WO2001086130A1 - A rotor unit and a method for its balancing - Google Patents

A rotor unit and a method for its balancing Download PDF

Info

Publication number
WO2001086130A1
WO2001086130A1 PCT/SE2001/000993 SE0100993W WO0186130A1 WO 2001086130 A1 WO2001086130 A1 WO 2001086130A1 SE 0100993 W SE0100993 W SE 0100993W WO 0186130 A1 WO0186130 A1 WO 0186130A1
Authority
WO
WIPO (PCT)
Prior art keywords
balancing
rotor
tie bolt
shaft
unbalance
Prior art date
Application number
PCT/SE2001/000993
Other languages
French (fr)
Inventor
Johnny Rehn
Original Assignee
Turbec Ab
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Turbec Ab filed Critical Turbec Ab
Priority to AU2001256913A priority Critical patent/AU2001256913A1/en
Publication of WO2001086130A1 publication Critical patent/WO2001086130A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • F02C3/09—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage of the centripetal type
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • 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
    • 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
    • G01M1/24—Performing balancing on elastic shafts, e.g. for crankshafts
    • 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
    • G01M1/36—Compensating imbalance by adjusting position of masses built-in the body to be tested

Definitions

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  • the construction of a gas turbine unit is simplified due to fewer parts, i e no gear is needed between the generator and the rotor unit, and the maintanence and replacement of a rotor unit is facilitated due to the fact that the balancing of it can be done in advance and it can be stored as a stock article, thereby reducing associated costs.
  • the time required when handling the rotor unit is reduced due to fewer parts.
  • FIG 1 is a longitudinal side view in section showing a preferred embodiment of a rotor unit according to the invention mounted in a gas turbine
  • FIG 2 is a longitudinal side view in section showing a first preferred embodiment of a rotor unit according to the invention
  • FIG 3 is a longitudinal side view in section showing a second preferred embodiment of a rotor unit according to the invention
  • FIG 4 is an enlarged longitudinal side view in section showing one end of any of the preferred embodiments of the rotor unit
  • FIG 5 is an enlarged longitudinal side view in section showing the other end of the first embodiment of the rotor unit in FIG 2,
  • FIG 6 is an enlarged longitudinal side view in section showing the other end of the second embodiment of the rotor unit in FIG 3
  • FIG 7 is a side view of the rotor unit in FIG 3 illustrating the locations and planes on the rotor unit where unbalances are measured and compensated during a balancing procedure of the rotor unit according to the invention
  • FIG 8 is a side view illustrating a step in the balancing procedure in FIG 7,
  • FIG 9 is a side view illustrating another step in the balancing procedure in FIG 7, and
  • FIG 10 is a side view illustrating yet another step in the balancing procedure in FIG 7.
  • FIG 1 shows a rotor unit 10 according to the invention mounted in a gas turbine unit 20.
  • the gas turbine unit also comprises a housing 2, a combustion chamber 3 (only partly shown) , a generator 4, and an air intake 5.
  • FIGS 2-3 show the rotor unit 10 according to the invention in two preferred embodiments .
  • the rotor unit comprises a mono-shaft construction 30 below simply called a mono-shaft, i e a single shaft for a compressor wheel 40, a turbine wheel 50, and a generator rotor 80 in the generator 4, wherein the turbine wheel drives both the compressor wheel and the generator rotor.
  • the compressor wheel 40 is of a single-stage centrifugal type and the turbine wheel 50 is of a single-stage radial- flow type.
  • the mono-shaft 30 also comprises a tie bolt 60, a tie bolt nut 70 and a first bearing arrangement 100 at a first end, and a second bearing arrangement 110 and a rotor shaft 90 at a second end.
  • the compressor wheel 40 and the turbine wheel 50 form a detachable unit, which is attached by means of the tie bolt 60 at the second end of said mono- shaft 30, creating a shaft overhang.
