US20170114664A1 - Torsional damping for gas turbine engines - Google Patents
Torsional damping for gas turbine engines Download PDFInfo
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- US20170114664A1 US20170114664A1 US14/920,993 US201514920993A US2017114664A1 US 20170114664 A1 US20170114664 A1 US 20170114664A1 US 201514920993 A US201514920993 A US 201514920993A US 2017114664 A1 US2017114664 A1 US 2017114664A1
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- generator
- damper
- torsional
- gas turbine
- electrical
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 43
- 239000000446 fuel Substances 0.000 claims abstract description 18
- 230000010355 oscillation Effects 0.000 claims abstract description 16
- 230000003993 interaction Effects 0.000 claims description 11
- 230000003247 decreasing effect Effects 0.000 claims description 6
- 238000004146 energy storage Methods 0.000 claims description 6
- 238000004804 winding Methods 0.000 claims description 6
- 239000007789 gas Substances 0.000 description 48
- 238000000034 method Methods 0.000 description 22
- 238000010586 diagram Methods 0.000 description 12
- 239000000567 combustion gas Substances 0.000 description 5
- 230000005284 excitation Effects 0.000 description 5
- 239000012530 fluid Substances 0.000 description 4
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000013017 mechanical damping Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
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- 230000005540 biological transmission Effects 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000037361 pathway Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/026—Shaft to shaft connections
-
- 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
- F01D25/04—Antivibration arrangements
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D7/00—Controlling wind motors
- F03D7/02—Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor
- F03D7/0296—Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor to prevent, counteract or reduce noise emissions
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/10—Suppression of vibrations in rotating systems by making use of members moving with the system
- F16F15/16—Suppression of vibrations in rotating systems by making use of members moving with the system using a fluid or pasty material
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- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/14—Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
-
- 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
- F02C7/22—Fuel supply systems
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2240/35—Combustors or associated equipment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
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- 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
- H02K7/003—Couplings; Details of shafts
-
- 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
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- 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
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Abstract
The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
Description
- The present application relates generally to gas turbine engines and more particularly to a torsional damper and torsional damping control to protect gas turbine engines from torsional interaction.
- A gas turbine engine generally includes, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air enters an inlet of the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section. Fuel is mixed with the compressed air and burned within the combustion section to provide combustion gases. The combustion gases are routed from the combustion section through a hot gas path defined within the turbine section and then exhausted from the turbine section via the exhaust section.
- In particular configurations, the turbine section includes, in serial flow order, a high pressure (HP) turbine and a low pressure (LP) turbine. The HP turbine and the LP turbine each include various rotatable turbine components such as turbine rotor blades, rotor disks and retainers, and various stationary turbine components such as stator vanes or nozzles, turbine shrouds and engine frames. The rotatable and the stationary turbine components at least partially define the hot gas path through the turbine section. As the combustion gases flow through the hot gas path, thermal energy is transferred from the combustion gases to the rotatable turbine components and the stationary turbine components.
- Gas turbine engines and other types of turbo-machinery are often used to drive loads such as electrical generators. Gas turbine engines and other large drive train systems have a moment of inertia, a torsional stiffness, and natural damping. The low mechanical damping in high power trains can cause torsional interaction between power system components and the mechanical drive train. For example, if one of the natural frequencies of the mechanical drive train is excited to a torsional resonance, the resulting alternating mechanical torque can reach values that can damage or cause fatigue in components of the rotor shaft system.
- Thus, a system and method of operating a gas turbine engine or similar machinery so as to provide improved torsional damping would be welcomed in the art.
- Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.
- In accordance with one aspect of the present disclosure, a gas turbine engine assembly is disclosed. The gas turbine engine assembly includes a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine (e.g. high- and low-pressure turbines) coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to a shaft system of the turbine (e.g. any one of or combination of a high pressure shaft system, a low pressure shaft system, or an intermediate shaft system) via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations on the shaft system of the generator, e.g. caused by negative damping and/or forced excitations. Moreover, the controller is configured to provide additional damping control to the generator.
