WO2015104488A1 - Procede d'identification de la configuration d'equilibrage installee sur un rotor de turbomachine - Google Patents
Procede d'identification de la configuration d'equilibrage installee sur un rotor de turbomachine Download PDFInfo
- Publication number
- WO2015104488A1 WO2015104488A1 PCT/FR2015/050007 FR2015050007W WO2015104488A1 WO 2015104488 A1 WO2015104488 A1 WO 2015104488A1 FR 2015050007 W FR2015050007 W FR 2015050007W WO 2015104488 A1 WO2015104488 A1 WO 2015104488A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rotor
- screw
- mass
- screws
- angular position
- 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
- 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
- F05D2230/72—Maintenance
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
-
- 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
- F05D2270/00—Control
- F05D2270/80—Devices generating input signals, e.g. transducers, sensors, cameras or strain gauges
- F05D2270/804—Optical devices
- F05D2270/8041—Cameras
Definitions
- the present invention relates to the general field of the balancing of a turbomachine rotor, and in particular of an airplane turbojet fan.
- a turbojet engine comprises a fan supplying air with a primary flow channel in which a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine are positioned in particular. pressure.
- the turbojet At its upstream end, the turbojet comprises an air inlet for supplying the fan.
- This includes in particular a disk on which are mounted blades circumferentially spaced apart from each other.
- An inlet cone fixed on the disk of the fan makes it possible to deflect the air admitted into the turbojet engine towards the blades of the fan.
- clips are mounted on the free ends of the blades of the last stage of this turbine.
- the number and position of these clips define a balancing configuration of the low pressure turbine that is installed on it.
- each balancing weight screw has a screw head having a particular visual characteristic associated with its mass (for example a color or a particular shape) that is directly detectable to the naked eye (screw heads are mismatched).
- a particular visual characteristic associated with its mass for example a color or a particular shape
- the identification of the balancing masses which are mounted on the rotor, for example the turbomachine fan is obtained by simply visualizing the heads of the engine. screw and comparison of the characteristics of these with a pre-established table.
- the present invention therefore has the main purpose of providing a method of identifying the balancing configuration installed on a turbomachine rotor which does not have the aforementioned drawbacks.
- this object is achieved by means of a method of identifying the balancing configuration installed on a turbomachine rotor by means of a plurality of screws forming balancing masses which are mounted on the rotor at different angular positions thereof, the screws each having a predetermined mass and being each associated with an identification element of their mass and their angular position on the rotor, the method comprising the non-contact scanning of all the screws mounted on the rotor by an identification device for recognizing the identification elements of the mass and the angular position associated with each screw.
- the method according to the invention is remarkable in that the identification of the identification elements of the mass and of the angular position on the rotor of the balancing masses is done through the intermediary of, not of a human, but of an identification device working without contact. As a result, human error is no longer possible when reading the balancing configuration.
- this identification method can be automated, which allows to completely get rid of an operator and gives the possibility of systematic identification of the balancing configuration of the rotor.
- the scanning of all the screws mounted on the rotor is performed by a digital camera associated with image processing software.
- each screw is mounted in a hole of the rotor which has a visual element for identifying its angular position on the rotor and each screw comprises a screw head having a visual characteristic previously associated with its mass.
- the visual element for identifying the angular position on the rotor of the screws may be a visual mark, in particular a number, affixed at each hole of the rotor and previously associated with a determined angular position on the rotor and the visual characteristics of the Screw heads may consist of particular shapes and / or colors.
- the scanning of all the screws mounted on the rotor is performed by a radiofrequency reader of radio tags associated with a data processing software.
- each screw is mounted in a hole of the rotor by means of a nut, each screw comprising a radio-tag having an electronic chip which contains an identification element of the mass of the screw, and each nut having a radio tag having an electronic chip which contains an identification element of the angular position of the screw on the rotor.
- the method may comprise a preliminary step of establishing a table in which each identification element of the mass and the angular position of the screws is listed.
