US20050121916A1 - Integrated microturbine gearbox generator assembly - Google Patents
Integrated microturbine gearbox generator assembly Download PDFInfo
- Publication number
- US20050121916A1 US20050121916A1 US10/730,156 US73015603A US2005121916A1 US 20050121916 A1 US20050121916 A1 US 20050121916A1 US 73015603 A US73015603 A US 73015603A US 2005121916 A1 US2005121916 A1 US 2005121916A1
- Authority
- US
- United States
- Prior art keywords
- rotor
- speed
- turbine
- housing
- shaft
- Prior art date
- Legal status (The legal status 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 status listed.)
- Granted
Links
Images
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
- 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
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- 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
- 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
- F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
- F02C3/05—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module the compressor and the turbine being of the radial flow type
-
- 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
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
-
- 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
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
- H02K7/1807—Rotary generators
- H02K7/1823—Rotary generators structurally associated with turbines or similar engines
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/14—Combined heat and power generation [CHP]
Definitions
- the present invention relates to a system and method for driving a low-speed component using a high-speed prime mover. More particularly, the present invention relates to a system and method for driving a low-speed component using a high-speed microturbine.
- Microturbine engines are relatively small and efficient sources of power. Microturbines can be used to generate electricity and/or to power auxiliary equipment such as pumps or compressors. When used to generate electricity, microturbines can be used independent of the utility grid or synchronized to the utility grid. In general, microturbine engines are limited to applications requiring 2 megawatts (MW) of power or less. However, some applications larger than 2 MWs may utilize a microturbine engine.
- MW megawatts
- microturbine engines include a turbine-compressor assembly that rotates at a high rate of speed.
- the turbine-compressor assembly or a separate turbine, is coupled to the generator, which also rotates at a high rate of speed.
- the generator output is then conditioned to produce a usable electrical current (e.g., 50 Hz or 60 Hz).
- a gearbox is positioned between the turbine and the generator to allow the generator to operate at a lower speed.
- the gearbox often requires several high-speed bearings to support the various gears.
- the dynamic and mechanical issues associated with the gearbox and turbine can affect the operation of the other component.
- a slight imbalance in the gearbox can produce a vibration that is transmitted to the turbine.
- the high speed of the turbine can act to increase the magnitude or the effect caused by the vibration. This can lead to undesirable operating conditions, system instability, and unwanted engine trips or shutdowns.
- the present invention generally provides a microturbine engine comprising a turbine including a first housing and a turbine rotor.
- the engine also includes a generator having a second housing and a generator rotor.
- the generator rotor is supported for low-speed rotation by a low-speed bearing.
- the engine also includes a gearbox having a third housing connected to the first housing and the second housing, a pinion gear, and a low-speed gear connected to the generator rotor and at least partially supported by the low-speed bearing.
- a shaft is connected to the turbine rotor and the pinion gear and a first high-speed bearing and a second high-speed bearing are positioned to support the turbine rotor and the shaft for high-speed rotation.
- the invention generally provides a microturbine engine including a turbine having a turbine housing and a turbine rotor.
- the engine also includes a compressor having a compressor housing coupled to the turbine housing and a compressor rotor coupled to the turbine rotor.
- a rotor flange is coupled to the compressor rotor such that the turbine rotor, the compressor rotor, and the rotor flange at least partially define a rotor train.
- a first high-speed bearing and a second high-speed bearing are coupled to the rotor train and at least partially support the rotor train for rotation. The first high-speed bearing and the second high-speed bearing are positioned to define a space between the bearings and a space that extends beyond the bearings.
- the engine also includes a synchronous generator having a generator housing and a generator rotor.
- the generator rotor is supported for low-speed rotation by at least one low-speed bearing.
- the engine further includes a gearbox having a gearbox housing connected to the compressor housing and the generator housing.
- the gearbox includes a ring gear connected to the generator rotor, a plurality of planetary gears, and a pinion gear positioned to engage each of the planetary gears.
- a quill shaft is coupled to the rotor flange and the pinion gear such that the quill shaft is fully supported by the second high-speed bearing, which is coupled to the rotor flange, and the planetary gears.
- the present invention generally provides a method of coupling a rotating element of an engine that operates at a first speed to a driven component that operates at a second speed, the second speed slower than the first speed.
- the method includes coupling a shaft to the rotating element and supporting the rotating element and the shaft with a first high-speed bearing and a second high-speed bearing.
- the rotating element is supported such that at least a portion of the rotating element is disposed in a space between the bearings and at least a portion of the rotating element is disposed in a space beyond the bearings.
- the method also includes engaging a second end of the shaft with a plurality of planetary gears and supporting the driven component with at least one low-speed bearing.
- the method also includes coupling a low-speed gear to the driven component, the low-speed gear coupled to each of the planetary gears.
- FIG. 1 is a perspective view of a portion of a microturbine engine
- FIG. 2 is a sectional view of the turbine-compressor-generator portion of the engine of FIG. 1 ;
- FIG. 3 is an enlarged view of the turbine-compressor and gearbox portion
- FIG. 4 is an enlarged view of the gearbox portion of the engine of FIG. 1 ;
- FIG. 5 is an enlarged sectional view of a quill shaft of the microturbine engine of FIG. 1 ;
- FIG. 6 is a perspective view of the quill shaft of FIG. 4 .
- a microturbine engine system 10 that includes a turbine section 15 , a generator section 20 , and a control system 25 is illustrated.
- the turbine section 15 includes a radial flow turbine 35 , a compressor 45 , a recuperator 50 , and a combustor 55 .
- the recuperator 50 may be of the plate-fin variety with the combustor 55 in the inlet manifold as disclosed in U.S. Pat. No. 5,450,724, the entire contents of which is incorporated herein by reference.
- the engine 10 includes a standard Brayton cycle combustion turbine with the recuperator 50 added to improve engine efficiency.
- the engine shown is a single-spool engine (one set of rotating elements). However, multi-spool engines are also contemplated by the invention.
- the compressor 45 is a centrifugal-type compressor having a compressor rotor 56 that rotates in response to operation of the turbine 35 .
- the compressor 45 shown is a single-stage compressor. However, multi-stage compressors can be employed where a higher pressure ratio is desired. Alternatively, compressors of different designs (e.g., axial-flow compressors, reciprocating compressors, and the like) can be employed to supply compressed air to the engine.
- the turbine 35 is a radial flow single-stage turbine having a turbine rotor 57 directly coupled to the compressor rotor 56 . In other constructions, multi-stage turbines or other types of turbines may be employed.
- the coupled rotors 56 , 57 of the turbine 35 and the compressor 45 engage the generator section 20 through a gearbox 60 .
- the recuperator 50 includes a heat exchanger employed to transfer heat from a hot fluid to the relatively cool compressed air leaving the compressor 45 .
- One suitable recuperator 50 is described in U.S. Pat. No. 5,983,992 fully incorporated herein by reference.
- the recuperator 50 includes a plurality of heat exchange cells stacked on top of one another to define flow paths therebetween. The cool compressed air flows within the individual cells, while a flow of hot exhaust gas passes between the heat exchange cells.
- the compressor rotor 56 rotates in response to rotation of the turbine rotor 57 .
- the compressor 45 draws in atmospheric air and increases its pressure.
- the high-pressure air exits the air compressor 45 and flows to the recuperator 50 .
- the flow of compressed air, now preheated within the recuperator 50 flows to the combustor 55 as a flow of preheated air.
- the preheated air mixes with a supply of fuel within the combustor 55 and is combusted to produce a flow of products of combustion.
- the use of a recuperator 50 to preheat the air allows for the use of less fuel to reach the desired temperature within the flow of products of combustion, thereby improving engine efficiency.