- In one embodiment, the torsional damper may include at least one of a mechanical damper or an electrical damper. For example, in particular embodiments, the mechanical damper may include a viscous damper. More specifically, the viscous damper may be positioned circumferentially around the shaft of the generator.
- In certain embodiments, the gas turbine engine assembly may also include a power converter having one or more electrical circuits. Thus, in such embodiments, the electrical damper may include a resistor integrated into one of the electrical circuits of the power converter. In addition, in certain embodiments, the controller may be configured to control the resistor so as to prohibit the generator from having a constant power load at frequencies of torsional interaction.
- In another embodiment, the gas turbine engine assembly may include a power bus damper configured to prohibit the generator from having a constant power load at frequencies of torsional interaction. More specifically, in certain embodiments, the power bus damper may include at least one of an active load, a controlled resistive load, an energy storage device, or similar.
- In further embodiments, the controller may be configured to control a power factor of the generator so as to provide torsional damping of the generator by decreasing the power factor and creating losses internal to windings of the generator.
- In additional embodiments, the torsional damper may be configured to reduce the oscillating torque between the generator and the turbine.
- In another aspect, the present disclosure is directed to an electrical power system. The electrical power system includes a first inertia system connected to a second inertia system via a shaft. Further, the first inertia system is larger than the second inertia system. In addition, the second inertia system may include a negative ratio of delta torque and delta speed. Thus, the electrical power system also includes a torsional damper configured to dampen torsional oscillations between the first and second inertia systems, e.g. caused by negative damping and/or forced excitations.
- In yet another aspect, the present disclosure is directed to a method of operating a gas turbine engine assembly. The method includes pressurizing air via a compressor of the assembly. The method also includes providing the pressurized air from the compressor to a combustion chamber. Still another step includes injecting fuel into the pressurized air within the combustion chamber and igniting the fuel so as to raise a temperature and energy level of the pressurized air. The method further includes providing combustion products from the combustion chamber to a turbine coupled to a generator of the assembly. In addition, the method includes damping torsional oscillations of a shaft system of the generator via a torsional damper and additional damping provided by a generator controller.
- In one embodiment, the step of damping torsional oscillations of the shaft system of the generator via the torsional damper may further include providing at least one of a mechanical damper or an electrical damper. More specifically, in certain embodiments, the step of damping torsional oscillations of the shaft system of the generator may include positioning the mechanical damper circumferentially around the shaft.
- In another embodiment, the method may include integrating the electrical damper into a power converter of the generator. More specifically, in such an embodiment, the electrical damper may include a resistor. For example, in certain embodiments, the method may include controlling, via the controller, the resistor so as to prohibit the generator from having a constant power load at frequencies of torsional interaction.
- In additional embodiments, the method may include operatively coupling a power bus damper with the power converter and controlling the power bus damper so as to prohibit the generator from having a constant power load. More specifically, in such embodiments, the power bus damper may include at least one of an active load, a controlled resistive load, an energy storage device, or similar.
- In yet another embodiment, the method may include controlling a power factor of the generator so as to provide torsional damping of the generator by decreasing the power factor and creating losses internal to windings of the generator.
- These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.
- A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which:
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FIG. 1 illustrates a schematic cross-sectional view of a gas turbine engine according to the present disclosure; -
FIG. 2 illustrates a block diagram of one embodiment of a gas turbine engine assembly according to the present disclosure; -
FIG. 3 illustrates a block diagram of another embodiment of a gas turbine engine assembly according to the present disclosure; -
FIG. 4 illustrates a block diagram of yet another embodiment of a gas turbine engine assembly according to the present disclosure; -
FIG. 5 illustrates a block diagram of one embodiment of a generator of a gas turbine engine assembly according to the present disclosure; -
FIG. 6 illustrates a block diagram of another embodiment of a gas turbine engine assembly according to the present disclosure; -
FIG. 7 illustrates a partial block diagram of one embodiment of a generator and a power converter of a gas turbine engine assembly according to the present disclosure; -
FIG. 8 illustrates a block diagram of one embodiment of an electrical damper of a gas turbine engine assembly according to the present disclosure; -
FIG. 9 illustrates a partial block diagram of another embodiment of a gas turbine engine assembly according to the present disclosure, particularly illustrating various embodiments of a power bus damper; -
FIG. 10 illustrates a block diagram of one embodiment of an electrical power system according to the present disclosure; and -
FIG. 11 illustrates a flow diagram of one embodiment of a method of operating a gas turbine engine assembly according to the present disclosure. - Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the invention. As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. The terms “upstream” and “downstream” refer to the relative flow direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the flow direction from which the fluid flows, and “downstream” refers to the flow direction to which the fluid flows.
