WO2017067982A1 - Unité de micro-turbine à gaz améliorée et son procédé de fonctionnement - Google Patents

Unité de micro-turbine à gaz améliorée et son procédé de fonctionnement Download PDF

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Publication number
WO2017067982A1
WO2017067982A1 PCT/EP2016/075090 EP2016075090W WO2017067982A1 WO 2017067982 A1 WO2017067982 A1 WO 2017067982A1 EP 2016075090 W EP2016075090 W EP 2016075090W WO 2017067982 A1 WO2017067982 A1 WO 2017067982A1
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WO
WIPO (PCT)
Prior art keywords
bearing
shaft
turbine
thrust
elements
Prior art date
Application number
PCT/EP2016/075090
Other languages
English (en)
Inventor
Fabrizio Stefani
Ramon FRANCESCONI
Andrea Perrone
Luca RATTO
Original Assignee
Universita' Degli Studi Di Genova
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 Universita' Degli Studi Di Genova filed Critical Universita' Degli Studi Di Genova
Publication of WO2017067982A1 publication Critical patent/WO2017067982A1/fr

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/22—Lubricating arrangements using working-fluid or other gaseous fluid as lubricant
    • 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
    • F01D25/166—Sliding contact bearing
    • F01D25/168—Sliding contact bearing for axial load mainly
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • F05D2240/50—Bearings
    • F05D2240/52—Axial thrust bearings
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/80—Size or power range of the machines
    • F05D2250/82—Micromachines

Definitions

  • the present invention relates to the field of micro gas turbine units.
  • turbomachines usually comprising a compressor, a combustion chamber and a small turbine, typically working at a rotational speed even of 100,000 rpm.
  • Such machines are made according to the standard ISO 3977-1:1997 and have dimensions compatible with powers ranging from 28 kW to about 100-200 kW.
  • micro gas turbine units In micro gas turbine units the rotor of the compressor and the rotor of the turbine are mounted on the same (single) shaft.
  • the shaft is held in position with respect to a frame, free to rotate, by means of rolling bearings, often angular contact bearings.
  • Such lifespans have to be ideally compared with the lifespan of a micro gas turbine unit, that currently is 60,000-80,000 hours.
  • the air foil bearing exerts its function when the rotational speed is such to generate an aerodynamic lift thereof .
  • the suggested solution that provides air foil bearings, is optimal in a continuous operating condition, but it has still some drawbacks if it is employed on plants (such as micro gas turbine units) that are frequently started/stopped.
  • foil bearings Another drawback of foil bearings is their high costs. Still another drawback is the low load capacity (specific bearing load of 0,7 Mpa against 2Mpa of rolling bearings) and the impossibility of a retrofit (installation on already existing units) : the fact of selecting air foil bearings involves a design philosophy completely different from that of rolling bearings (for example shafts will have to have a higher diameter such to guarantee the sufficient peripheral speed allowing a suitable aerodynamic lift) .
  • foil bearings have to be suitably designed for each specific application; this makes their availability reduced on the whole.
  • Another object of the invention is to suitably distribute thrusts, such to suitably load the bearings.
  • the general idea at the base of the present invention provides to make a micro gas turbine unit comprising a frame, a compressor part provided with at least one compressor rotor, a turbine part provided with at least one turbine rotor, which compressor rotor and turbine rotor are connected by a shaft, wherein according to the invention in at least one operating condition of the unit the turbine rotor is coupled to the frame such to discharge thereon all or a part of an axial load.
  • the turbine rotor is coupled to a first end of the shaft by a first spline coupling, said first spline coupling being a helical spline, which helical spline ends at an annular shoulder of the shaft, and wherein the compressor rotor is coupled to a second and opposite end of the shaft by a second spline coupling, there being further provided:
  • At least one main thrust air bearing comprising first and second aerodynamic elements intended to generate an aerodynamic lift of the first elements relative to the second elements above a rotational speed of relative lift between said first and second elements, said first elements being fastened to the turbine rotor and said second elements being fastened to the frame, such to discharge thereon an axial thrust generated by the turbine rotor in an operating condition wherein the turbine rotor rotates at a speed higher than or equal to said lift speed,
  • the main thrust air bearing upon the self-lift phase discharges the thrust on the frame while under sliding contact conditions (at low speed) it discharges it on the shaft.