- the flow of products of combustion enters the turbine 35 and transfers thermal and kinetic energy to the turbine 35 .
- the energy transfer results in rotation of the turbine rotor 57 and a drop in the temperature of the products of combustion.
- the energy transfer allows the turbine 35 to drive both the compressor 45 and the generator 20 .
- the products of combustion exit the turbine 35 as a first exhaust gas flow.
- the first turbine 35 drives only the compressor, while the second turbine drives the generator 20 or any other device to be driven.
- the second turbine receives the first exhaust flow, rotates in response to the flow of exhaust gas therethrough, and discharges a second exhaust flow.
- the first exhaust flow enters the flow areas between the heat exchange cells of the recuperator 50 and transfers excess heat energy to the flow of compressed air.
- the exhaust gas then exits the recuperator 50 and is discharged to the atmosphere, processed, or further used as desired (e.g., cogeneration using a second heat exchanger).
- FIGS. 2 and 3 the portion of the engine of FIG. 1 that includes the generator 20 , the turbine 35 , the compressor 45 , and the gearbox 60 is illustrated.
- the components are arranged and coupled to one another such that the turbine 35 , the compressor 45 , and the generator 20 rotate on a common axis A-A.
- the generator 20 may be offset such that it rotates on an axis different from that of the turbine 35 and the compressor 45 .
- the turbine 35 is located at one end of the engine 10 and includes the turbine rotor 57 and a first, or turbine housing 65 .
- the turbine housing 65 remains stationary and provides support to the turbine rotor 57 as well as the stationary flow elements such as inlet guide vanes 70 , a shroud/diffuser cone 75 , and a central body 80 .
- the turbine housing 65 includes a scroll 85 that receives the flow of products of combustion from the combustor 55 .
- the shroud/diffuser cone 75 and scroll 85 direct the flow of products of combustion to the inlet guide vanes 70 that then direct the products of combustion into the turbine rotor 57 along the desired path.
- the flow of products of combustion After passing through the turbine rotor 57 , the flow of products of combustion enters a diffuser 90 made up of the diffuser cone 75 and the central body 80 .
- the diffuser walls, defined by the cone 75 and the central body 80 gradually diverge from one another to allow the exhaust gas exiting the turbine 35 to efficiently decelerate the flow as it is discharged from the engine 10 .
- another diffuser may be attached to the turbine 35 to further decelerate the flow.
- the compressor 45 includes the compressor rotor 56 and a second, or compressor housing 95 .
- the compressor housing 95 is directly connected to the turbine housing 65 to fix the position of the two components 65 , 95 relative to one another.
- the compressor housing 95 includes an inlet plenum 100 that receives atmospheric air for use in the engine 10 .
- the air is drawn in by operation of the compressor 45 and may be filtered before it enters the plenum 100 , as it enters the plenum 100 , or before it enters the compressor rotor 56 .
- the air enters the compressor 45 in a substantially axial direction (i.e., parallel to the rotational axis A-A of the compressor 45 ) and exits in a substantially 5 radial direction (i.e., centrifugal).
- the air collects in a volute chamber 105 defined within the compressor housing 95 and is directed from the compressor housing 95 to the recuperator 50 .
- the compressor rotor 56 is directly coupled to the turbine rotor 57 such that the two components 56 , 57 rotate in unison about the rotational axis A-A.
- a first high-speed bearing 1 10 supports the compressor end of the turbine-compressor rotor assembly 115 .
- the turbine-compressor rotor assembly 115 is supported in a cantilever fashion with all of its support points being on the air inlet side (i.e., adjacent the inlet plenum 100 ) of the compressor 45 .
- This arrangement supports the rotors 56 , 57 for rotation without subjecting the first high-speed bearing 110 (or any other bearings) to the high operating temperatures associated with the turbine 35 .
- the generator 20 also shown in FIG. 2 , includes a generator housing 120 that contains a stator and a generator rotor 125 (shown in FIG. 4 ).
- the rotor 125 is supported for rotation by two low-speed bearings (not shown) located within the generator housing 120 and positioned at either end of the rotor 125 .
- the generator rotor 125 includes a shaft 130 that extends out of the generator housing 120 and supports a ring gear 135 . While a synchronous generator that operates at 3600 RPM or 1800 RPM to output 60 Hz is preferred, other types of generators will also function with the invention. For example, a synchronous generator that operates at 3000 RPM or 1500 RPM to output 50 Hz will also work with the present invention.
- asynchronous or high-speed generators can also be driven by the present invention. These generators may operate at 4,000 RPM or higher in some cases.
- components other than generators e.g., pumps, compressors, conveyors, and the like
- Some of these components may operate in excess of 15,000 RPM.
- the gearbox 60 is positioned between the compressor 45 and the generator 20 and includes a gearbox housing 140 and a plurality of gears.
- the gearbox housing 140 attaches to the compressor housing 95 to align the components 95 , 140 and maintain their positions relative to one another.
- the generator housing 120 also attaches to the gearbox housing 140 to fix the positions of the stationary components of the engine 10 relative to one another. With all of the housings 65 , 95 , 120 , 140 attached, a relatively rigid structural backbone is established that supports the rotating components 56 , 57 , 125 in their desired locations.
- the relatively rigid housings 65 , 95 , 120 , 140 also reduces undesirable movement between components and/or vibration during engine operation.
- the gearbox housing 140 includes an adapter plate 145 that facilitates the attachment of the generator housing 120 and the gearbox housing 140 .
- the adapter plate 145 directly attaches to both the gearbox housing 140 and the generator housing 120 .
- the use of the adapter plate 145 allows for the use of a standard gearbox housing 140 with multiple generators 20 or other components.
- engines 10 of various sizes can use the same gearbox housing 140 with different adapter plates and generators.
- different speed engines e.g., 60 Hz vs. 50 Hz
- a standard gearbox housing 140 can be mated to a pump or compressor.
- the gearbox 60 includes a plurality of gears that are sized and arranged to step down a high input speed (e.g., 40,000 RPM or higher) to a low output speed (e.g., 15,000 RPM or lower to drive pumps or compressors and 3600 RPM or lower to drive synchronous generators).
- the gearbox 60 includes three planetary gears 150 , each supported by a planetary shaft 155 for rotation about a planetary axis B-B.
- the planetary axes B-B are spaced about 120 degrees apart around the rotational axis A-A and are spaced a parallel distance from the rotational axis A-A, thereby allowing a pinion gear 160 to engage all three planetary gears 150 simultaneously.
- Each planetary shaft 155 supports a drive gear 165 and is supported for rotation by two bearings 170 .
- Each of the drive gears 165 is sized and positioned to engage the ring gear 135 and drive the generator rotor 125 . As illustrated in FIG. 4 , the drive gears 165 are formed as part of the planetary shafts 155 . In other constructions, separate gears 165 attach to the shafts 155 in a known manner (e.g., pinned, shrunk on, welded, bolted, and the like).
- the gear ratio between the pinion gear 160 and each of the planetary gears 150 allows for the use of relatively low-speed bearings 170 (e.g., about 9,000 RPM) rather than high-speed bearings (e.g., 10,000 RPM or higher).
- relatively low-speed bearings 170 e.g., about 9,000 RPM
- high-speed bearings e.g., 10,000 RPM or higher.
- the size of the drive gears 165 and the ring gear 135 are chosen to assure that the generator rotor 125 operates at the proper speed when the turbine-compressor shaft assembly rotates at its operating speed.
- a quill shaft 175 extends from the gearbox 60 and forms at least a portion of the connection between the turbine-compressor rotor assembly 115 and the gearbox 60 .