- Further, as used herein, the terms “axial” or “axially” refer to a dimension along a longitudinal axis of an engine. The term “forward” used in conjunction with “axial” or “axially” refers to a direction toward the engine inlet, or a component being relatively closer to the engine inlet as compared to another component. The term “rear” used in conjunction with “axial” or “axially” refers to a direction toward the engine nozzle, or a component being relatively closer to the engine nozzle as compared to another component. The terms “radial” or “radially” refer to a dimension extending between a center longitudinal axis of the engine and an outer engine circumference.
- Generally, the present disclosure is directed to a gas turbine engine assembly having improved torsional damping. The gas turbine engine assembly generally includes a compressor, a combustion chamber, at least one turbine (e.g. a high- and low-pressure turbine) coupled to a generator, a torsional damper, and a controller configured to provide additional damping. As is generally understood, the combustion chamber is configured to receive pressurized air from the compressor, wherein fuel is injected into the pressurized air and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to a shaft system of the turbine via a shaft. Thus, the torsional damper (i.e. mechanical, electrical, and/or both) is configured to dampen torsional oscillations of the shaft system of the generator. In addition, the controller is configured to provide additional damping control to the generator.
- Thus, the present disclosure provides many advantages not present in the prior art. For example, the present disclosure provides a stable mechanical drive of a generator or motor for an aircraft power system as well as any other suitable electrical power system by reducing oscillating torque between the generator to the turbine (i.e. caused by negative damping and/or forced excitations). In addition, the system provides simpler analysis of the power system loads. Further, the torsional damping of the present disclosure is configured to smooth the transmission of torque to the turbine, thereby allowing overall turbine design requirements to be relaxed. Thus, the size, cost, and/or weight of the turbine thus may be reduced. Moreover, the gas turbine engine may be more reliable with longer component lifetime. In addition, the torsional damping features of the present disclosure may be original equipment or part of a retrofit.
- Referring now to the drawings in detail, wherein identical numerals indicate the same elements throughout the figures,
FIG. 1 illustrates an exemplary gas turbine engine 10 (high bypass type) according to one embodiment of the present disclosure. As shown, the illustratedgas turbine engine 10 has an axiallongitudinal centerline axis 12 therethrough for reference purposes. Further, thegas turbine engine 10 preferably includes a core gas turbine engine generally identified bynumeral 14 and afan section 16 positioned upstream thereof. Thecore engine 14 typically includes a generally tubularouter casing 18 that defines anannular inlet 20. Theouter casing 18 further encloses and supports abooster 22 for raising the pressure of the air that enterscore engine 14 to a first pressure level. A high pressure, multi-stage, axial-flow compressor 24 receives pressurized air from thebooster 22 and further increases the pressure of the air. The pressurized air flows to acombustor 26, where fuel is injected into the pressurized air stream and ignited to raise the temperature and energy level of the pressurized air. The high energy combustion products flow from thecombustor 26 to a first (high pressure) turbine 28 for driving thehigh pressure compressor 24 through a first (high pressure) driveshaft 30, and then to a second (low pressure)turbine 32 for driving thebooster 22 and thefan section 16 through a second (low pressure) driveshaft 34 that is coaxial with thefirst drive shaft 30. After driving each of theturbines 28 and 32, the combustion products leave thecore engine 14 through anexhaust nozzle 36 to provide at least a portion of the jet propulsive thrust of theengine 10. - The
