WO2014114883A1 - Assemblage de masselotte d'équilibrage a un élément de rotor - Google Patents
Assemblage de masselotte d'équilibrage a un élément de rotor Download PDFInfo
- Publication number
- WO2014114883A1 WO2014114883A1 PCT/FR2014/050125 FR2014050125W WO2014114883A1 WO 2014114883 A1 WO2014114883 A1 WO 2014114883A1 FR 2014050125 W FR2014050125 W FR 2014050125W WO 2014114883 A1 WO2014114883 A1 WO 2014114883A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- flange
- weight
- assembly
- balancing
- rotor
- Prior art date
Links
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
-
- 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
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/32—Correcting- or balancing-weights or equivalent means for balancing rotating bodies, e.g. vehicle wheels
- F16F15/34—Fastening arrangements therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/31—Retaining bolts or nuts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
Definitions
- the subject of the invention is an improved balancing feeder assembly with a rotor element.
- the balancing of the rotors is systematically necessary to guarantee their proper functioning and the service life of the machines to which they belong. In rotors composed of several assembled modules, balancing is done on each of the modules.
- FIG 8 which shows the assembly of two rotor elements 1 and 2 by assembly pins 3, established through adjacent flanges 4 and 5 of these modules 1 and 2.
- a counterweight 6 is attached to a tab 7 that also passes through the stud 3, and it hangs inside the rotor, projecting towards the axis of rotation. Such weights 6 may be distributed over the circumference of the rotor, only one being shown here.
- the invention represents a balancer weight fixing assembly improved under these criteria, and which allows in particular to place the flyweights with very high accuracy.
- a balancing feeder assembly to a rotor element, comprising a device for fixing the flyweight, which passes through the flyweight and a flange of the element, characterized in that it comprises a screw prefixing the feeder having a conical head, the prefixing screw extending through a hole in the flange and in the flyweight, the bore being provided with a conical countersink on a face opposite to the weight, the conical countersunk receiving the conical head.
- the conjunction of the conical head screw and conical countersink ensures a precise position of the screw relative to the flange, and therefore the weight attached to it.
- the pre-fixing takes place before the assembly of the rotor elements between them and can therefore be accomplished easily, even with small diameter elements, or which will have very little free space around the weight once they have been assembled.
- Final fixing of the weight can be obtained as in the previous design, by using assembly pins of the flange of the element to a flange of a neighboring rotor element; in this case, the studs can however be provided with clamping tabs of the weight.
- Flange sagging is possible in order to relieve it at the point where the pre-fixing screw and the bolt connection holes are drilled, avoiding the stress concentrations.
- FIGS. 1 and 2 are two general views of the assembly
- FIG. 3 illustrates, respectively, a balancing weight, a fixing pin and a prefixing screw
- the flyweight 8 of the invention is as previously fixed to a plane flange 9 of a rotor element 10; the flange 9 is attached to an adjacent flange 11 of a neighboring element 12 of the rotor by studs 13 assembly.
- the studs 13 are threaded rods with tightening nuts at both ends (only one is shown here).
- FIG. 2 shows that several weights 8 can be mounted side by side on the flange 9.
- the feeder 8 or each feeder 8 is here formed of a plate 14 held on the flange 9 and a flange 15, giving it a section bent and extending inside the flange 9, towards the flange 11 of the other element 12.
- the device comprises, for each weight 8, a prefixing screw 16 with a cylindrical rod and countersunk head which is a conical head 22.
- the prefixing screw 16 passes through the flange 9 through a bore 17 and the end of the rod extends into a tapping 18 passing through the plate 14 of the flyweight 8.
- the tightening of the pre-fixing screw 16 thus maintains the plate 14 on the flange 9.
- the bore 17 is provided with a conical countersink 19 in which the conical head 22, complementary shape, is housed, which places the rod of the screw and the weight 8 has a determined position, with great precision.
- the studs 13 pass through holes 20 established through the weight 8 and the two flanges 9 and 11 ( Figure 3).