- the quill shaft 175 is a substantially hollow member having a pinion end 180 and a diaphragm end 185 .
- the pinion gear 160 is positioned at the pinion end 180 of 5 the quill shaft 175 .
- the pinion gear 160 is formed as part of the quill shaft 175 .
- other constructions include a pinion gear 160 that is attached to the quill shaft 175 (e.g., shrunk-on, pinned, screwed, welded, and the like).
- the pinion gear 160 and the pinion end 180 of the quill shaft 175 are supported for rotation by the three planetary gears 150 . As such, no additional high-speed bearing is needed to support the pinion end 180 of the quill shaft 175 .
- the diaphragm end 185 includes a diaphragm portion 190 that forms an attachment surface 195 .
- the attachment surface 195 facilitates the attachment of the quill shaft 175 to a rotor flange 200 .
- the rotor flange 200 includes a planar surface 205 that engages the diaphragm 190 and a central bore that includes a tapered surface 210 .
- a second high-speed bearing 215 supports the rotor flange 200 for high-speed rotation.
- the various rotating components i.e., turbine rotor 57 , compressor rotor 56 , rotor flange 200 ) at least partially define a rotor train that is supported by the first and second high-speed bearings 110 , 215 .
- the bearings 110 , 215 are positioned to define a space between the bearings 110 , 215 and a space beyond the bearings 110 , 215 .
- a portion of the rotor train is positioned within the space between the bearings 110 , 215 and a portion is disposed in the space beyond the bearings 110 , 215 .
- a portion of the compressor rotor 56 and the entire turbine rotor 57 are disposed in the space beyond the bearings 110 , 215 .
- the compressor rotor 56 and the turbine rotor 57 are supported in a cantilever fashion with the turbine rotor 57 defining a free end 57 a.
- the rotor flange also defines a catcher 216 that includes a first diameter bore 217 and a second diameter bore 218 .
- the first diameter bore 217 is disposed adjacent the planar surface 205 and is sized to snuggly receive the diaphragm 190 .
- the first diameter acts as a guide to assure that the quill shaft 175 is aligned with the rotor flange 200 .
- the second diameter bore 218 is positioned adjacent the first diameter bore 217 and extends for the remaining length of the catcher 216 .
- the second diameter bore 218 is also larger than the first diameter bore 217 .
- a plurality of coupling members such as bolts 220 and shear pins 225 , extend between the diaphragm 190 and the flange 200 to allow for the transmission of torque therebetween.
- the bolts 220 and shear pins 225 are sized to transmit torque generated by the turbine rotor 57 to the generator rotor 125 .
- the pins 225 and bolts 220 are sized to fail at a predetermined torque level.
- the bolts 220 and pins 225 will fail in shear.
- the quill shaft 175 moves axially away from the rotor shaft 232 .
- the gearbox housing 140 limits the extent of this axial movement such that the diaphragm 190 remains within the axial extent of the catcher 216 .
- the second diameter bore 218 acts as a guide to the diaphragm 190 as the two separated portions of the rotor train decelerate at different rates.
- the second diameter bore 218 substantially maintains the alignment of the quill shaft 175 as it decelerates.
- the diaphragm 190 is flexible enough to allow slight misalignments between the rotor assembly 115 and the planetary gears 150 (i.e., angular misalignment) as well as slight axial displacements of the rotor flange 200 relative to the quill shaft 175 .
- the ability of the diaphragm 190 to flex allows the arrangement to tune the vibrations transmitted by the turbine-compressor rotor assembly 115 or the gearbox 160 .
- a tie-bolt 230 extends through the rotor flange 200 , a rotor shaft 232 , and the compressor rotor 56 to the turbine rotor 57 .
- a first end 235 of the tie-bolt 230 engages the turbine rotor 57 (e.g., threads, pins, shrink-fit, and the like) or an intermediate component such as a threaded sleeve.
- a second end 240 of the tie-bolt 230 shown in FIG. 5 , includes a threaded portion 245 that extends beyond the tapered surface 210 disposed within the rotor flange 200 .
- the rotor shaft fits between the compressor rotor and the rotor flange.
- a tapered nut 250 engages the threaded portion 245 and the tapered surface 210 within the rotor flange 200 to lock the rotor flange 200 , the rotor shaft 232 , the compressor rotor 56 , and the turbine rotor 57 for rotation, while pretensioning the tie-bolt 230 .
- the pretensioning of the tie bolt 230 applies a compressive force to the rotor flange 200 , the rotor shaft 232 , and the compressor rotor 56 .
- tie-bolt arrangement described herein is but one way of coupling the rotating elements (i.e., turbine rotor 57 , compressor rotor 56 , rotor shaft 232 , rotor flange 200 ) that define the rotor train.
- rotating elements i.e., turbine rotor 57 , compressor rotor 56 , rotor shaft 232 , rotor flange 200
- the invention should not be limited to the tie-bolt arrangement just described.
- the turbine-compressor rotor assembly 115 rotates at a high speed (e.g., typically in excess of 40,000 RPM).
- the quill shaft 175 also rotates at a high speed.
- the high-speed components are coupled to one another via the tie-bolt 230 and are completely supported for rotation by two high-speed bearings 110 , 215 and the planetary gears 150 of the gearbox 60 .
- the rotating quill shaft 175 drives the pinion gear 160 , which engages and drives the planetary gears 150 .
- the planetary gears 150 are sized relative to the pinion gear 160 to achieve a rotational speed that is low enough to allow for the use of low-speed bearings 170 to support the planetary gears 150 .
- the planetary gears 150 rotate at about 9,000 RPM with slower or higher speeds being possible.
- the drive gears 165 rotate with the planetary gears 150 and drive the ring gear 135 that is attached to the generator rotor 125 .
- the ring gear 135 is sized to rotate at the desired low speed (e.g., typically 3600 RPM or 1800 RPM for 60 Hz generators and 3000 RPM or 1500 RPM for 50 Hz generators) when the turbine-compressor rotor assembly 115 is rotating at the high speed.
- the ring gear 135 and the generator rotor 125 are supported for rotation by low-speed bearings.
- the present arrangement allows for the support and rotation of several high-speed and low-speed components using only two high-speed bearings 110 , 215 .
- the close coupling of the engine, the generator, and the gearbox allows the bearings 110 , 215 to support various other high-speed components.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
Description
- The present invention relates to a system and method for driving a low-speed component using a high-speed prime mover. More particularly, the present invention relates to a system and method for driving a low-speed component using a high-speed microturbine.
- Microturbine engines are relatively small and efficient sources of power. Microturbines can be used to generate electricity and/or to power auxiliary equipment such as pumps or compressors. When used to generate electricity, microturbines can be used independent of the utility grid or synchronized to the utility grid. In general, microturbine engines are limited to applications requiring 2 megawatts (MW) of power or less. However, some applications larger than 2 MWs may utilize a microturbine engine.
- Many microturbine engines include a turbine-compressor assembly that rotates at a high rate of speed. To generate electricity, the turbine-compressor assembly, or a separate turbine, is coupled to the generator, which also rotates at a high rate of speed. The generator output is then conditioned to produce a usable electrical current (e.g., 50 Hz or 60 Hz). In other constructions, a gearbox is positioned between the turbine and the generator to allow the generator to operate at a lower speed. However, due to the high speed of the turbine, the gearbox often requires several high-speed bearings to support the various gears. In addition, the dynamic and mechanical issues associated with the gearbox and turbine (e.g., vibration, imbalance, thrust loading, thermal expansion, and the like) can affect the operation of the other component. For example, a slight imbalance in the gearbox can produce a vibration that is transmitted to the turbine. The high speed of the turbine can act to increase the magnitude or the effect caused by the vibration. This can lead to undesirable operating conditions, system instability, and unwanted engine trips or shutdowns.