  • the air bearing is not more affected by wear due to repeated start/stop cycles.
  • the provision of the air bearing, together with the manner it is mounted and with the provision of the helical spline (wherein grooves form a helix around the shaft) in practice makes a kind of "load partitioner” .
  • the aim of the "load partitioner” is to distribute the axial load between the auxiliary thrust bearing and the main air bearing.
  • the auxiliary bearing supports the axial load while the main thrust bearing works as relieved and thus with a minimum or null wear.
  • the thrust of the turbine is exerted by the turbine rotor on the shoulder of the shaft rather than on the air bearing. Through the shoulder and the shaft such thrust is then transferred to the support of the shaft, that is to the auxiliary bearing, as in a conventional bearings-rotor layout.
  • the main air bearing starts to bear and it relieves the auxiliary bearing: the shoulder of the shaft does not receive any more the thrust since the turbine rotor, forced by the aerodynamic pressure generated in the film of the main bearing, moves on the spline coupling and moves away from the shoulder.
  • the load is transferred between the two bearings such to prevent the main bearing from being worn during the start/stop phase of the machine and such to relieve the auxiliary bearing of the axial load under full operating condition.
  • the splined profile on the turbine side acts as a load partitioner in two manners :
  • the major function as load partitioner is the second one of the two manners just described that is the function carried out by a helical spline: theoretically speaking the first manner requires a micrometric axial movement (since the aerodynamic film is in the order of a micron) .
  • the thrust of the turbine Ft would be completely supported by the main thrust bearing as well as the compressor thrust Fc would be supported by the auxiliary bearing.
  • the helical spline acts as an actuator since the torque exerted by the working fluid on the blades of the rotor is translated into an axial thrust on the shaft due to the kinematic bond between rotation and axial movement characteristic of the helical pair, where such movement depends on the helix angle.
  • the transfer of the load between the two bearings is achieved such to guarantee an optimal life of the thrust /radial auxiliary bearings and to reduce loads on the air thrust bearing.
  • the second spline coupling is a straight tooth spline coupling.
  • the main thrust air bearing is an air foil bearing, wherein the first aerodynamic elements comprise a washer and the second aerodynamic elements comprise a plurality of corrugated foils.
  • the unit further comprises a third radial bearing coupled between the frame and the shaft near the main thrust bearing, more preferably placed between the compressor and the turbine such to reduce their operating temperature .
  • the coupling of the third radial bearing with the frame is a slide coupling, where the third radial bearing is free to axially slide with respect to the frame, such to permit an axial expansion of the shaft.
  • At least one of the auxiliary radial/thrust bearing and the third radial bearing comprises a rolling bearing.
  • the rolling bearing is preferably a double direction bearing and more preferably it comprises a plurality of single-row angular contact bearings.
  • At least one of the auxiliary radial/thrust bearing and the third radial bearing comprises a magnetic bearing.
  • the helix angle ⁇ of the helical spline coupling ranges from 45 DEG to 135 DEG.