- the method may further include storing and automatically transmitting the identified balancing configuration to an avionics system.
- FIGS. 1 to 3 are schematic views of a turbojet fan having a balancing configuration to which the identification method according to the invention applies;
- FIG. 4 shows an example of identification elements of the mass and of the angular position on the fan of the balancing masses of FIGS. 1 to 3;
- FIG. 5 is a schematic view of a turbojet fan with an alternative embodiment of the invention.
- the invention applies to any turbomachine rotor, and in particular to a turbojet engine fan such as that shown very schematically in FIGS. 1 to 3.
- the fan 10 of a turbojet engine comprises in particular a disk 12 centered on an axis of rotation 14 and on which are mounted blades 16 spaced circumferentially from each other.
- An air intake cone 18 is fixed on the disc 12 upstream thereof to deflect the air admitted into the turbojet engine to the blades 16 of the fan.
- the fan 10 also comprises a plurality of holes 20 1 to 20 N (for example 36 in number) which are regularly spaced around its axis of rotation 14. These holes 20i to 20N are for example formed at the outer periphery of the cone of air inlet 18. They could alternatively be practiced directly in the disc 12 of the blower.
- these holes 20i to 20N extend in a radial direction and each have a cross section of circular shape and the same diameter.
- At least some of the holes 20 1 to 20 N are intended to receive screws 22 forming balancing masses. These screws have the same diameter but different lengths, which allows to obtain a lot of screws having different masses.
- the number, the angular position around the axis of rotation 14 of the fan and the mass of the screws 22 mounted on the air intake cone of the fan define a balancing configuration of the fan which is installed on the in order to reduce the vibrations of the low-pressure body of the turbojet engine during its operation.
- Such a balancing configuration of the blower is specific to each engine and is developed during delivery of the engine.
- the way this configuration is developed and then translated in terms of angular positioning of the balancing masses on the blower is well known to those skilled in the art and will not be detailed here.
- each screw 22 forming a balancing mass is associated with an identification element of its mass.
- this mass identification element is the screw head 22a which has a particular visual characteristic which is previously associated with its mass.
- visual characteristic here means a characteristic of shape and / or color to distinguish the screws between them to the naked eye.
- the screw heads 22a can thus have a square shape, a circle, a hexagon, etc. or be provided with features.
- the screw heads 22a may be painted red, yellow, green, etc.
- a correspondence table is established in which is identified each screw that can be used as balancing mass in the blower by listing each form and / or color of screw head associated with the mass of the corresponding screw.
- This correspondence table is stored in a memory of a work computer 24 (FIG. 3).
- each hole 20i at 20 N is associated an identification element of its angular position on the air intake cone 18 of the fan.
- this element for identifying the angular position of the holes is a visual mark, in particular a number, affixed to each hole 20i-20 N and previously associated with a predetermined angular position on the air intake cone of the blower.
- the number 1 will be affixed at the hole 20i
- the number 2 will be affixed to the hole 20 2 directly adjacent the hole 20i clockwise, etc.
- other visual marks could be affixed to visually identify the angular position of the various holes of the air inlet cone of the blower in which the balancing mass screws are mounted.
- Another correspondence table is established in which is identified each visual identification mark of the angular position of the holes of the air inlet cone of the blower, as well as the corresponding angular position of the holes on the inlet cone of the air intake cone. 'air.
- This correspondence table is also stored in a memory of the working computer 24.
- the method of identifying the balancing configuration thus installed on the fan comprises the non-contact scanning of all the screws 22 mounted on the inlet cone 18 of the fan 10 by a device identification for recognizing the identification elements of the mass and the angular position associated with each screw.
- This method is automatic, in that it does not require the intervention of an operator to make the correspondence between the various screws mounted on the inlet cone of the fan and their angular position thereon.
- the identification apparatus is a digital camera 26 which is associated with on-board image processing software in the working computer 24.