- The present invention generally provides a microturbine engine comprising a turbine including a first housing and a turbine rotor. The engine also includes a generator having a second housing and a generator rotor. The generator rotor is supported for low-speed rotation by a low-speed bearing. The engine also includes a gearbox having a third housing connected to the first housing and the second housing, a pinion gear, and a low-speed gear connected to the generator rotor and at least partially supported by the low-speed bearing. A shaft is connected to the turbine rotor and the pinion gear and a first high-speed bearing and a second high-speed bearing are positioned to support the turbine rotor and the shaft for high-speed rotation.
- In another aspect, the invention generally provides a microturbine engine including a turbine having a turbine housing and a turbine rotor. The engine also includes a compressor having a compressor housing coupled to the turbine housing and a compressor rotor coupled to the turbine rotor. A rotor flange is coupled to the compressor rotor such that the turbine rotor, the compressor rotor, and the rotor flange at least partially define a rotor train. A first high-speed bearing and a second high-speed bearing are coupled to the rotor train and at least partially support the rotor train for rotation. The first high-speed bearing and the second high-speed bearing are positioned to define a space between the bearings and a space that extends beyond the bearings. At least a portion of the rotor train is positioned within the space beyond the bearings to define a cantilever portion having a free end. The engine also includes a synchronous generator having a generator housing and a generator rotor. The generator rotor is supported for low-speed rotation by at least one low-speed bearing. The engine further includes a gearbox having a gearbox housing connected to the compressor housing and the generator housing. The gearbox includes a ring gear connected to the generator rotor, a plurality of planetary gears, and a pinion gear positioned to engage each of the planetary gears. A quill shaft is coupled to the rotor flange and the pinion gear such that the quill shaft is fully supported by the second high-speed bearing, which is coupled to the rotor flange, and the planetary gears.
- In yet another aspect, the present invention generally provides a method of coupling a rotating element of an engine that operates at a first speed to a driven component that operates at a second speed, the second speed slower than the first speed. The method includes coupling a shaft to the rotating element and supporting the rotating element and the shaft with a first high-speed bearing and a second high-speed bearing. The rotating element is supported such that at least a portion of the rotating element is disposed in a space between the bearings and at least a portion of the rotating element is disposed in a space beyond the bearings. The method also includes engaging a second end of the shaft with a plurality of planetary gears and supporting the driven component with at least one low-speed bearing. The method also includes coupling a low-speed gear to the driven component, the low-speed gear coupled to each of the planetary gears.
- The description particularly refers to the accompanying figures in which:
-
FIG. 1 is a perspective view of a portion of a microturbine engine; -
FIG. 2 is a sectional view of the turbine-compressor-generator portion of the engine ofFIG. 1 ; -
FIG. 3 is an enlarged view of the turbine-compressor and gearbox portion; -
FIG. 4 is an enlarged view of the gearbox portion of the engine ofFIG. 1 ; -
FIG. 5 is an enlarged sectional view of a quill shaft of the microturbine engine ofFIG. 1 ; and -
FIG. 6 is a perspective view of the quill shaft ofFIG. 4 . - Before any embodiments of the invention are explained, it is to be understood that the invention is not limited in its application to the details of construction and the arrangements of components set forth in the following description or illustrated in the following drawings. The invention is capable of other embodiments and of being practiced or of being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting. The use of “including,” “comprising,” or “having” and variations thereof is meant to encompass the items listed thereafter and equivalence thereof as well as additional items. The terms “connected,” “coupled,” and “mounted” and variations thereof are used broadly and encompass direct and indirect connections, couplings, and mountings. In addition, the terms “connected” and “coupled” and variations thereof are not restricted to physical or mechanical connections or couplings.
- With reference to
FIG. 1 , amicroturbine engine system 10 that includes aturbine section 15, agenerator section 20, and acontrol system 25 is illustrated. Theturbine section 15 includes aradial flow turbine 35, acompressor 45, arecuperator 50, and acombustor 55. Therecuperator 50 may be of the plate-fin variety with thecombustor 55 in the inlet manifold as disclosed in U.S. Pat. No. 5,450,724, the entire contents of which is incorporated herein by reference. - The
engine 10 includes a standard Brayton cycle combustion turbine with therecuperator 50 added to improve engine efficiency. The engine shown is a single-spool engine (one set of rotating elements). However, multi-spool engines are also contemplated by the invention. Thecompressor 45 is a centrifugal-type compressor having acompressor rotor 56 that rotates in response to operation of theturbine 35. Thecompressor 45 shown is a single-stage compressor. However, multi-stage compressors can be employed where a higher pressure ratio is desired. Alternatively, compressors of different designs (e.g., axial-flow compressors, reciprocating compressors, and the like) can be employed to supply compressed air to the engine. - The
turbine 35 is a radial flow single-stage turbine having aturbine rotor 57 directly coupled to thecompressor rotor 56. In other constructions, multi-stage turbines or other types of turbines may be employed. The coupledrotors turbine 35 and thecompressor 45 engage thegenerator section 20 through agearbox 60. - The
recuperator 50 includes a heat exchanger employed to transfer heat from a hot fluid to the relatively cool compressed air leaving thecompressor 45. Onesuitable recuperator 50 is described in U.S. Pat. No. 5,983,992 fully incorporated herein by reference. Therecuperator 50 includes a plurality of heat exchange cells stacked on top of one another to define flow paths therebetween. The cool compressed air flows within the individual cells, while a flow of hot exhaust gas passes between the heat exchange cells. - During operation of the
microturbine engine system 10, thecompressor rotor 56 rotates in response to rotation of theturbine rotor 57. Thecompressor 45 draws in atmospheric air and increases its pressure. The high-pressure air exits theair compressor 45 and flows to therecuperator 50. - The flow of compressed air, now preheated within the
recuperator 50, flows to thecombustor 55 as a flow of preheated air. The preheated air mixes with a supply of fuel within thecombustor 55 and is combusted to produce a flow of products of combustion. The use of arecuperator 50 to preheat the air allows for the use of less fuel to reach the desired temperature within the flow of products of combustion, thereby improving engine efficiency. - The flow of products of combustion enters the