fan section 16 includes a rotatable, axial-flow fan rotor 38 that is surrounded by anannular fan casing 40. It will be appreciated thatfan casing 40 is supported from thecore engine 14 by a plurality of substantially radially-extending, circumferentially-spaced outlet guide vanes 42. In this way, thefan casing 40 encloses thefan rotor 38 and thefan rotor blades 44. Thedownstream section 46 of thefan casing 40 extends over an outer portion of thecore engine 14 to define a secondary, or bypass,airflow conduit 48 that provides additional jet propulsive thrust. - From a flow standpoint, it will be appreciated that an initial airflow, represented by
arrow 50, enters thegas turbine engine 10 through aninlet 52 to thefan casing 40. The airflow passes through thefan blades 44 and splits into a first air flow (represented by arrow 54) that moves through theconduit 48 and a second air flow (represented by arrow 56) which enters thebooster 22. - The pressure of the
second airflow 56 is increased and enters thehigh pressure compressor 24, as represented byarrow 58. After mixing with fuel and being combusted in thecombustor 26, thecombustion products 60 exit thecombustor 26 and flow through the first turbine 28. Thecombustion products 60 then flow through thesecond turbine 32 and exit theexhaust nozzle 36 to provide at least a portion of the thrust for thegas turbine engine 10. - Still referring to
FIG. 1 , thecombustor 26 includes anannular combustion chamber 62 that is coaxial withlongitudinal centerline axis 12, as well as aninlet 64 and anoutlet 66. As noted above, thecombustor 26 receives an annular stream of pressurized air from a high pressurecompressor discharge outlet 69. A portion of this compressor discharge air (“CDP” air) flows into a mixer (not shown). Fuel is injected from afuel nozzle 100 to mix with the air and form a fuel-air mixture that is provided to thecombustion chamber 62 for combustion. Ignition of the fuel-air mixture is accomplished by a suitable igniter, and the resultingcombustion gases 60 flow in an axial direction toward and into an annular, firststage turbine nozzle 72. Thenozzle 72 is defined by an annular flow channel that includes a plurality of radially-extending, circumferentially-spacednozzle vanes 74 that turn the gases so that they flow angularly and impinge upon the first stage turbine blades of the first turbine 28. As shown inFIG. 1 , the first turbine 28 preferably rotates the high-pressure compressor 24 via thefirst drive shaft 30. The low-pressure turbine 32 preferably drives thebooster 24 and thefan rotor 38 via thesecond drive shaft 34. - The
combustion chamber 62 is housed within engineouter casing 18. Fuel is supplied into the combustion chamber by one or more fuel nozzles. Liquid fuel is transported through conduits or passageways within a stem of each fuel nozzle. Further, thegas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels. Moreover, thegas turbine engine 10 may have different configurations and may use other types of components in addition to those components shown. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together. - Referring now to
FIGS. 2-4 , various simplified, schematic views of a gasturbine engine assembly 100 according to the present disclosure is illustrated. As shown in the illustrated embodiments, the gasturbine engine assembly 100 generally includes acompressor 102, acombustion chamber 104, a high-pressure turbine 106 and a high-pressure shaft 110, a low-pressure turbine 108 and a low-pressure shaft 112, and various other optional components. For example, the gasturbine engine assembly 100 may also include agenerator 114 or a similar type of load. Thegenerator 114 may be any type of device for the generation of electrical power. More specifically, as shown inFIG. 5 , thegenerator 114 may include agenerator rotor 113 that rotates within agenerator stator 115. More specifically, rotation of therotor 113 is due to the interaction 13 between the windings and/or magnetic fields of thegenerator 114 which produces a torque around the rotor's axis. Further, thegenerator 114 may be driven by theturbines shafts - In addition, as shown in