  • the tie bolt 60 is a solid, long and straight essentially cylinder-shaped axle and has at least one rest surface S0 seen in FIGS 2-6, for supporting the tie bolt against the inner walls of the centre through hole in the mono-shaft 30. This support is achieved due to the bigger diameter at the rest surface, whereby the portion or portions between the rest surface and respective ends of the tie bolt 60 have a smaller diameter forming a waist. The ends of the tie bolt are threaded.
  • the mono-shaft 30 is essentially cylinder-shaped and is composed of the generator rotor 80 and the rotor shaft 90, each of them being cylinder-shaped and having a centre through hole for containing the tie bolt 60.
  • the generator rotor has different constructions in the two embodiments, shown in FIG 2 and 3 , by differently designed annular permanent-magnets 81a, 81b around its periphery giving certain features for the generator rotor 80a with permanent-magnets 81a in FIG 2 and other features for the generator rotor 80b with permanent-magnets 81b in FIG 3.
  • the second embodiment of the generator rotor 80b also comprises a runner retainer 61 and a screw 62 for attaching it to the first end of the generator rotor 80b, as shown in FIG 3.
  • the runner retainer is equipped with magnets, which are placed so that they correspond to the poles of the magnets 81b on the generator rotor 80b, serving as a help when starting the gas turbine unit 20.
  • Another balancing principle when balancing is first to weigh all of the rotating parts to be balanced before starting the balancing procedure, then calibrating and measuring wobbling, unbalances and remaining unbalances for the concerned parts.
  • Another balancing principle that may be used differs from the above-mentioned principle in that the weighing of the parts to be balanced is unnecessary, as is readily understood by a skilled person using a common balancing machine of today. All the other balancing steps in this second balancing principle are the same as in the first principle .
  • the balancing is first done for the generator rotor 80a or 80b and then together with the other rotating parts, which are mounted step by step forming groups up to the complete rotor unit 10.
  • Each step is documented regarding wobbling, unbalance, unbalance remaining after the calibration, and the result of the balancing in a balancing record.
  • the calibration of each part and group of parts is done in an ordinary balancing machine available on the market (not shown) .
  • the balancing machine measures the unbalance at predefined planes and locations of the rotor unit 10, shown in FIG 7, by rotating the rotor unit at a certain rotation speed, in this application 2500 rpm, thereby defining the quantity of unbalance, and the location and the radius on which it is located.
  • the balancing procedure may be performed at any other suitable rotation speed, e g at speeds lower than 2500 rpm, speeds higher than 2500 rpm, and even at full speed for the gas turbine when operating at full load, as is readily understood by a skilled person.
  • the measured unbalance is compensated by putting adhesive material on the right radius, position and plane corresponding to the unbalance, i e spaced 180° from the location of the unbalance seen in a circle, until the unbalance is almost equal to zero or below an allowed ⁇ ⁇ to to ⁇ 1
  • the ball bearing 101 is mounted at the first end of the generator rotor, the roller bearing 111 and a long balancing sleeve 120 are mounted at the second end, and the tie bolt 60, the tie bolt nut 70 and the bearing clamp plate 102 are mounted at the first end, as shown in FIG 8.
  • This is followed by a rough calibration in the balancing machine at plane C and D shown in FIG 7, and a rough balancing by cutting, here drilling away material at plane C and D at radius 24 mm with an inclination of 20°. Remaining unbalance may be compensated for by putting adhesive material on the appropriate radius at plane C and D.
  • the long balancing sleeve 120 is removed, and the rotor shaft 90 and a short balancing sleeve 130 are mounted at the second end of the generator rotor 80a or 80b, and the tie bolt 60, the tie bolt nut 70 and the bearing clamp plate 102 are mounted at the first end of the generator rotor as shown in FIG 9.
  • These components are then calibrated as a group in the balancing machine at plane C and L shown in FIG 7, wherein unbalance may be compensated for by putting adhesive material on the right radius at plane of the rotor shaft .