turbine 35 and transfers thermal and kinetic energy to theturbine 35. The energy transfer results in rotation of theturbine rotor 57 and a drop in the temperature of the products of combustion. The energy transfer allows theturbine 35 to drive both thecompressor 45 and thegenerator 20. The products of combustion exit theturbine 35 as a first exhaust gas flow. - In constructions that employ a second turbine, the
first turbine 35 drives only the compressor, while the second turbine drives thegenerator 20 or any other device to be driven. The second turbine receives the first exhaust flow, rotates in response to the flow of exhaust gas therethrough, and discharges a second exhaust flow. - The first exhaust flow, or second exhaust flow in two turbine engines, enters the flow areas between the heat exchange cells of the
recuperator 50 and transfers excess heat energy to the flow of compressed air. The exhaust gas then exits therecuperator 50 and is discharged to the atmosphere, processed, or further used as desired (e.g., cogeneration using a second heat exchanger). - Turning to
FIGS. 2 and 3 , the portion of the engine ofFIG. 1 that includes thegenerator 20, theturbine 35, thecompressor 45, and thegearbox 60 is illustrated. The components are arranged and coupled to one another such that theturbine 35, thecompressor 45, and thegenerator 20 rotate on a common axis A-A. In other constructions, thegenerator 20 may be offset such that it rotates on an axis different from that of theturbine 35 and thecompressor 45. - The
turbine 35 is located at one end of theengine 10 and includes theturbine rotor 57 and a first, orturbine housing 65. Theturbine housing 65 remains stationary and provides support to theturbine rotor 57 as well as the stationary flow elements such asinlet guide vanes 70, a shroud/diffuser cone 75, and acentral body 80. Theturbine housing 65 includes ascroll 85 that receives the flow of products of combustion from thecombustor 55. The shroud/diffuser cone 75 and scroll 85 direct the flow of products of combustion to theinlet guide vanes 70 that then direct the products of combustion into theturbine rotor 57 along the desired path. After passing through theturbine rotor 57, the flow of products of combustion enters adiffuser 90 made up of thediffuser cone 75 and thecentral body 80. The diffuser walls, defined by thecone 75 and thecentral body 80, gradually diverge from one another to allow the exhaust gas exiting theturbine 35 to efficiently decelerate the flow as it is discharged from theengine 10. In other constructions another diffuser may be attached to theturbine 35 to further decelerate the flow. - The
compressor 45 includes thecompressor rotor 56 and a second, orcompressor housing 95. Thecompressor housing 95 is directly connected to theturbine housing 65 to fix the position of the twocomponents compressor housing 95 includes aninlet plenum 100 that receives atmospheric air for use in theengine 10. The air is drawn in by operation of thecompressor 45 and may be filtered before it enters theplenum 100, as it enters theplenum 100, or before it enters thecompressor rotor 56. The air enters thecompressor 45 in a substantially axial direction (i.e., parallel to the rotational axis A-A of the compressor 45) and exits in a substantially 5 radial direction (i.e., centrifugal). After passing through thecompressor rotor 56, the air collects in avolute chamber 105 defined within thecompressor housing 95 and is directed from thecompressor housing 95 to therecuperator 50. - The
compressor rotor 56 is directly coupled to theturbine rotor 57 such that the twocomponents speed bearing 1 10 supports the compressor end of the turbine-compressor rotor assembly 115. Thus, the turbine-compressor rotor assembly 115 is supported in a cantilever fashion with all of its support points being on the air inlet side (i.e., adjacent the inlet plenum 100) of thecompressor 45. This arrangement supports therotors turbine 35. - While many different types of bearing can be used (e.g., roller, ball, needle, journal, and the like), angular contact bearings are preferred. Angular contact bearings support the
rotors engine 10. Thus, the need for an independent thrust bearing is avoided. In addition, angular contact bearings provide increased efficiency over many other types of bearings. - The
generator 20, also shown inFIG. 2 , includes agenerator housing 120 that contains a stator and a generator rotor 125 (shown inFIG. 4 ). Therotor 125 is supported for rotation by two low-speed bearings (not shown) located within thegenerator housing 120 and positioned at either end of therotor 125. Thegenerator rotor 125 includes ashaft 130 that extends out of thegenerator housing 120 and supports aring gear 135. While a synchronous generator that operates at 3600 RPM or 1800 RPM tooutput 60 Hz is preferred, other types of generators will also function with the invention. For example, a synchronous generator that operates at 3000 RPM or 1500 RPM tooutput 50 Hz will also work with the present invention. In addition, asynchronous or high-speed generators (alternators) can also be driven by the present invention. These generators may operate at 4,000 RPM or higher in some cases. Furthermore, components other than generators (e.g., pumps, compressors, conveyors, and the like) can also be driven by the present invention. Some of these components may operate in excess of 15,000 RPM. - The
gearbox 60 is positioned between thecompressor 45 and thegenerator 20 and includes agearbox housing 140 and a plurality of gears. Thegearbox housing 140 attaches to thecompressor housing 95 to align thecomponents generator housing 120 also attaches to thegearbox housing 140 to fix the positions of the stationary components of theengine 10 relative to one another. With all of thehousings rotating components rigid housings - The
gearbox housing 140 includes anadapter plate 145 that facilitates the attachment of thegenerator housing 120 and thegearbox housing 140. Theadapter plate 145 directly attaches to both thegearbox housing 140 and thegenerator housing 120. The use of theadapter plate 145 allows for the use of astandard gearbox housing 140 withmultiple generators 20 or other components. For example,engines 10 of various sizes can use thesame gearbox housing 140 with different adapter plates and generators. Similarly, different speed engines (e.g., 60 Hz vs. 50 Hz) can use thesame gearbox housing 140 with different rotating components and generators. Furthermore, with a new adapter plate, astandard gearbox housing 140 can be mated to a pump or compressor. - The
gearbox 60, shown inFIG. 4 , includes a plurality of gears that are sized and arranged to step down a high input speed (e.g., 40,000 RPM or higher) to a low output speed (e.g., 15,000 RPM or lower to drive pumps or compressors and 3600 RPM or lower to drive synchronous generators). Thegearbox 60 includes threeplanetary gears 150, each supported by aplanetary shaft 155 for rotation about a planetary axis B-B. The planetary axes B-B are spaced about 120 degrees apart around the rotational axis A-A and are spaced a parallel distance from the rotational axis A-A, thereby allowing apinion gear 160 to engage all threeplanetary gears 150 simultaneously. Eachplanetary shaft 155 supports adrive gear 165 and is supported for rotation by twobearings 170. - Each of the drive gears 165 is sized and positioned to engage the
ring gear 135 and drive thegenerator rotor 125. As illustrated inFIG. 4 , the drive gears 165 are formed as part of theplanetary shafts 155. In other constructions,separate gears 165 attach to theshafts 155 in a known manner (e.g., pinned, shrunk on, welded, bolted, and the like). - The gear ratio between the