- This camera 26 sweeps (automatically or with the aid of an operator) the set of holes 20i to 20N of the air inlet cone of the blower in which the screws 22 forming balancing mass are mounted (the camera makes a complete turn of the cone of air inlet).
- the images of the holes recorded during this complete scanning of the air inlet cone are transmitted to the working computer 24 by any suitable transfer means for processing.
- the image processing software of the working computer processes these images by automatically recognizing the numbers 1 to 36 affixed to each hole 20i to 36 of the air inlet cone of the blower, as well as the different shapes of the screw heads 22a. Using the correspondence tables stored in its memory, the work computer can then automatically identify the balancing configuration installed on the fan.
- the acquisition, transmission and processing of images can be done automatically without the intervention of an operator.
- FIG. 5 represents an alternative embodiment of the method for identifying the balancing configuration installed on the fan according to the invention.
- each screw 22 forming balancing mass comprises a radio-tag 28 having an electronic chip which contains a data identification of the mass of the screw.
- the screws 22 forming balancing mass are mounted in one of the holes 20i 20 N of the air intake cone 18 of the fan through a nut 30, these nuts each having a radio- label 32 having an electronic chip which contains an identification data of the angular position of the corresponding screw on the air intake cone.
- the method comprises the non-contact sweeping of all the screws 22 mounted on the air inlet cone of the blower via a radiofrequency reader of radio-labels 34 (FIG. also called RFID reader for "Radio Frequency Identification”) which is associated with a data processing software embedded in the working computer 24.
- a radiofrequency reader of radio-labels 34 (FIG. also called RFID reader for "Radio Frequency Identification”
- RFID reader for "Radio Frequency Identification”
- This radio frequency reader 34 sweeps (automatically or using an operator) all the holes 20i to 20 N of the air intake cone of the blower in which are mounted the screws 22 forming a mass of balancing.
- the radio frequency reader 34 records and transmits to the working computer the data relating to the mass of the screws and to the angular position of the corresponding holes which are stored in the electronic chips of the radio tags associated with each screw and at each hole of the air intake cone of the blower.
- the data processing software can then automatically identify the balancing configuration installed on the blower.
- the identification system of the balancing configuration installed on the fan is shipped on board the aircraft to communicate to the avionics system that manages the balancing state of the fan. In this way, such a system knows automatically and permanently the balancing state of the engine blower without the need for an operator to inform it.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Testing Of Balance (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1612315.0A GB2536592B (en) | 2014-01-13 | 2015-01-05 | Method for identifying the balancing configuration installed on a turbomachine rotor |
US15/111,414 US10598017B2 (en) | 2014-01-13 | 2015-01-05 | Method of identifying the balancing configuration installed on a turbine engine rotor |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1450250A FR3016392B1 (fr) | 2014-01-13 | 2014-01-13 | Procede d'identification de la configuration d'equilibrage installee sur un rotor de turbomachine |
FR1450250 | 2014-01-13 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015104488A1 true WO2015104488A1 (fr) | 2015-07-16 |
Family
ID=50483122
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2015/050007 WO2015104488A1 (fr) | 2014-01-13 | 2015-01-05 | Procede d'identification de la configuration d'equilibrage installee sur un rotor de turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US10598017B2 (fr) |