  • the short balancing sleeve 130 is removed, and the compressor wheel 40 and a balancing sleeve 140 are mounted at the second end of the generator rotor 80a or 80b, and the tie bolt 60, the tie bolt nut 70 and the bearing clamp plate 102 are mounted as in the preceding step, as is illustrated in FIG 10.
  • the generator rotor 80a or 80b, the rotor shaft 90, the compressor wheel 40, the balancing sleeve 140, the tie bolt, the tie bolt nut, and the bearing clamp plate 102 are calibrated as a group in the balancing machine at plane E and F shown in FIG 7.
  • the compressor wheel 40 is mounted in four different positions, each ⁇ CO to t ⁇ 1
  • the balancing sleeve 140 is then removed, and the turbine wheel 50, the turbine sleeve 53 and the turbine nut 52 are mounted together with the tie bolt 60, the tie bolt nut 70 and the bearing clamp plate 102, wherein the tie bolt is mounted in the same way as in the preceding steps.
  • the wobbling of the outlet of the turbine wheel is measured and documented, and material on the turbine wheel 50 is cut away by grinding its surface at plane G and the surface at plane H near the outlet of the turbine wheel . Large amounts of material are cut away with the turbine wheel 50 dismounted, and an unbalance of 10 gmm is allowed at plane G and an unbalance of 5 gmm is allowed at plane H.
  • a final cutting can be done with the turbine wheel mounted for achieving an approved balancing result .
  • a control of the final balancing is done by transferring the value of the unbalance for the turbine wheel to the calibration planes of the generator rotor 80a or 80b, i e the unbalance at planes C and D has to be below an approved level .
  • the complete bearing arrangements 100 and 110 are mounted, whereby the rotor unit is complete, for checking that possible remaining unbalance after the final balancing lies within the allowed interval.
  • the last step of balancing the rotor unit 10 concerns an accurate marking of the "best" positions for all of the balanced rotating components adherent to the rotor unit.
  • balancing planes A-L may be changed for the same reasons .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Manufacture Of Motors, Generators (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A gas turbine unit (20) has a rotor unit (10) comprising a mono-shaft (30), a compressor wheel (40), a turbine wheel (50), a tie bolt (60), and a tie bolt nut (70). The mono-shaft (30) is essentially cylinder-shaped with a centre through hole for containing the tie bolt (60), and has a first supporting bearing arrangement (100) detachably attached to a first end and a second supporting bearing arrangement (110) detachably attached to a second end. The compressor wheel (40) and the turbine wheel (50) constitute a detachable unit, which is attached by means of the tie bolt (60) at the second end of the mono-shaft (30), forming a shaft overhang, the tie bolt protruding through the centre of the mono-shaft and into the centre of the turbine wheel.

Description

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concerns sub steps of mounting each part or group of parts together, then calibrating each part or group of parts by registering its unbalance. This is followed by balancing each part or group of parts by cutting away material corresponding to the unbalance until an unbalance below an approved value for the complete rotor^unit is achieved. The last step concerns marking this "best" position or final balancing state on each rotating part of the complete rotor unit . By providing a gas turbine unit with a rotor unit that is easily balanced, the following advantages are obtained: the construction of a gas turbine unit is simplified due to fewer parts, i e no gear is needed between the generator and the rotor unit, and the maintanence and replacement of a rotor unit is facilitated due to the fact that the balancing of it can be done in advance and it can be stored as a stock article, thereby reducing associated costs. Moreover, the time required when handling the rotor unit is reduced due to fewer parts.