pinion gear 160 and each of theplanetary gears 150 allows for the use of relatively low-speed bearings 170 (e.g., about 9,000 RPM) rather than high-speed bearings (e.g., 10,000 RPM or higher). In addition, the size of the drive gears 165 and thering gear 135 are chosen to assure that thegenerator rotor 125 operates at the proper speed when the turbine-compressor shaft assembly rotates at its operating speed. - A
quill shaft 175, shown inFIGS. 4-6 , extends from thegearbox 60 and forms at least a portion of the connection between the turbine-compressor rotor assembly 115 and thegearbox 60. Thequill shaft 175 is a substantially hollow member having apinion end 180 and adiaphragm end 185. Thepinion gear 160 is positioned at thepinion end 180 of 5 thequill shaft 175. In most constructions, thepinion gear 160 is formed as part of thequill shaft 175. However, other constructions include apinion gear 160 that is attached to the quill shaft 175 (e.g., shrunk-on, pinned, screwed, welded, and the like). Thepinion gear 160 and thepinion end 180 of thequill shaft 175 are supported for rotation by the threeplanetary gears 150. As such, no additional high-speed bearing is needed to support thepinion end 180 of thequill shaft 175. - The
diaphragm end 185 includes adiaphragm portion 190 that forms anattachment surface 195. Theattachment surface 195 facilitates the attachment of thequill shaft 175 to arotor flange 200. - The
rotor flange 200 includes aplanar surface 205 that engages thediaphragm 190 and a central bore that includes atapered surface 210. A second high-speed bearing 215 supports therotor flange 200 for high-speed rotation. The various rotating components (i.e.,turbine rotor 57,compressor rotor 56, rotor flange 200) at least partially define a rotor train that is supported by the first and second high-speed bearings bearings bearings bearings bearings bearings compressor rotor 56 and theentire turbine rotor 57 are disposed in the space beyond thebearings compressor rotor 56 and theturbine rotor 57 are supported in a cantilever fashion with theturbine rotor 57 defining afree end 57 a. - The rotor flange also defines a
catcher 216 that includes a first diameter bore 217 and a second diameter bore 218. The first diameter bore 217 is disposed adjacent theplanar surface 205 and is sized to snuggly receive thediaphragm 190. Thus, the first diameter acts as a guide to assure that thequill shaft 175 is aligned with therotor flange 200. The second diameter bore 218 is positioned adjacent the first diameter bore 217 and extends for the remaining length of thecatcher 216. The second diameter bore 218 is also larger than thefirst diameter bore 217. - To connect the
diaphragm 190 to therotor flange 200, a plurality of coupling members, such asbolts 220 andshear pins 225, extend between thediaphragm 190 and theflange 200 to allow for the transmission of torque therebetween. Thebolts 220 andshear pins 225 are sized to transmit torque generated by theturbine rotor 57 to thegenerator rotor 125. To protect theengine 10 from damage caused by high-torque transients that may periodically arise, thepins 225 andbolts 220 are sized to fail at a predetermined torque level. Thus, if the torque between thequill shaft 175 and thecompressor shaft 56 exceeds that predetermined level, thebolts 220 and pins 225 will fail in shear. Generally, following the shear failure of thebolts 220 and pins 225 thequill shaft 175 moves axially away from therotor shaft 232. Thegearbox housing 140 limits the extent of this axial movement such that thediaphragm 190 remains within the axial extent of thecatcher 216. The second diameter bore 218 acts as a guide to thediaphragm 190 as the two separated portions of the rotor train decelerate at different rates. Thus, the second diameter bore 218 substantially maintains the alignment of thequill shaft 175 as it decelerates. - The
diaphragm 190 is flexible enough to allow slight misalignments between therotor assembly 115 and the planetary gears 150 (i.e., angular misalignment) as well as slight axial displacements of therotor flange 200 relative to thequill shaft 175. In addition, the ability of thediaphragm 190 to flex allows the arrangement to tune the vibrations transmitted by the turbine-compressor rotor assembly 115 or thegearbox 160. - A tie-
bolt 230 extends through therotor flange 200, arotor shaft 232, and thecompressor rotor 56 to theturbine rotor 57. Afirst end 235 of the tie-bolt 230 engages the turbine rotor 57 (e.g., threads, pins, shrink-fit, and the like) or an intermediate component such as a threaded sleeve. Asecond end 240 of the tie-bolt 230, shown inFIG. 5 , includes a threadedportion 245 that extends beyond the taperedsurface 210 disposed within therotor flange 200. The rotor shaft fits between the compressor rotor and the rotor flange. Atapered nut 250 engages the threadedportion 245 and thetapered surface 210 within therotor flange 200 to lock therotor flange 200, therotor shaft 232, thecompressor rotor 56, and theturbine rotor 57 for rotation, while pretensioning the tie-bolt 230. The pretensioning of thetie bolt 230 applies a compressive force to therotor flange 200, therotor shaft 232, and thecompressor rotor 56. It should be noted that the tie-bolt arrangement described herein is but one way of coupling the rotating elements (i.e.,turbine rotor 57,compressor rotor 56,rotor shaft 232, rotor flange 200) that define the rotor train. One of ordinary skill will realize that there are many other methods available to couple the rotating elements to one another. As such, the invention should not be limited to the tie-bolt arrangement just described. - In operation, the turbine-
compressor rotor assembly 115 rotates at a high speed (e.g., typically in excess of 40,000 RPM). Thequill shaft 175 also rotates at a high speed. The high-speed components are coupled to one another via the tie-bolt 230 and are completely supported for rotation by two high-speed bearings planetary gears 150 of thegearbox 60. - The
rotating quill shaft 175 drives thepinion gear 160, which engages and drives theplanetary gears 150. Theplanetary gears 150 are sized relative to thepinion gear 160 to achieve a rotational speed that is low enough to allow for the use of low-speed bearings 170 to support theplanetary gears 150. In preferred constructions, theplanetary gears 150 rotate at about 9,000 RPM with slower or higher speeds being possible. By properly sizing thegears gearbox 60 can be avoided. High-speed bearings are susceptible to wear and have a higher instance of failure due to the significantly increased stress levels under which they operate. In addition, high-speed bearings are much more sensitive to vibration and imbalance issues than are their low-speed counterparts. As such, it is desirable to avoid the use of high-speed bearings where possible. - The drive gears 165 rotate with the
planetary gears 150 and drive thering gear 135 that is attached to thegenerator rotor 125. Thering gear 135 is sized to rotate at the desired low speed (e.g., typically 3600 RPM or 1800 RPM for 60 Hz generators and 3000 RPM or 1500 RPM for 50 Hz generators) when the turbine-compressor rotor assembly 115 is rotating at the high speed. Thering gear 135 and thegenerator rotor 125 are supported for rotation by low-speed bearings. Thus, as one of ordinary skill will realize, the present arrangement allows for the support and rotation of several high-speed and low-speed components using only two high-speed bearings bearings - Although the invention has been described in detail with reference to certain preferred embodiments, variations and modifications exist within the scope and spirit of the invention as described and defined in the following claims.
Claims (41)
