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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/26—Rotors specially for elastic fluids
  • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
  • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/60—Mounting; Assembling; Disassembling
  • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
  • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
  • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
  • F04D29/00—Details, component parts, or accessories
  • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
  • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
  • F04D29/662—Balancing of rotors
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
  • G01M1/00—Testing static or dynamic balance of machines or structures
  • G01M1/14—Determining imbalance
  • G01M1/16—Determining imbalance by oscillating or rotating the body to be tested
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
  • G01M1/00—Testing static or dynamic balance of machines or structures
  • G01M1/30—Compensating imbalance
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2230/00—Manufacture
  • F05B2230/60—Assembly methods
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2240/00—Components
  • F05B2240/40—Use of a multiplicity of similar components
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2260/00—Function
  • F05B2260/96—Preventing, counteracting or reducing vibration or noise
• • 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
• • 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 exemplary embodiments relate generally to rotor assemblies for gas turbine engines and more particularly to methods and systems for assembling rotor assemblies.
• a gas turbine engine is an example of a large rotary machine requiring dimensional precision for reducing vibration at high rotational speed. Vibration may occur due to mass unbalance around an axial centerline axis of the engine, and/or due to eccentricity of the rotor therearound. Runout, roundness, concentricity and flatness are of particular concern in an assembly of rotor components since they may contribute to eccentricity.
• the individual rotors in a typical gas turbine engine vary in configuration for aerodynamic, mechanical, and aeromechanical reasons, which increases the complexity of the engine design and the difficulty in reducing undesirable eccentricity.
• a multistage compressor or turbine includes rows of airfoils extending radially outwardly from supporting rotor disks.
• the airfoils may be removably mounted in corresponding dovetail slots formed in the perimeter of the disks, or may be integrally formed therewith in a unitary construction known as a blisk.
• Individual disks may be bolted together at corresponding annular flanges having a row of axial bolt holes through which fastening bolts extend for joining together the several rotors in axial end-to-end alignment.
• Some rotor disks are typically formed in groups in a common or unitary rotor drum, with the drum having end flanges bolted to adjoining rotors having similar annular flanges. Accordingly, the multistage assembled rotor includes several rotor disks axially joined together at corresponding annular flanges. Each rotor is separately manufactured and is subject to eccentricity between its forward and aft mounting flanges, and is also subject to non-perpendicularity or tilt of its flanges relative to the axial centerline axis of the engine. [0004] Both eccentricity and tilt of the rotor end flanges are random and typically limited to relatively small values.
• the assembly of the individual rotors with their corresponding flange eccentricities and tilts are subject to stack-up and the possibility of significantly larger maximum eccentricity due to the contribution of the individual eccentricities. Accordingly, when the rotor assembly is mounted in bearings in the supporting engine stator, the corresponding rotor seats or journals mounted in the bearings may have relative eccentricity therebetween, and intermediate flange joints between individual rotors of the assembly may have an eccentricity from the engine centerline axis which exceeds the specified limit on eccentricity for the rotors due to stack-up. In this case, the rotor assembly must be torn down and reassembled in an attempt to reduce stack-up eccentricities to an acceptable level within specification.
• One manner of reducing the random nature of the assembly stack-up is to measure each rotor during the assembly sequence to determine the runout, roundness, concentricity and flatness of mating diameters and flanges and then assembling that component to a preceding component for reducing the collective stack-up of eccentricity upon final rotor assembly.
• Individual rotors are mounted on a turntable using a suitable fixture so that the rotor may be rotated about its axial centerline axis.
• Linear measurement gauges are mounted to the table and engage the corresponding mounting flanges of the rotor for measuring any variation of radius of the flanges from the axial centerline axis around the circumference of the flanges, and for measuring any variation in axial position of each of the flanges around the circumference.
• the gauges are operatively joined to a computer, which receives the measurement data from the gauges mounted at each end flange during measurement.
• the computer is programmed to calculate various geometric parameters for the end flanges.
• the radial measurement data may be used to determine high and low points on the flanges.
• the computer may then determine a mating rotor surface based on the high and low points of the measured rotors.
• the computer may also utilize a least squares center algorithm to determine a best-fit surface. This algorithm provides a single vector representing the slope of a face surface or eccentricity of a flange surface.
• the computer may then determine a best-fit based on vectors from multiple rotors and assemble them accordingly.
• the least squares center results are a simplified description of the average surface. It presents a best-fit model not taking into account local variations in the topography of the mating surfaces and diameters, which may have a significant impact on the stack. For example, if a rotor with a flange face with two equal and substantial peaks 180 degrees apart was mated to a perfectly flat part, it could be rocked to one side or the other, pivoting about the peaks, depending on which side was attached first. Using the same example with two peaks, if the mating part had a similar feature (two peaks), the computer does not optimize the stack by looking at an interlocking of peaks.
• a system for assembling a rotor stack having a plurality of rotor disks may include a measurement system for measuring characteristics of the rotor disks, a computer electronically connected to the measurement system for capturing data from the measurement system, and solid modeling software for creating a virtual stack of the rotor disks optimized for concentricity.
• a method for assembling a rotor stack having a plurality of rotor disks may include the steps of measuring one or more characteristics of the rotor disks with a measurement system, obtaining data from the measuring step, converting the data into solid models of the rotor disks, and creating a virtual stack based on the solid models to optimize concentricity.
• Figure 1 is a schematic representation of one exemplary embodiment of a system for assembling a rotor stack.