Brief Description of the Drawings The present invention will now be described in further detail, reference being made to the accompanying drawings, in which: FIG 1 is a longitudinal side view in section showing a preferred embodiment of a rotor unit according to the invention mounted in a gas turbine,
FIG 2 is a longitudinal side view in section showing a first preferred embodiment of a rotor unit according to the invention,
FIG 3 is a longitudinal side view in section showing a second preferred embodiment of a rotor unit according to the invention, FIG 4 is an enlarged longitudinal side view in section showing one end of any of the preferred embodiments of the rotor unit,
FIG 5 is an enlarged longitudinal side view in section showing the other end of the first embodiment of the rotor unit in FIG 2,
FIG 6 is an enlarged longitudinal side view in section showing the other end of the second embodiment of the rotor unit in FIG 3 , FIG 7 is a side view of the rotor unit in FIG 3 illustrating the locations and planes on the rotor unit where unbalances are measured and compensated during a balancing procedure of the rotor unit according to the invention, FIG 8 is a side view illustrating a step in the balancing procedure in FIG 7,
FIG 9 is a side view illustrating another step in the balancing procedure in FIG 7, and
FIG 10 is a side view illustrating yet another step in the balancing procedure in FIG 7.
Detailed Description of the Invention
FIG 1 shows a rotor unit 10 according to the invention mounted in a gas turbine unit 20. The gas turbine unit also comprises a housing 2, a combustion chamber 3 (only partly shown) , a generator 4, and an air intake 5.
FIGS 2-3 show the rotor unit 10 according to the invention in two preferred embodiments . For clarity reasons no sectioning are shown in the following drawings. The rotor unit comprises a mono-shaft construction 30 below simply called a mono-shaft, i e a single shaft for a compressor wheel 40, a turbine wheel 50, and a generator rotor 80 in the generator 4, wherein the turbine wheel drives both the compressor wheel and the generator rotor. The compressor wheel 40 is of a single-stage centrifugal type and the turbine wheel 50 is of a single-stage radial- flow type. The mono-shaft 30 also comprises a tie bolt 60, a tie bolt nut 70 and a first bearing arrangement 100 at a first end, and a second bearing arrangement 110 and a rotor shaft 90 at a second end. The compressor wheel 40 and the turbine wheel 50 form a detachable unit, which is attached by means of the tie bolt 60 at the second end of said mono- shaft 30, creating a shaft overhang.
The tie bolt 60 is a solid, long and straight essentially cylinder-shaped axle and has at least one rest surface S0 seen in FIGS 2-6, for supporting the tie bolt against the inner walls of the centre through hole in the mono-shaft 30. This support is achieved due to the bigger diameter at the rest surface, whereby the portion or portions between the rest surface and respective ends of the tie bolt 60 have a smaller diameter forming a waist. The ends of the tie bolt are threaded.
The mono-shaft 30 is essentially cylinder-shaped and is composed of the generator rotor 80 and the rotor shaft 90, each of them being cylinder-shaped and having a centre through hole for containing the tie bolt 60. The generator rotor has different constructions in the two embodiments, shown in FIG 2 and 3 , by differently designed annular permanent-magnets 81a, 81b around its periphery giving certain features for the generator rotor 80a with permanent-magnets 81a in FIG 2 and other features for the generator rotor 80b with permanent-magnets 81b in FIG 3.
The second embodiment of the generator rotor 80b also comprises a runner retainer 61 and a screw 62 for attaching it to the first end of the generator rotor 80b, as shown in FIG 3. The runner retainer is equipped with magnets, which are placed so that they correspond to the poles of the magnets 81b on the generator rotor 80b, serving as a help when starting the gas turbine unit 20. UJ ω to DO H H
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principle when balancing is first to weigh all of the rotating parts to be balanced before starting the balancing procedure, then calibrating and measuring wobbling, unbalances and remaining unbalances for the concerned parts. Another balancing principle that may be used differs from the above-mentioned principle in that the weighing of the parts to be balanced is unnecessary, as is readily understood by a skilled person using a common balancing machine of today. All the other balancing steps in this second balancing principle are the same as in the first principle .
The balancing is first done for the generator rotor 80a or 80b and then together with the other rotating parts, which are mounted step by step forming groups up to the complete rotor unit 10.