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/730,156 US6897578B1 (en) | 2003-12-08 | 2003-12-08 | Integrated microturbine gearbox generator assembly |
GB0424011A GB2409003A (en) | 2003-12-08 | 2004-10-28 | Bearing and shaft arrangement in microturbine and generator combination. |
FR0413083A FR2863310A1 (en) | 2003-12-08 | 2004-12-08 | MICROTURBINE ENGINE AND METHOD FOR DRIVING A ROTARY ELEMENT FOR A MOTOR |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/730,156 US6897578B1 (en) | 2003-12-08 | 2003-12-08 | Integrated microturbine gearbox generator assembly |
Publications (2)
Publication Number | Publication Date |
---|---|
US6897578B1 US6897578B1 (en) | 2005-05-24 |
US20050121916A1 true US20050121916A1 (en) | 2005-06-09 |
Family
ID=33518253
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/730,156 Expired - Fee Related US6897578B1 (en) | 2003-12-08 | 2003-12-08 | Integrated microturbine gearbox generator assembly |
Country Status (3)
Country | Link |
---|---|
US (1) | US6897578B1 (en) |
FR (1) | FR2863310A1 (en) |
GB (1) | GB2409003A (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050153812A1 (en) * | 2004-01-12 | 2005-07-14 | Locust, Usa, Inc. | Small-size traction drive transmission system for use in microturbine-powered aircraft |
US20060138779A1 (en) * | 2004-11-25 | 2006-06-29 | Snecma | Two-spool bypass turbojet with a rear electricity generator, and an air flow connection device and system |
US20070051846A1 (en) * | 2004-01-12 | 2007-03-08 | Box J W | Small-size high-speed transmission system for use in microturbine-powered aircraft |
US7575192B1 (en) | 2005-12-16 | 2009-08-18 | Locust Usa, Inc. | Transmission system for use in microturbine-powered applications |
US20100110053A1 (en) * | 2007-04-09 | 2010-05-06 | Hiromi Katoh | Liquid crystal display device |
CZ303864B6 (en) * | 2011-10-14 | 2013-05-29 | Majchráková@Viktória | Two-stage expansion turbine |
US20140239636A1 (en) * | 2013-02-26 | 2014-08-28 | Sumitomo(S.H.I.) Construction Machinery Co., Ltd. | Shovel and method of controlling shovel |
CN104213982A (en) * | 2013-05-31 | 2014-12-17 | 西安统领动力有限公司 | Novel back-to-back end-tooth transmission minisize gas turbine |
US20160281678A1 (en) * | 2013-11-15 | 2016-09-29 | University Of Washington Through Its Center For Commercialization | Energy recovery systems for ventilation exhausts and associated apparatuses and methods |
EP3266995A1 (en) * | 2016-07-05 | 2018-01-10 | Hamilton Sundstrand Corporation | Pinned mechanical fuse for engine motoring system |
US20230104669A1 (en) * | 2020-03-10 | 2023-04-06 | Safran Aircraft Engines | Turbomachine module equipped with an electric machine rotor |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7703551B2 (en) * | 2005-06-21 | 2010-04-27 | Bow River Tools And Services Ltd. | Fluid driven drilling motor and system |
AU2010247851B2 (en) | 2009-05-12 | 2014-07-24 | Icr Turbine Engine Corporation | Gas turbine energy storage and conversion system |
WO2011109514A1 (en) | 2010-03-02 | 2011-09-09 | Icr Turbine Engine Corporatin | Dispatchable power from a renewable energy facility |
US8984895B2 (en) | 2010-07-09 | 2015-03-24 | Icr Turbine Engine Corporation | Metallic ceramic spool for a gas turbine engine |
EP2612009B1 (en) | 2010-09-03 | 2020-04-22 | ICR Turbine Engine Corporatin | Gas turbine engine |
US9051873B2 (en) | 2011-05-20 | 2015-06-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine shaft attachment |
WO2013059586A1 (en) | 2011-10-20 | 2013-04-25 | Icr Turbine Engine Corporation | Multi-fuel service station |
US10094288B2 (en) | 2012-07-24 | 2018-10-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine volute attachment for a gas turbine engine |
CA2890703A1 (en) * | 2014-05-09 | 2015-11-09 | Stc Footwear Inc. | Footwear energy harvesting apparatus and method |
US10305350B2 (en) * | 2016-11-18 | 2019-05-28 | Cummins Power Generation Limited | Generator set integrated gearbox |
US10816086B2 (en) | 2017-08-14 | 2020-10-27 | General Electric Company | Power gearbox gear arrangement |
US10934931B2 (en) | 2018-06-22 | 2021-03-02 | Cummins Power Generation Limited | Integrated epicyclic gearbox and alternator |
US11661831B2 (en) * | 2020-10-23 | 2023-05-30 | Catalyst Energy Services LLC | System and method for a frac system |
Citations (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4043146A (en) * | 1974-07-27 | 1977-08-23 | Motoren- Und Turbinen-Union Muenchen Gmbh M.A.N. Maybach Mercedes-Benz | Shaft coupling |
US4075910A (en) * | 1976-08-20 | 1978-02-28 | Caterpillar Tractor Co. | Overload safety device for gas turbine engines |
US4086759A (en) * | 1976-10-01 | 1978-05-02 | Caterpillar Tractor Co. | Gas turbine shaft and bearing assembly |
US4105372A (en) * | 1975-01-31 | 1978-08-08 | Hitachi, Ltd. | Fluid rotary machine |
US4307629A (en) * | 1978-07-31 | 1981-12-29 | Moller Paul S | Torque converter |
US4649307A (en) * | 1984-04-12 | 1987-03-10 | Bech Jean A | Induction-type planetary reducing coupling for very high speed rotating machines |
US5261289A (en) * | 1991-04-16 | 1993-11-16 | Aisin Seiki Kabushiki Kaisha | High reduction gear assembly with lubrication |
US5526640A (en) * | 1994-05-16 | 1996-06-18 | Technical Directions, Inc. | Gas turbine engine including a bearing support tube cantilevered from a turbine nozzle wall |
US5553448A (en) * | 1992-05-14 | 1996-09-10 | General Electric Company | Intercooled gas turbine engine |
US6073857A (en) * | 1998-09-14 | 2000-06-13 | Fairlane Tool Company | Co-generator utilizing micro gas turbine engine |
US6170251B1 (en) * | 1997-12-19 | 2001-01-09 | Mark J. Skowronski | Single shaft microturbine power generating system including turbocompressor and auxiliary recuperator |
US6198174B1 (en) * | 1997-12-20 | 2001-03-06 | Alliedsignal Inc. | Microturbine power generating system |
US6294842B1 (en) * | 1997-12-19 | 2001-09-25 | Alliedsignal Inc. | Fog cycle for microturbine power generating system |
US6324828B1 (en) * | 1999-05-22 | 2001-12-04 | Rolls-Royce Plc | Gas turbine engine and a method of controlling a gas turbine engine |
US6352385B1 (en) * | 2000-07-31 | 2002-03-05 | General Electric Company | Mechanical coupling for cooperating rotatable members |
US6363706B1 (en) * | 1998-12-24 | 2002-04-02 | Alliedsignal | Apparatus and method to increase turbine power |
US6516618B1 (en) * | 1999-11-26 | 2003-02-11 | Rolls-Royce Deutschland Ltd & Co. Kg | Gas-turbine engine with a bearing chamber |
US6526757B2 (en) * | 2001-02-13 | 2003-03-04 | Robin Mackay | Multi pressure mode gas turbine |
US6546736B2 (en) * | 1998-09-25 | 2003-04-15 | Alm Development, Inc. | Method of operation of gas turbine engine |
US6571561B1 (en) * | 1998-10-28 | 2003-06-03 | Giovanni Aquino | Power generation system |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3632222A (en) * | 1970-10-21 | 1972-01-04 | Avco Corp | Damping means for differential gas turbine engine |
SE8101237L (en) * | 1980-06-26 | 1981-12-27 | Avco Corp | DRIVE SHAFT AND SET FOR MANUFACTURING THE SAME |
EP0539636B1 (en) * | 1991-10-31 | 1996-06-05 | Honda Giken Kogyo Kabushiki Kaisha | Gas turbine engine |
SE505609C2 (en) * | 1995-12-04 | 1997-09-22 | Voith Safeset Ab | COUPLING |
DE19630792A1 (en) * | 1996-04-04 | 1997-10-09 | Jung Nadine | Gas turbine unit |
AU2635897A (en) * | 1996-04-04 | 1997-10-29 | Nadine Jung | Gas-turbine unit |
US6134124A (en) * | 1999-05-12 | 2000-10-17 | Abb Power T&D Company Inc. | Universal distributed-resource interface |
SE520475C2 (en) * | 2001-11-19 | 2003-07-15 | Volvo Aero Corp | The gas turbine unit |
JP3735297B2 (en) * | 2001-12-18 | 2006-01-18 | 三菱重工業株式会社 | Planetary roller traction drive device |
US6769874B2 (en) * | 2002-03-15 | 2004-08-03 | Hamilton Sundstrand | Permanent magnet alternator for a gas turbine engine |