  • another object of the invention is an operating method of a micro gas turbine unit, said unit comprising a frame, a compressor part provided with at least one compressor rotor, a turbine part provided with at least one turbine rotor, which compressor rotor and turbine rotor are connected by a shaft, wherein the turbine rotor is coupled to a first end of the shaft by a first spline coupling ending at an annular shoulder of the shaft
  • At least one main thrust air bearing comprising first and second aerodynamic elements intended to generate an aerodynamic lift of the first elements relative to the second elements above a rotational speed of relative lift between said first and second elements, said first elements being fastened to the turbine rotor and said second elements being fastened to the frame,
  • the support system in the solution of the invention has fewer temperature-related problems, compared to the conventional layout, the most stressed rolling bearing has lower loads and, since it is on the compressor side, it is subjected at a less extent to temperature-related problems downstream the combustion chamber and upstream the turbine;
  • the main thrust foil bearing placed in a hotter area, usually withstands temperatures much higher than rolling bearings (foil bearings withstand above 300DEG more than rolling bearings and such margin can be further increased considering that the innovation makes not important the role of the tribology coating in foil bearings) ;
  • the spline couplings suggested in the solution of the invention allow the rotors and the bearings to be easily disassembled for overhaul and maintenance reasons; such characteristic is particularly interesting for a small machine as a micro gas turbine unit ;
  • Figure 2A is a graph about the selection of parameters for implementing the micro gas turbine unit according to the invention under a second design condition in which compressor and turbine thrusts are directed toward the outer side of the machine;
  • Figure 3 is - perspective view - an assembly of compressor rotor / shaft / turbine rotor of the micro gas turbine unit according to the invention in a partially disassembled condition;
  • Figure 4 is -longitudinal section - the turbine rotor and part of the shaft of the assembly of fig 3;
  • Figure 5 is - in perspective view - a part of the shaft of fig.4 provided with a helical spline
  • Figure 8 is - partial section - a part of the shaft and the compressor rotor of the previous figures;
  • Figure 12 is a perspective view in partial phantom of the turbine rotor comprising a third bearing
  • Figure 13 is a section of another embodiment of the invention .
  • Figure 14 is an enlarged sectional view of a particular of the embodiment of fig.13.
  • micro gas turbine unit 1 comprising a frame 2, a compressor part 3 provided with at least one compressor rotor 31, a turbine part 4 provided with at least one turbine rotor 41.
  • the turbine rotor 41 is directly coupled to the frame such to discharge thereon all or a part of an axial load.
  • directly coupled means that it is not coupled only, or solely, to the frame, by the shaft 5.
  • the compressor rotor 31 and the turbine rotor 41 are connected by a shaft 5: the turbine rotor 41 is coupled to a first end of the shaft 5 by a first spline coupling, that in the example is an helical one 51, ending at an annular shoulder 53 of the shaft 5.
  • a first straight spline coupling instead of the helical spline it is also possible to use a first straight spline coupling.
  • the compressor rotor 31 is coupled to a second - and opposite - end of the shaft 5 by a second spline coupling 52, in this non limitative example a straight tooth spline.
  • the spline couplings 51 and 52 are free, not forced, that is they allow the parts to carry out a relative movement along the grooves.
  • the diameters are selected such not to cause interference and in particular, with reference to DIN 5480 standard currently in force, they are preferably of the H/e, H/f, H/h type.
  • At least one main thrust air bearing 61 is further provided.
  • Such bearing 61 comprises first 611 and second 612 aerodynamic elements intended to generate an aerodynamic lift of the first elements 611 relative to the second elements 612 (or vice versa, in the same manner) upon reaching or exceeding a rotational speed of relative lift between the first and second elements 611, 612.
  • the first elements 611 are fastened to the turbine rotor 41 while the second elements 612 are fastened to the frame 2, such to discharge thereon an axial thrust generated by the turbine rotor 41 in an operating condition where the turbine rotor rotates at a speed higher than or equal to said lift speed.
  • the unit 1 then comprises the auxiliary radial/thrust bearing 62, interposed between the frame 2 and the shaft 5 near the spline coupling 52.
  • the radial/thrust bearing 62 (preferably angular contact ball bearing) is placed on the compressor side, as an auxiliary axial and radial support, while the thrust air bearing 61, preferably a foil bearing, is placed on the turbine side, as the main axial support.
  • the connections with the shaft 5 of rotors 31, 41 of the compressor and of the turbine are a conventional spline coupling 52 (grooves with straight generatrices) and a helical spline 51 (grooves with helical generatrices) respectively.