Each step is documented regarding wobbling, unbalance, unbalance remaining after the calibration, and the result of the balancing in a balancing record. The calibration of each part and group of parts is done in an ordinary balancing machine available on the market (not shown) . The balancing machine measures the unbalance at predefined planes and locations of the rotor unit 10, shown in FIG 7, by rotating the rotor unit at a certain rotation speed, in this application 2500 rpm, thereby defining the quantity of unbalance, and the location and the radius on which it is located. The balancing procedure may be performed at any other suitable rotation speed, e g at speeds lower than 2500 rpm, speeds higher than 2500 rpm, and even at full speed for the gas turbine when operating at full load, as is readily understood by a skilled person.
Preferably, the measured unbalance is compensated by putting adhesive material on the right radius, position and plane corresponding to the unbalance, i e spaced 180° from the location of the unbalance seen in a circle, until the unbalance is almost equal to zero or below an allowed ω ω to to μ1
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the wobbling of the generator rotor 80a or 80b manually with a dial indicator for controlling that there is no big wobbling. Then the ball bearing 101 is mounted at the first end of the generator rotor, the roller bearing 111 and a long balancing sleeve 120 are mounted at the second end, and the tie bolt 60, the tie bolt nut 70 and the bearing clamp plate 102 are mounted at the first end, as shown in FIG 8. This is followed by a rough calibration in the balancing machine at plane C and D shown in FIG 7, and a rough balancing by cutting, here drilling away material at plane C and D at radius 24 mm with an inclination of 20°. Remaining unbalance may be compensated for by putting adhesive material on the appropriate radius at plane C and D. The long balancing sleeve 120 is removed, and the rotor shaft 90 and a short balancing sleeve 130 are mounted at the second end of the generator rotor 80a or 80b, and the tie bolt 60, the tie bolt nut 70 and the bearing clamp plate 102 are mounted at the first end of the generator rotor as shown in FIG 9. These components are then calibrated as a group in the balancing machine at plane C and L shown in FIG 7, wherein unbalance may be compensated for by putting adhesive material on the right radius at plane of the rotor shaft . The short balancing sleeve 130 is removed, and the compressor wheel 40 and a balancing sleeve 140 are mounted at the second end of the generator rotor 80a or 80b, and the tie bolt 60, the tie bolt nut 70 and the bearing clamp plate 102 are mounted as in the preceding step, as is illustrated in FIG 10. The generator rotor 80a or 80b, the rotor shaft 90, the compressor wheel 40, the balancing sleeve 140, the tie bolt, the tie bolt nut, and the bearing clamp plate 102 are calibrated as a group in the balancing machine at plane E and F shown in FIG 7. The compressor wheel 40 is mounted in four different positions, each ω CO to t μ1
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unbalance for the compressor wheel 40 to the calibration of the generator rotor 80a or 80b at plane C and D.
The balancing sleeve 140 is then removed, and the turbine wheel 50, the turbine sleeve 53 and the turbine nut 52 are mounted together with the tie bolt 60, the tie bolt nut 70 and the bearing clamp plate 102, wherein the tie bolt is mounted in the same way as in the preceding steps. The wobbling of the outlet of the turbine wheel is measured and documented, and material on the turbine wheel 50 is cut away by grinding its surface at plane G and the surface at plane H near the outlet of the turbine wheel . Large amounts of material are cut away with the turbine wheel 50 dismounted, and an unbalance of 10 gmm is allowed at plane G and an unbalance of 5 gmm is allowed at plane H. A final cutting can be done with the turbine wheel mounted for achieving an approved balancing result . After the turbine wheel is balanced a control of the final balancing is done by transferring the value of the unbalance for the turbine wheel to the calibration planes of the generator rotor 80a or 80b, i e the unbalance at planes C and D has to be below an approved level . Then the complete bearing arrangements 100 and 110 are mounted, whereby the rotor unit is complete, for checking that possible remaining unbalance after the final balancing lies within the allowed interval. The last step of balancing the rotor unit 10 concerns an accurate marking of the "best" positions for all of the balanced rotating components adherent to the rotor unit.