FR (1) | FR3016392B1 (fr) |
GB (1) | GB2536592B (fr) |
WO (1) | WO2015104488A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11732585B2 (en) | 2021-01-28 | 2023-08-22 | General Electric Company | Trapped rotatable weights to improve rotor balance |
US20230349297A1 (en) * | 2022-04-29 | 2023-11-02 | Pratt & Whitney Canada Corp. | Method of manufacturing a mistuned rotor |
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 (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1261830A (fr) | 1960-07-07 | 1961-05-19 | Wilfley & Sons Inc A | Procédé de centrage de l'enveloppe des pompes centrifuges |
US20070110543A1 (en) * | 2005-11-12 | 2007-05-17 | Christopher Milton Fitch | Tail-driven screw fastener for use in tamper-resistant and decorative applications |
FR2939470A1 (fr) * | 2008-12-10 | 2010-06-11 | Snecma | Soufflante pour turbomachine comprenant un systeme d'equilibrage a trous borgnes de logement de masses |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7303377B2 (en) * | 2004-04-14 | 2007-12-04 | Pratt & Whitney Canada Corp. | Apparatus and method of balancing a shaft |
US7957851B2 (en) * | 2005-05-09 | 2011-06-07 | American Airlines, Inc. | System and method for utilization of transmitted digital flight data acquisition information to accomplish vibration balance solutions |
GB0514149D0 (en) * | 2005-07-09 | 2005-08-17 | Rolls Royce Plc | In-situ component monitoring |
US7412898B1 (en) * | 2006-07-28 | 2008-08-19 | Disney Enterprises, Inc. | Load sensing system including RFID tagged fasteners |
FR2920187B1 (fr) * | 2007-08-24 | 2014-07-04 | Snecma | Soufflante pour turbomachine d'aeronef comprenant une bride d'equilibrage masqueee par le cone d'entree. |
US8434216B2 (en) * | 2008-01-08 | 2013-05-07 | General Electric Company | Methods and systems for in-situ machine maintenance |
US8322991B2 (en) * | 2009-04-10 | 2012-12-04 | Rolls-Royce Corporation | Balance weight |
GB0908502D0 (en) * | 2009-05-19 | 2009-06-24 | Rolls Royce Plc | A balanced rotor for a turbine engine |
FR2977029B1 (fr) * | 2011-06-22 | 2013-07-12 | Airbus Operations Sas | Procede d'equilibrage pour systeme propulsif a helices contrarotatives non carenees |
GB201210870D0 (en) * | 2012-06-20 | 2012-08-01 | Rolls Royce Plc | Rotor balancing method |
FR2999227B1 (fr) * | 2012-12-10 | 2015-02-06 | Snecma | Procede d'equilibrage d'un rotor de turbomachine et rotor equilibre par un tel procede |
FR3001291B1 (fr) * | 2013-01-18 | 2015-02-27 | Snecma | Dispositif d'equilibrage moteur pour capot d'entree de turbomachine |
US9016560B2 (en) * | 2013-04-15 | 2015-04-28 | General Electric Company | Component identification system |
US10030534B2 (en) * | 2016-02-24 | 2018-07-24 | General Electric Company | Detectable datum markers for gas turbine engine components for measuring distortion |
-
2014
- 2014-01-13 FR FR1450250A patent/FR3016392B1/fr active Active
-
2015
- 2015-01-05 GB GB1612315.0A patent/GB2536592B/en active Active
- 2015-01-05 WO PCT/FR2015/050007 patent/WO2015104488A1/fr active Application Filing
- 2015-01-05 US US15/111,414 patent/US10598017B2/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1261830A (fr) | 1960-07-07 | 1961-05-19 | Wilfley & Sons Inc A | Procédé de centrage de l'enveloppe des pompes centrifuges |
US20070110543A1 (en) * | 2005-11-12 | 2007-05-17 | Christopher Milton Fitch | Tail-driven screw fastener for use in tamper-resistant and decorative applications |
FR2939470A1 (fr) * | 2008-12-10 | 2010-06-11 | Snecma | Soufflante pour turbomachine comprenant un systeme d'equilibrage a trous borgnes de logement de masses |
Also Published As
Publication number | Publication date |
---|---|
GB2536592B (en) | 2020-07-01 |
US20160333695A1 (en) | 2016-11-17 |
GB201612315D0 (en) | 2016-08-31 |
FR3016392A1 (fr) | 2015-07-17 |
US10598017B2 (en) | 2020-03-24 |
FR3016392B1 (fr) | 2016-02-05 |
GB2536592A (en) | 2016-09-21 |
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