• Figure 2 is a flow chart of one exemplary embodiment of a method for assembly a rotor stack.
• Figure 3 is a polar plot of an example data set from measuring a component to be assembled in a rotor stack.
• Figure 1 illustrates schematically one exemplary embodiment of a system 100 for assembling a rotor stack.
• the system 100 includes a measurement system 102 and a computer 104 connected to the measurement system 102.
• the measurement system 102 may be used to measure one or more characteristics of a plurality of rotor disks that may be used to assemble a rotor stack.
• the one or more characteristics may be any characteristic of a rotor disk that, taken separately or combined as a rotor stack, may contribute to the eccentricity of the rotor stack.
• the characteristics may include runout, roundness, concentricity, perpendicularity, parallelism and/or flatness.
• the measurement system may include a platform 106 that supports a turntable 108.
• the turntable 108 may fix the rotor disk 110 in a rotatable relationship to the platform 106.
• the measurement system 102 may have one or more measurement probes 112 that may be fixed to the platform 106.
• the measurement probes 112 may be any probes known in the art for measuring one or more characteristics of the rotor disk 110, including, but not limited to, linear variable displacement transducers (LVDTs), non-contact laser-based probes and ultrasonic probes.
• LVDTs linear variable displacement transducers
• the probes 112 may be positioned to measure certain locations on the rotor disk 110, such as, but not limited to, mating diameters and flanges.
• the diameters and flanges may also include a plurality of holes or other similar features that may be used with other connecting components, such as, bolts or similar components, to assemble one rotor disk to another adjacent rotor disk.
• the probes 112 may obtain data related to the characteristics of the rotor disk 110 and the locations measured.
• the computer 104 may be electronically connected to the probes 112 to capture data obtained by the probes 112.
• the computer 104 may be any suitable computer system known in the art and may include solid modeling software 114. In one exemplary embodiment, a separate computer may be used to capture the data from the probes 112.
• Solid modeling software 114 is software capable of representing the solid parts of an object in a three dimensional digital environment.
• the LVDT probes provide relative displacement.
• a rotary encoder 116 may be provided and interfaced with the computer 104 to provide simultaneous reference position information for the LVDT data
• the system 100 may be used to measure, stack and assemble a plurality of rotor disks.
• Figure 2 illustrates one exemplary embodiment of a method of assembling a rotor stack.
• a rotor disk 110 is loaded into the measurement system 102 and fixed into place on the turntable 108 at step 200.
• Measurement probes 112 are positioned adjacent the locations to be measured on the rotor disk 110 at step 202.
• the turntable 108 may be rotated and the probes 112 may capture data about the rotor disk 110.
• the probes 112 may capture data on any number of different characteristics of the rotor disk, such as, but not limited to, runout, roundness, concentricity, perpendicularity, parallelism and/or flatness.
• the captured data may be a collection of numbers related to points in space of the rotor disk.
• Figure 3 illustrates an example 118 of the data collected by the probes as represented within polar graph form. The relative deflection of the probes is displayed as a function of angular position. Noise, such as, but not limited to, friction of the probe against the rotor disk, vibration and any environmental conditions may be filtered from the data.
• a major shape 120 may be identified by a best-fit calculation of the data after the noise has been filtered.
• the data may be transmitted to the solid modeling software 114 at step 206.
• the solid modeling software 114 then translates the captured data from the probes 112 into approximations of surfaces on a solid model of the rotor disk at step 208.
• the computer 104 may be used to capture the data from the probes 112 as well as run the solid modeling software 114 or two separate computers may be used.
• the major shape 120 may be expanded to form a band that is an approximation of the surface of the part measured. This gives the solid modeling software a 3D approximation of the surface of the measured part to compare to other measured parts. Steps 200 through 208 may be repeated for each rotor disk 110 to be measured and assembled.
• the software 114 may build a virtual stack optimized for straightness and concentricity at step 210 taking into account all characteristics such as peaks and valleys inherent to the parts surface or diameter that combine to affect the outcome of the stack. This may be accomplished by iteratively checking each of the mating combinations. There may be as many mating combinations as there are holes or similar connection features in the mating components. For example, the software may begin with a predetermined mating combination, rotate the component one mating combination to the right or left and compare the mating combinations. The software may identify the better combination and then move to the next adjacent combination. This may be repeated for each mating combination. Once complete, the software will have identified the optimum mating combination.
• the virtual stack may step through a series of educated combinations.
• the software may identify the maximum and minimum surfaces of the mating components and compare those mating combinations with the adjacent mating combination.
• the software may identify the better combination and then move to the next adjacent combination on the opposite side of the original combination. This may be repeated as many times as practical until the optimum virtual stack is identified.
• the process may be repeated for each other component in the virtual stack until the optimum virtual stack is identified. This may take into account not only general measurements such as concentricity or perpendicularity, but the specific undulations seen on the diameter and faces of the mating parts.
• the rotor disks 110 may be assembled according to the optimized virtual stack, at step 212.
• the exemplary embodiments described allow a rotor stack to be formed in an optimum way by taking into account the specific geometry of each mating surface. By doing so, the amount of concentricity and perpendicularity can by minimized.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Physics & Mathematics (AREA)
• General Physics & Mathematics (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Manufacture Of Motors, Generators (AREA)

Priority Applications (4)

Applications Claiming Priority (2)

Publications (3)

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ID=40738876

Family Applications (1)

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• 2007
  • 2007-12-31 US US11/968,098 patent/US7792600B2/en not_active Expired - Fee Related
• 2008
  • 2008-12-18 DE DE112008003453T patent/DE112008003453T5/de not_active Withdrawn
  • 2008-12-18 GB GB1010160.8A patent/GB2468440B/en not_active Expired - Fee Related
  • 2008-12-18 JP JP2010540801A patent/JP2011508153A/ja active Pending
  • 2008-12-18 CA CA2710019A patent/CA2710019A1/en not_active Abandoned
  • 2008-12-18 WO PCT/US2008/087466 patent/WO2009088696A2/en not_active Ceased

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