All of the balancing steps explained above are common for the two embodiments of the generator rotor 80a and 80b of the rotor unit 10 according to the invention. However, the balancing of the second embodiment of the generator rotor 80b differs from the procedure when balancing the first embodiment of the generator rotor 80a. The difference is a few additional steps in the balancing procedure before the last step of the accurate marking of the "best"
Figure imgf000015_0001
in the balancing may be altered and/or existing balancing steps may be unnecessary. Furthermore, the position and number of balancing planes A-L may be changed for the same reasons .

Claims

1. A rotor unit (10) of a gas turbine unit (20) comprising a mono-shaft (30) , a compressor wheel (40) , a turbine wheel (50) , a tie bolt (60) , and a tie bolt nut (70) , c h a r a c t e r i z e d in that the mono-shaft (30) is essentially cylinder-shaped with a centre through hole for containing the tie bolt (60) , and has a first supporting bearing arrangement (100) detachably attached to a first end and a second supporting bearing arrangement (110) detachably attached to a second end.
2. A rotor unit (10) according to claim 1, wherein the compressor wheel (40) and the turbine wheel (50) constitute a detachable unit, which is attached by means of the tie bolt (60) at the second end of the mono-shaft (30) , forming a shaft overhang, the tie bolt protruding through the centre of the mono-shaft and into the centre of the turbine wheel, where one end of the tie bolt is detachably connected to the centre of the turbine wheel or the compressor wheel, and the tie bolt nut (70) is detachably connected to the other end of the tie bolt at the first end of the mono-shaft (30) .
3. A rotor unit according to claim 2, wherein the mono-shaft (30) is composed of two parts detachable from each other, a permanent-magnet generator rotor (80a, 80b) , and a cylinder-shaped rotor shaft (90) , both having a centre through hole for containing the tie bolt (60) , and detachably attached and guided by guiding pins (31) at one end to the second end of the generator rotor, and attached at the other end to the compressor wheel (40) .
4. A rotor unit according to claim 3, wherein the tie bolt nut (70) holds the first bearing arrangement (100) against a shoulder (100') on the generator rotor (80a, 80b) by means of a bearing clamp plate (102) , thereby ensuring a secure attachment of the first bearing arrangement .
5. A rotor unit according to claim 4, wherein the rotor shaft (90) holds the second bearing arrangement (110) against a shoulder (101') on the generator rotor (80a, 80b) , thereby ensuring a secure attachment of the second bearing arrangement .
6. A rotor unit according to claim 5, wherein the permanent-magnet generator rotor (80a, 80b) has annular magnets (81a, 81b) attached around the periphery of the generator rotor forming the main outer surface between the two bearing arrangements (100, 110)
7. A rotor unit according to claim 6, wherein the compressor wheel (40) is of a single-stage centrifugal type and the turbine wheel (50) is of a single-stage radial-flow type.
8. A method for balancing the rotor unit (10) according to claim 3, c h a r a c t e r i z e d in that the balancing of the rotor unit (10) is done step by step, i e the the rotor unit is constituted by several detachable parts, which are mounted together in groups starting with the mounting and a first balancing step of a first part, then mounting another part onto the first part and balancing them together in a second step and so on until all of the parts forming the complete rotor unit (10) have been mounted and balanced together, wherein each balancing step concerns sub steps of mounting each part or group of parts together, then calibrating each part or group of parts by registering its unbalance, and then balancing each part or group of parts by cutting away material corresponding to the unbalance until an unbalance below an approved value for the complete rotor unit (10) is achieved, and finally, in the last step, marking this "best" position or final balancing state on each rotating part of the complete rotor unit (10) .
