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

• CD rt i f 9 rt CD CD ⁇ CD 0 CD ⁇ P. ⁇ TJ ii ro 0 rt TJ 3 ⁇ - ⁇ ⁇ - CQ H 9J TJ 9 ) rt rt 0 ii rt CD 0 TJ 9 ) ⁇ - rt 0 0 TJ ⁇ i ⁇ tr rt rt ⁇ - 0 tr rt ii CD 1 tr rt 0 0 0 rt ⁇ •> 1 H. 9 ) rt 0
• CD 0 9 rt tr ⁇ - 3 CD 0 ii tr •» 3 0 ⁇ CQ CD tr CQ ⁇ . 0 ⁇ tr rt rt rt tr ⁇ D 9 ) 0 rt CQ 0 tr CD CD rt tr CD ⁇ - CD rt 9 ) 9 ) ro li H 1 ) CD CD 0 f» D ⁇ 0 CQ CD ⁇ - rt Hi 9 ) 91 CD CQ $ ⁇ fl 0 ⁇ CD ⁇ • ⁇ !
• 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 .

Landscapes

• 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)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Manufacture Of Motors, Generators (AREA)

Priority Applications (1)

Applications Claiming Priority (2)

Publications (1)

Family

ID=20279588

Family Applications (1)

Country Status (3)

Cited By (9)

Citations (4)

• 2000
  • 2000-05-09 SE SE0001690A patent/SE520612C2/sv not_active IP Right Cessation
• 2001
  • 2001-05-08 WO PCT/SE2001/000993 patent/WO2001086130A1/en active Application Filing
  • 2001-05-08 AU AU2001256913A patent/AU2001256913A1/en not_active Abandoned

Patent Citations (4)

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