  • the latter acts as a "thrust partitioner" between the main thrust bearing 61 and the radial/thrust one or auxiliary one 62.
  • the bearing 61 has pads or foils 612 fastened to the frame and the washer 611 integral with the turbine rotor 41; their relative position and the preloading of the foils can be adjusted by means of spacers.
  • Such main thrust bearing 61 in full operating condition discharges the thrust (preferably the most considerable portion) directly on the frame 2 (and not on the shaft 5) .
  • Such portion is variable and it is defined in design phase by selecting the helix angle of the spline 51. Moreover the life of such main thrust bearing 61, limited only by the number of starts/stops of the machine, is practically infinite, since the load is completely borne by the angular contact bearing 62 till the generation of the speed forming the air film dynamized by virtue of the positioning of the foils or pads 612 on the frame 2. When the foil bearing 61 has no aerodynamic lift, the thrust of the turbine rotor 41 acts on the shoulder 53 of the shaft 5.
  • the main thrust air bearing 61 is an air foil bearing
  • the first aerodynamic elements 611 comprise a washer
  • the second aerodynamic elements 612 comprise a plurality of pads composed of a plurality of corrugated foils 614 and a smooth top foil 613, such as shown in figs. 9-11.
  • the second aerodynamic elements 612 are fastened to the frame such as shown in fig.4, while the washer is placed on the rear part of the turbine rotor 41, such that the opposite surfaces of the sliding kinematic pair (that is the top foils of the pads and the surface of the washer) , are separated by a given clearance ca .
  • the two surfaces of the pair of the air foil bearing are preferably in contact when the rotational speed of the turbine is zero (unit 1 in stop condition) , such that the elasticity of the corrugated foils exerts a given (slight) preloading.
  • the clearance ca therefore is provided (slightly) negative (the structure composed of the foils 612 is elastic) .
  • the thrust of the turbine rotor 41 acts on the shoulder 53 of the shaft 5.
  • its micrometric thickness causes the washer 611 to be moved by the same amount and the turbine rotor 41 to be moved in the axial direction (with reference to the shaft) such that the contact between the hub of the turbine rotor 41 and the shoulder 53 does not occur anymore.
  • Such helix spline 51 acts as a "thrust partitioner" between the main thrust bearing 61 and the auxiliary bearing 62.
  • Vectors Ft and Fc are the thrust Ft of the turbine and the thrust Fc of the compressor, respectively, generated by the pressure of the fluid on the relevant blades.
  • the force Ft-R acts on the bearing 61.
  • Vectors R show the actions and (equal) reactions that the turbine rotor exerts on the shaft through the helical spline coupling 51.
  • the axial force Fc-R is the thrust to which the shaft is subjected and that will be supported by the auxiliary thrust bearing 62.
  • Inventors have analysed the different scenarios as the helix angle ⁇ of the spline 51 changes from 45DEG to 135DEG, where a 90DEG value corresponds to a spline with straight generatrices (straight teeth) .
  • rp is the radius of the pitch circle in the event of involute spline profiles or the inner radius for straight-sided profiles.
  • figure 2 shows as a function of the helix angle ⁇ , for the data supposed above in table 1, the trend of the load transfer R (continuous thick curve) in line with the above equation.
  • ⁇ 90 ⁇
  • the load on the main thrust bearing 61 is higher than the one related to a conventional plant, since it is equal to the whole thrust Ft of the turbine, while the auxiliary radial/thrust bearing 62 bears the thrust Fc of the compressor, directed from the compressor to the turbine (positive) .
  • the maximum lifespan/reliability of the bearing 62 is achieved for the minimum one typical of the conventional layout for the most hard load on the main thrust bearing 61, equal to that of a conventional layout, occurs at the minimum (null) one for
  • the helix angle ⁇ is clearly shown in fig.5 and it corresponds to the acute angle measured between the tangent to one of the helixes drawn by the side of a tooth on the pitch cylinder and a plane perpendicular to the axis of the cylinder.