9. A method for balancing the rotor unit (10) according to claim 8, c h a r a c t e r i z e d by the consecutive steps of a first balancing step, which comprises a first sub step of measuring wobbling for the generator rotor (80a, 80b) manually with a dial indicator, a second sub step of mounting a ball bearing (101) at the first end of the generator rotor, a roller bearing (111) and a long balancing sleeve (120) at the second end, and the tie bolt (60) , the tie bolt nut (70) and the bearing clamp plate (102) at the first end of the generator rotor (80a, 80b) , a third sub step of roughly calibrating the generator rotor in a balancing machine, a fourth sub step of roughly balancing the generator rotor by cutting away material on it, and a fifth sub step of calibrating the generator rotor (80a, 80b) in the balancing machine by registering remaining unbalance in the generator rotor, a second balancing step that comprises a first sub step of removing the long balancing sleeve (120) , a second sub step of mounting the rotor shaft (90) and a short balancing sleeve (130) at the second end of the generator rotor (80a, 80b) , and the tie bolt, the tie bolt nut and the bearing clamp plate at the first end of the generator rotor, and a third sub step of calibrating the generator rotor, the rotor shaft, the short balancing sleeve, the tie bolt, the tie bolt nut, and the bearing clamp plate in the LO ω to DO μ> μ>
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compressor wheel (40) , the rotor shaft (90) , and the tie bolt (60) , and the length of the protruding part of the tie bolt is measured and documented, followed by a procedure similar to the first balancing step, which comprises a first sub step of removing the turbine wheel (50) , the compressor wheel (40) , and the rotor shaft (90) , a second sub step of mounting the long balancing sleeve (120) together with the tie bolt (60) , the tie bolt nut (70) and the bearing clamp plate (102) , wherein the tie bolt is mounted with the same length of its protruding part as in the preceding steps; and a third sub step, wherein material on the generator rotor (80a, 80b) is cut away until an unbalance below 1.0 gmm is achieved, followed by a procedure similar to the second balancing step, which comprises the first sub step of removing the long balancing sleeve (120) , the second sub step of mounting the rotor shaft (90) and the short balancing sleeve (130) together with the tie bolt (60) , the tie bolt nut (70) and the bearing clamp plate (102) ; and a third sub step, wherein material on the rotor shaft is cut away until an unbalance below 3.0 gmm is achieved, followed by a procedure similar to the third balancing step, which comprises the first sub step of removing the short balancing sleeve (130) , the second sub step of mounting the compressor wheel (40) and the balancing sleeve (140) together with the tie bolt (60) , the tie bolt nut (70) and the bearing clamp plate (102) , wherein the tie bolt is mounted with the same length of its protruding part as in the preceding step; a third sub step, wherein material on the compressor wheel is cut away at a suitable plane near the rotor shaft and/or at a suitable plane near the turbine wheel until an unbalance below 5 gmm is achieved in the plane near the rotor shaft and an unbalance below 10 gmm is achieved in the plane near the turbine; and a fourth sub step, wherein the balanced compressor wheel (40) is controlled by checking how remaining unbalance affects the bearing points of the generator rotor (80a, 80b) , followed by a procedure similar to the fourth balancing step, which comprises the first sub step of removing the balancing sleeve (140) , the second sub step of mounting the turbine wheel (50) , the turbine sleeve (51) , and the turbine nut (52) together with the tie bolt (60) , the tie bolt nut (70) and the bearing clamp plate (102) , wherein the tie bolt is mounted with the same length of its protruding part as in the preceding steps; a third sub step in which the wobbling of the turbine wheel is measured; a fourth sub step, wherein material on the turbine wheel (50) is cut away at a first plane near the compressor wheel (40) and at a second plane near the outlet of the turbine wheel, large amounts of material are cut away with the turbine wheel dismounted, an unbalance of 10 gmm is allowed in the first plane and an unbalance of 5 gmm is allowed in the second plane, a final cutting can be done with the turbine wheel mounted; and after the turbine wheel (50) is balanced a fifth sub step follows, wherein a control is done at the bearing points of the generator rotor (80a, 80b) , followed by mounting the bearing arrangements (100, 110) , whereby the rotor unit (10) is complete, for checking that possible remaining unbalance after the final balancing lies within the allowed interval, and finally the last balancing step concerns marking of this "best" position or final balancing step on all the balanced components adherent to the rotor unit (10) .