US6634853B1 (en) * | 2002-07-24 | 2003-10-21 | Sea Solar Power, Inc. | Compact centrifugal compressor |
-
2003
- 2003-12-08 US US10/730,156 patent/US6897578B1/en not_active Expired - Fee Related
-
2004
- 2004-10-28 GB GB0424011A patent/GB2409003A/en not_active Withdrawn
- 2004-12-08 FR FR0413083A patent/FR2863310A1/en active Pending
Patent Citations (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4043146A (en) * | 1974-07-27 | 1977-08-23 | Motoren- Und Turbinen-Union Muenchen Gmbh M.A.N. Maybach Mercedes-Benz | Shaft coupling |
US4105372A (en) * | 1975-01-31 | 1978-08-08 | Hitachi, Ltd. | Fluid rotary machine |
US4075910A (en) * | 1976-08-20 | 1978-02-28 | Caterpillar Tractor Co. | Overload safety device for gas turbine engines |
US4086759A (en) * | 1976-10-01 | 1978-05-02 | Caterpillar Tractor Co. | Gas turbine shaft and bearing assembly |
US4307629A (en) * | 1978-07-31 | 1981-12-29 | Moller Paul S | Torque converter |
US4649307A (en) * | 1984-04-12 | 1987-03-10 | Bech Jean A | Induction-type planetary reducing coupling for very high speed rotating machines |
US5261289A (en) * | 1991-04-16 | 1993-11-16 | Aisin Seiki Kabushiki Kaisha | High reduction gear assembly with lubrication |
US5553448A (en) * | 1992-05-14 | 1996-09-10 | General Electric Company | Intercooled gas turbine engine |
US5526640A (en) * | 1994-05-16 | 1996-06-18 | Technical Directions, Inc. | Gas turbine engine including a bearing support tube cantilevered from a turbine nozzle wall |
US6170251B1 (en) * | 1997-12-19 | 2001-01-09 | Mark J. Skowronski | Single shaft microturbine power generating system including turbocompressor and auxiliary recuperator |
US6294842B1 (en) * | 1997-12-19 | 2001-09-25 | Alliedsignal Inc. | Fog cycle for microturbine power generating system |
US6198174B1 (en) * | 1997-12-20 | 2001-03-06 | Alliedsignal Inc. | Microturbine power generating system |
US6307278B1 (en) * | 1997-12-20 | 2001-10-23 | Honeywell Power Systems Inc. | Microturbine power generating system |
US6073857A (en) * | 1998-09-14 | 2000-06-13 | Fairlane Tool Company | Co-generator utilizing micro gas turbine engine |
US6546736B2 (en) * | 1998-09-25 | 2003-04-15 | Alm Development, Inc. | Method of operation of gas turbine engine |
US6571561B1 (en) * | 1998-10-28 | 2003-06-03 | Giovanni Aquino | Power generation system |
US6363706B1 (en) * | 1998-12-24 | 2002-04-02 | Alliedsignal | Apparatus and method to increase turbine power |
US6324828B1 (en) * | 1999-05-22 | 2001-12-04 | Rolls-Royce Plc | Gas turbine engine and a method of controlling a gas turbine engine |
US6516618B1 (en) * | 1999-11-26 | 2003-02-11 | Rolls-Royce Deutschland Ltd & Co. Kg | Gas-turbine engine with a bearing chamber |
US6352385B1 (en) * | 2000-07-31 | 2002-03-05 | General Electric Company | Mechanical coupling for cooperating rotatable members |
US6526757B2 (en) * | 2001-02-13 | 2003-03-04 | Robin Mackay | Multi pressure mode gas turbine |
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20050153812A1 (en) * | 2004-01-12 | 2005-07-14 | Locust, Usa, Inc. | Small-size traction drive transmission system for use in microturbine-powered aircraft |
US20070051846A1 (en) * | 2004-01-12 | 2007-03-08 | Box J W | Small-size high-speed transmission system for use in microturbine-powered aircraft |
US7481396B2 (en) | 2004-01-12 | 2009-01-27 | Locust, Usa, Inc. | Small-size high-speed transmission system for use in microturbine-powered aircraft |
US20060138779A1 (en) * | 2004-11-25 | 2006-06-29 | Snecma | Two-spool bypass turbojet with a rear electricity generator, and an air flow connection device and system |
US7372175B2 (en) * | 2004-11-25 | 2008-05-13 | Snecma | Two-spool bypass turbojet with a rear electricity generator, and an air flow connection device and system |
US7575192B1 (en) | 2005-12-16 | 2009-08-18 | Locust Usa, Inc. | Transmission system for use in microturbine-powered applications |
US20100110053A1 (en) * | 2007-04-09 | 2010-05-06 | Hiromi Katoh | Liquid crystal display device |
CZ303864B6 (en) * | 2011-10-14 | 2013-05-29 | Majchráková@Viktória | Two-stage expansion turbine |
US20140239636A1 (en) * | 2013-02-26 | 2014-08-28 | Sumitomo(S.H.I.) Construction Machinery Co., Ltd. | Shovel and method of controlling shovel |
US9407174B2 (en) * | 2013-02-26 | 2016-08-02 | Sumitomo(S.H.I.) Construction Machinery Co., Ltd. | Shovel and method of controlling shovel |
CN104213982A (en) * | 2013-05-31 | 2014-12-17 | 西安统领动力有限公司 | Novel back-to-back end-tooth transmission minisize gas turbine |
US20160281678A1 (en) * | 2013-11-15 | 2016-09-29 | University Of Washington Through Its Center For Commercialization | Energy recovery systems for ventilation exhausts and associated apparatuses and methods |
EP3266995A1 (en) * | 2016-07-05 | 2018-01-10 | Hamilton Sundstrand Corporation | Pinned mechanical fuse for engine motoring system |
US10422284B2 (en) | 2016-07-05 | 2019-09-24 | Hamilton Sundstrand Corporation | Pinned mechanical fuse for engine motoring system |
US11536199B2 (en) | 2016-07-05 | 2022-12-27 | Hamilton Sundstrand Corporation | Method for manufacturing a motoring system for a gas turbine engine |
US20230104669A1 (en) * | 2020-03-10 | 2023-04-06 | Safran Aircraft Engines | Turbomachine module equipped with an electric machine rotor |
US11952904B2 (en) * | 2020-03-10 | 2024-04-09 | Safran Aircraft Engines | Turbomachine module equipped with an electric machine rotor |
Also Published As
Publication number | Publication date |
---|---|
FR2863310A1 (en) | 2005-06-10 |
US6897578B1 (en) | 2005-05-24 |
GB0424011D0 (en) | 2004-12-01 |
GB2409003A (en) | 2005-06-15 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US6897578B1 (en) | Integrated microturbine gearbox generator assembly | |
US10174630B2 (en) | Gas turbine in mechanical drive applications and operating methods | |
US7065954B2 (en) | Turbine, particularly useful for small aircraft | |
US20090211260A1 (en) | Multi-Spool Intercooled Recuperated Gas Turbine | |
JP6263170B2 (en) | Combination of two gas turbines to drive a load | |
EP2395202A2 (en) | A mounting assembly for a gearbox of gas turbine engine | |
US11970947B2 (en) | Power generation system | |
US20230121431A1 (en) | Gas turbine propulsion system | |
US10774746B2 (en) | Systems and methods for cooling components of a gas turbine | |
EP3699414A1 (en) | Gas turbine engine with accessory gearbox | |
CN112780410A (en) | Compact type turbine compressor structure | |
EP4173955A1 (en) | Cabin blower system |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: INGERSOLL-RAND ENERGY SYSTEMS CORPORATION, NEW HAM Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:OLSEN, ANDREW J.;CHILD, MALCOLM S.;SANDOE, ERNEST J.;REEL/FRAME:014786/0594;SIGNING DATES FROM 20031204 TO 20031205 |
|
AS | Assignment |
Owner name: SOUTHERN CALIFORNIA GAS COMPANY, CALIFORNIA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:INGERSOLL-RAND ENERGY SYSTEMS CORPORATION;REEL/FRAME:020279/0715 Effective date: 20071220 |
|
REMI | Maintenance fee reminder mailed | ||
FPAY | Fee payment |
Year of fee payment: 4 |
|
SULP | Surcharge for late payment | ||
FPAY | Fee payment |
Year of fee payment: 8 |
|
AS | Assignment |
Owner name: FLEXENERGY ENERGY SYSTEMS, INC., CALIFORNIA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SOUTHERN CALIFORNIA GAS COMPANY;REEL/FRAME:033132/0476 Effective date: 20121001 |
|
REMI | Maintenance fee reminder mailed | ||
LAPS | Lapse for failure to pay maintenance fees | ||
STCH | Information on status: patent discontinuation |
Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362 |
|
FP | Lapsed due to failure to pay maintenance fee |
Effective date: 20170524 |