- the studs 13 have a tab 21 to the mid-length.
- the lug 21 is supported on the flange 11 and allows to clamp the plate 14 securely against the flange 9 once the assembly of the elements 10 and 12 between them. It is supported on the flange 11 on one side opposite to the flyweight 8.
- the flange 9 comprises a housing 23 at the location of each pre-fixing screw 16, in which the piercing 17 opens, and which also receives the lug 21. This avoids any risk of contact between the heads 22 and the flange 11 and thus we guarantee an easy and correct assembly.
- Figures 6 and 7 illustrate that the flange 9 is provided with a scalloping 24, that is to say notches distributed around its circumference and which extend from its inner radius to the holes 17. Their effect is to decrease the amplitude and gradient of the stresses around the holes 17 and 25, so to relieve the flange 9 in general and extend its life.
- the holes 25 of the flange 9 which are intended for the passage of the studs 13 are also shown in these Figures 6 and 7.
- the design of the invention is compatible with any number of weights 8 and any number, and may be greater , bores 17 and radial scalloping notches 24 as a function of the drilling number 25.
- the bores 17 and scalloping notches 24 are here regularly distributed over the circumference of the flange 9 by alternating with the holes 25 of the studs 13.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Manufacture Of Motors, Generators (AREA)
- Connection Of Plates (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/762,065 US9909424B2 (en) | 2013-01-25 | 2014-01-23 | Assembly of a balance weight with a rotor element |
GB1512578.4A GB2523969B (en) | 2013-01-25 | 2014-01-23 | Assembly of a balance weight with a rotor element |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1350655A FR3001515B1 (fr) | 2013-01-25 | 2013-01-25 | Assemblage de masselotte d'equilibrage a un element de rotor |
FR1350655 | 2013-01-25 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014114883A1 true WO2014114883A1 (fr) | 2014-07-31 |
Family
ID=49713117
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2014/050125 WO2014114883A1 (fr) | 2013-01-25 | 2014-01-23 | Assemblage de masselotte d'équilibrage a un élément de rotor |
Country Status (4)
Country | Link |
---|---|
US (1) | US9909424B2 (fr) |
FR (1) | FR3001515B1 (fr) |
GB (1) | GB2523969B (fr) |
WO (1) | WO2014114883A1 (fr) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10465519B2 (en) * | 2013-10-17 | 2019-11-05 | Pratt & Whitney Canada Corp. | Fastening system for rotor hubs |
US10502059B2 (en) * | 2015-02-02 | 2019-12-10 | United Technologies Corporation | Alignment tie rod device and method of utilization |
DE102015219954A1 (de) * | 2015-10-14 | 2017-04-20 | Rolls-Royce Deutschland Ltd & Co Kg | Baugruppe für die drehfeste Verbindung mindestens zweier rotierender Bauteile in einer Gasturbine und Auswuchtverfahren |
US10823012B2 (en) * | 2016-05-20 | 2020-11-03 | Raytheon Technologies Corporation | Fastener openings for stress distribution |
FR3057017B1 (fr) * | 2016-09-30 | 2024-02-02 | Safran Aircraft Engines | Procede de dimensionnement de renfoncements dans la toile d'un organe de rotor |
US11053798B2 (en) * | 2018-11-07 | 2021-07-06 | Raytheon Technologies Corporation | Gas turbine engine having a trim balance |
FR3119647B1 (fr) * | 2021-02-11 | 2023-01-13 | Safran Aircraft Engines | Procédé de réparation d’une bride de rotor de turbomachine |
CN113969807B (zh) * | 2021-10-13 | 2024-07-05 | 中国航发沈阳发动机研究所 | 一种能在整机状态进行转子平衡的分油套结构 |