  • the graphical construction shown in fig. 2 aimed to find the possible design range for the helix angle ⁇ , consists of finding the zeros of the thrust functions Tt and Ts, i.e. the axial loads of the bearings (61) and (62), respectively, as a function of ⁇ . Such zeros locate the limits of ⁇ .
  • backside pressure plays an important role in determining the nominal axial thrusts.
  • compressor, turbine as well as total thrust directions can vary noticeably in intensity and reverse.
  • An axial force reversal can also occur during transient operation, e.g. the start/stop phase of the unit.
  • the range of design helix angles ⁇ which has been previously determined by means of the equation of the load transfer R and the graphical construction in fig. 2, may considerably change with the impeller design.
  • the upper and lower limits of the design angles which are respectively 82 and 76 DEG in fig. 2, can remarkably change when turbine, compressor and resultant thrusts (Ft, Fc and Tref ) are different from the values reported in tab. 1.
  • the helix angle of the spline coupling (51) can be chosen with reference to the nominal working conditions on the basis of the target life of the bearings within a suitable range, which limits are assessed by means of the proposed graphical construction.
  • the resulting choice of ⁇ must finally fall within the admissible range 45-135 DEG.
  • the second spline coupling 52 is a straight tooth spline coupling; however - as an alternative - it could be also another type of spline coupling, or, even, an interference fit.
  • main thrust air bearing 61 it is shown in a preferred embodiment in figures 9-11, showing the air foil bearing 61, the first aerodynamic elements 611 comprising a washer and the second aerodynamic elements 612 comprising a plurality of corrugated foils 614 and one smooth top foil 613.
  • the positioning of the parts is such that
  • the turbine rotor 41 is moved away from the annular shoulder 53 of the shaft 5, such that an axial thrust of the turbine rotor 41 is discharged partially directly on the frame 2 through the main thrust air bearing 61 and partially on the shaft 5 through the helical spline coupling 51.
  • a third radial bearing 63 visible in fig. 12 and coupled between the frame 2 and the shaft 5 near the main thrust bearing 61, the coupling of the third radial bearing 63 with the frame 5 being a slide coupling, where the third radial bearing 63 is free to axially slide with respect to the frame, such to permit an axial expansion of the shaft 5.
  • the use of the bearing 63 is suitable such not to cause the shaft 5 to work in a projecting manner.
  • auxiliary radial/thrust bearing 62 and the third radial bearing 63 if any, in one embodiment at least one of them comprises a rolling bearing, preferably a double direction bearing and still more preferably it comprises a plurality of single-row angular contact bearing.
  • the angular contact rolling bearing 62 shown is able to support both radial and axial loads, which are due to the weight of the rotor or a part thereof and to the action of the compressor and of the turbine respectively. Since the axial load is directed from the compressor 3 to the turbine 4 at the start and in an opposite direction under full operating condition, the bearing 62 is a double direction bearing; as an alternative, in the same manner, the same bearing 62 could be replaced by two single direction bearings put side by side or still, more generally, by a plurality of bearings exerting a function equivalent to that of a double direction bearing .
  • the bearing 62 is composed of two (or more) single-row angular contact bearings coupled with each other .
  • Figures show, for simplicity reasons, a solution where the bearing 62 is a four-point contact ball bearing.
  • Such bearing is mounted by inserting the outer ring into a suitable cavity in the frame of the machine and by placing the inner ring on the relevant seat on the shaft 5, with suitable tolerances.
  • outer ring is axially constrained to the frame 2 such to react to axial actions.
  • auxiliary radial/thrust bearing 62 and the third radial bearing 63 comprise a magnetic bearing, of the active or passive type .
  • the thrust Ft reverses and the constraint 61 should be on the opposite part (the low-pressure side) of the turbine 4.
  • the runner 611 which is mounted on the high-pressure side of the impeller 41 in fig. 4, might be moved on its opposite side and the location of bearing pads 612 might be modified accordingly.