10. A method for balancing the rotor unit (10) with the second embodiment of the generator rotor (80b) according to claim 9 , c h a r a c t e r i z e d by the additional steps of mounting the runner retainer (61) and its associated screw (62) at the first end of the generator rotor (80b) after the control of the balanced turbine wheel (50) is done at the bearing points of the generator rotor (80b) , measuring and documenting the wobbling and unbalance for the runner retainer, removing the runner retainer, cutting away material on the runner retainer at a plane located opposite the magnets on the runner retainer, followed by mounting the bearing arrangements (100, 110) before the runner retainer, whereby the rotor unit (10) is complete, for checking that possible remaining unbalance for the complete rotor unit lies within the allowed interval, and that the wobbling for the runner retainer is repeated after the final balancing, and finally the last balancing step concerns marking of this "best" position or final balancing step on all the balanced components adherent to the rotor unit (10) .
PCT/SE2001/000993 2000-05-09 2001-05-08 A rotor unit and a method for its balancing WO2001086130A1 (en)

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US5624235A (en) * 1989-02-03 1997-04-29 Hitachi, Ltd. Steam turbine, rotor shaft thereof, and heat resisting steel
US5214585A (en) * 1989-06-30 1993-05-25 General Electric Company Balancing method and product
US5836739A (en) * 1995-03-17 1998-11-17 Rolls-Royce Plc Gas turbine engine

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WO2003083266A1 (en) * 2002-03-28 2003-10-09 Dentsply International Inc. Method for balancing the rotating turbine element of a dental handpiece
CN100385090C (en) * 2003-05-20 2008-04-30 通用电气公司 Apparatus and methods for coupling axially aligned turbine rotors
EP1519179A1 (en) * 2003-09-25 2005-03-30 Snecma Moteurs Device for oil unbalance detection in a rotor, rotor with such a device, and apparatus comprising such a rotor
FR2860276A1 (en) * 2003-09-25 2005-04-01 Snecma Moteurs DEVICE FOR DETECTING AN OIL BALANCE IN A ROTOR, ROTOR COMPRISING SUCH A DEVICE, AND MACHINE EQUIPPED WITH SUCH A ROTOR
US7036371B2 (en) 2003-09-25 2006-05-02 Snecma Moteurs Device for detection of an unbalanced oil mass in a rotor, rotor fitted with such a device, and machine equipped with such a rotor
EP1936114A2 (en) 2006-12-20 2008-06-25 General Electric Company Methods and systems for balancing a rotatable member
JP2008157230A (en) * 2006-12-20 2008-07-10 General Electric Co <Ge> System for balancing rotatable member
EP1936114A3 (en) * 2006-12-20 2010-07-14 General Electric Company Methods and systems for balancing a rotatable member
US9429040B2 (en) 2011-01-04 2016-08-30 Exergy S.P.A. Expansion turbine
EP2661543B1 (en) 2011-01-04 2016-09-14 Exergy S.p.A. Expansion turbine
ITMI20110001A1 (en) * 2011-01-04 2012-07-05 Exergy Orc S R L EXPANSION TURBINE
WO2012093299A1 (en) 2011-01-04 2012-07-12 Exergy Orc S.R.L. Expansion turbine
CN102434217A (en) * 2011-11-01 2012-05-02 哈尔滨东安发动机（集团）有限公司 Integrated cantilever rotor structure
CN102528374A (en) * 2012-01-04 2012-07-04 西安加立方鼓风机有限公司 On-site repairing method for SJ type air-intake sintering system
WO2015116688A1 (en) * 2014-01-30 2015-08-06 Borgwarner Inc. Exhaust-gas turbocharger
CN106414949A (en) * 2014-01-30 2017-02-15 博格华纳公司 Exhaust-gas turbocharger
CN106414949B (en) * 2014-01-30 2020-04-10 博格华纳公司 Exhaust gas turbocharger
DE102016203615A1 (en) 2016-03-04 2017-09-07 Dürr Systems Ag Gas Turbine System
WO2017148891A1 (en) 2016-03-04 2017-09-08 Dürr Systems Ag Gas turbine system

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SE0001690L (en) 2001-11-10

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