue Technology, Incorporated | Fatigue life enhancement of dovetail connector slots and noncircular openings |
US7841834B1 (en) * | 2006-01-27 | 2010-11-30 | Florida Turbine Technologies, Inc. | Method and leading edge replacement insert for repairing a turbine engine blade |
Also Published As
Publication number | Publication date |
---|---|
GB572916A (en) | 1945-10-29 |
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