  • a more straightforward solution of the present invention consists in manufacturing a thrust collar/runner 611 that is either integral part of the turbine impeller or rigidly fastened to it, so that the bearing pads 612 can be located on both the sides of the runner regardless of the thrust direction.
  • the main thrust bearing 61 is a double effect foil air bearing instead of a single effect one.
  • the pads 612 are located on both sides of the thrust collar/runner 611.
  • the group of pads on the side that carries the thrust load in nominal working conditions is termed the “loaded” or active bearing, while the other group, on the opposite side of the thrust collar, is called the “slack" side or inactive bearing.
  • the active bearing is located on the right side of the runner and the helix angle ⁇ of the spline coupling 51 is lower than 90 DEG.
  • the annular shoulder 53 does not receive the thrust load directly from the turbine impeller 41. Indeed, it exerts the thrust on the inner ring side 54 of the bearing 63.
  • the flat washer 23 is fastened to the shaft 5 with a locking ring nut 24.
  • the spacer 22 is mounted between the washer 23 and the impeller 41 in order to adjust the axial gap of the turbine hub-shaft coupling.
  • two spacers 21 are employed to adjust the axial clearance of the air bearings (the active as well as the inactive one) .
  • the gap between pads and runner of the air bearings is the desired operating clearance and it is referred to as "hot" clearance.
  • the gap csl is the clearance between the spacer 22 and the turbine impeller 41, while cs2 is the gap between the turbine impeller 41 and the inner ring side 54 of the bearing 63.
  • the total hot clearance cat In order to avoid wear of the double-effect air bearing 61 due to dry contact between runner and pads at low speed, the total hot clearance cat must be higher than the clearance est (cat>cst) .
  • the axial clearance est of the coupling 51 must be very little (in the micron-length scale) .
  • est must be greater than the equivalent RMS roughness of the two contact surfaces at the impeller 41/inner ring side 54 interface (or impeller/annular shoulder 53, if the bearing 63 is not employed) , in order to provide the relief of the secondary axial bearing 62 over the speed at which the runner 611 becomes airborne.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne une unité de micro-turbine à gaz (1) comprenant un cadre (2), une partie compresseur (3) pourvue d'au moins un rotor de compresseur (31), une partie turbine (4) pourvue d'au moins un rotor de turbine (41), ledit rotor de compresseur (31) et ledit rotor de turbine (41) étant raccordés par un arbre (5) et, dans au moins une condition de fonctionnement de l'unité (1), le rotor de turbine (41) étant directement accouplé au cadre (2) de manière à décharger sur celui-ci une partie ou la totalité d'une charge axiale.
PCT/EP2016/075090 2015-10-20 2016-10-19 Unité de micro-turbine à gaz améliorée et son procédé de fonctionnement WO2017067982A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITUB2015A004891A ITUB20154891A1 (it) 2015-10-20 2015-10-20 Unita micro-turbogas perfezionato
IT102015000063286 2015-10-20

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WO2017067982A1 true WO2017067982A1 (fr) 2017-04-27

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB658778A (en) * 1948-10-28 1951-10-10 Rolls Royce Improvements relating to rotary fluid machine assemblies
US2732695A (en) * 1956-01-31 davis
JP2003148461A (ja) * 2001-11-15 2003-05-21 Mitsubishi Heavy Ind Ltd 動圧型気体軸受及び動圧型気体軸受を備えたマイクロガスタービン
WO2015141806A1 (fr) * 2014-03-19 2015-09-24 Ntn株式会社 Palier à feuilles

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2732695A (en) * 1956-01-31 davis
GB658778A (en) * 1948-10-28 1951-10-10 Rolls Royce Improvements relating to rotary fluid machine assemblies
JP2003148461A (ja) * 2001-11-15 2003-05-21 Mitsubishi Heavy Ind Ltd 動圧型気体軸受及び動圧型気体軸受を備えたマイクロガスタービン
WO2015141806A1 (fr) * 2014-03-19 2015-09-24 Ntn株式会社 Palier à feuilles

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