FR3145185A1 (fr) * | 2023-01-20 | 2024-07-26 | Safran Aircraft Engines | Dispositif d’arret en rotation pour rotor de turbomachine, rotor et turbomachine associes. |
US11976564B1 (en) | 2023-03-30 | 2024-05-07 | Rolls-Royce North American Technologies Inc. | Splined balance weight for rotating components in gas turbine engines |
US12018579B1 (en) | 2023-08-08 | 2024-06-25 | Rolls-Royce North American Technologies Inc. | Clocking balance weight rotor assembly for gas turbine engines |
US12018580B1 (en) | 2023-08-08 | 2024-06-25 | Rolls-Royce North American Technologies Inc. | Rotor assembly for gas turbine engines with replaceable balance weight pins |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2404212A1 (fr) * | 1977-09-23 | 1979-04-20 | Snecma | Dispositif d'equilibrage d'un rotor |
EP0691455A1 (fr) * | 1994-07-06 | 1996-01-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Joint métallique à levre et turbomachine équippé de ce joint |
EP1717481A1 (fr) * | 2005-04-29 | 2006-11-02 | Snecma | Dispositif d'équilibrage d'un rotor de turbomachine |
EP1918512A2 (fr) * | 2006-10-24 | 2008-05-07 | Snecma | Système d'équilibrage pour rotor de turbomachine |
DE102009042831A1 (de) * | 2008-10-27 | 2010-04-29 | Luk Lamellen Und Kupplungsbau Beteiligungs Kg | Antriebsstrang mit Fliehkraftpendel |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4480958A (en) * | 1983-02-09 | 1984-11-06 | The United States Of America As Represented By The Secretary Of The Air Force | High pressure turbine rotor two-piece blade retainer |
US6893222B2 (en) * | 2003-02-10 | 2005-05-17 | United Technologies Corporation | Turbine balancing |
FR2869374B1 (fr) * | 2004-04-23 | 2009-01-30 | Snecma Moteurs Sa | Systeme de fixation de pieces par des goujons a collerettes |
FR2885167B1 (fr) * | 2005-04-29 | 2007-06-29 | Snecma Moteurs Sa | Module de turbine pour moteur a turbine a gaz |
FR2907497B1 (fr) * | 2006-10-24 | 2009-01-23 | Snecma Sa | Systeme d'equilibrage pour rotor de turbomachine |
US8506253B2 (en) * | 2009-08-19 | 2013-08-13 | Pratt & Whitney Canada Corp. | Balancing apparatus for rotor assembly |
US8888458B2 (en) * | 2012-03-12 | 2014-11-18 | United Technologies Corporation | Turbomachine rotor balancing system |
-
2013
- 2013-01-25 FR FR1350655A patent/FR3001515B1/fr active Active
-
2014
- 2014-01-23 US US14/762,065 patent/US9909424B2/en active Active
- 2014-01-23 WO PCT/FR2014/050125 patent/WO2014114883A1/fr active Application Filing
- 2014-01-23 GB GB1512578.4A patent/GB2523969B/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2404212A1 (fr) * | 1977-09-23 | 1979-04-20 | Snecma | Dispositif d'equilibrage d'un rotor |
EP0691455A1 (fr) * | 1994-07-06 | 1996-01-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Joint métallique à levre et turbomachine équippé de ce joint |
EP1717481A1 (fr) * | 2005-04-29 | 2006-11-02 | Snecma | Dispositif d'équilibrage d'un rotor de turbomachine |
EP1918512A2 (fr) * | 2006-10-24 | 2008-05-07 | Snecma | Système d'équilibrage pour rotor de turbomachine |
DE102009042831A1 (de) * | 2008-10-27 | 2010-04-29 | Luk Lamellen Und Kupplungsbau Beteiligungs Kg | Antriebsstrang mit Fliehkraftpendel |
Also Published As
Publication number | Publication date |
---|---|
GB201512578D0 (en) | 2015-08-26 |
GB2523969A (en) | 2015-09-09 |
FR3001515A1 (fr) | 2014-08-01 |
US20150322794A1 (en) | 2015-11-12 |
US9909424B2 (en) | 2018-03-06 |
GB2523969B (en) | 2019-07-03 |
FR3001515B1 (fr) | 2015-03-20 |
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