FIGS. 6 and 7 , the gasturbine engine assembly 100 may also include apower converter 122 having one orelectrical circuits 127. Thepower converter 122 may include any suitable power converter. For example, thepower converter 122 generally includes circuitry for converting a variable frequency AC voltage from thegenerator 114 into a voltage that is supplied to power grid (not shown). Specifically, thepower converter 122 is selectively activated to produce an output voltage, which is the AC voltage supplied to power grid. Thus, thepower converter 122 may include various power switching devices such as, for example, insulated gate bipolar transistors (IGBTs), integrated gate-commutated thyristors (IGCTs), or any other suitable switching devices. - Referring now to
FIGS. 2-9 , the gasturbine engine assembly 100 also may include atorsional damper 116 configured to dampen torsional oscillations of thegenerator 114 and/or acontroller 120 configured to provide additional damping control to theengine 10. Thus, in certain embodiments, thetorsional damper 116 is configured to reduce the oscillating torque between thegenerator 114 and theturbine - More specifically, as shown in the illustrated embodiment of
FIGS. 2-5 , thetorsional damper 116 may be amechanical damper 117. In addition, as shown, themechanical damper 117 may be positioned circumferentially around theshaft 118, which operatively couples the low-pressure turbine 108 to thegenerator 114. Further, as shown inFIG. 2 , themechanical damper 117 may be configured at the front end of thegenerator 114. Alternatively, as shown inFIG. 3 , themechanical damper 117 may be configured at the rear end of thegenerator 114. In addition, themechanical damper 117 may be separate from the generator 114 (FIG. 2 ) or integral with the generator 114 (FIG. 5 ). Further, as shown inFIG. 2 , thetorsional damper 116 and thegenerator 114 may be mechanically connected to the low-pressure shaft system (i.e. the fan, booster, and/or low-pressure turbine 108). Alternatively, as shown inFIG. 4 , thetorsional damper 116 and thegenerator 114 may be mechanically connected to the high-pressure shaft system (i.e. thecompressor 102 and/or the high-pressure turbine 106). In still additional embodiments, thetorsional damper 116 may be connected to any other shaft system. - It should be understood that the
mechanical damper 117 may be any suitable mechanical damper now known or later developed in the art. For example, in one embodiment, themechanical damper 117 may include a viscous damper. As used herein, a viscous damper generally refers to a mechanical device, which resists motion via viscous friction. The resulting force is substantially proportional to the oscillating velocity, but acts in the opposite direction, thereby decreasing the oscillation and absorbing energy without resulting in steady state losses. - It should also be understood that, in addition to or in placement of the
mechanical damper 117, additional damping means may be used in theengine 10. For example, as shown inFIGS. 6-8 , thetorsional damper 116 may include anelectrical damper 124. More specifically, as shown, theelectrical damper 124 may be integrated into thepower converter 122 of theassembly 100. In certain embodiments, as shown inFIGS. 7 and 8 , theelectrical damper 124 may include one ormore resistors 125 integrated into one of theelectrical circuits 127 of thepower converter 122. Thus, in such an embodiment, thecontroller 120 may also be configured to control theresistor 125 so as to prohibit thegenerator 114 from having a constant power load, thereby providing torsional damping thereof. Accordingly, theelectrical damper 124 is configured to provide damping for forced excitations introduced to theassembly 100. - In another embodiment, as shown in
FIG. 9 , the gasturbine engine assembly 100 may include a powerbus damper component 126 configured to prohibit thegenerator 114 from having a constant power load. More specifically, as shown, the powerbus damper component 126 may include at least one of anactive load 128, a controlledresistive load 130, abus damper 132, or an energy storage device 134 (e.g. a battery, capacitor, or similar). Further, as shown, the power bus damper component(s) 126 is configured to receive a speed and/ortorque signal 136 from thegenerator 114 or thecontroller 120. Based on thesignal 136, thebus damper component 126 is configured to prevent the bus from having a constant power load separated from voltage control. Further, for generators having a power converter (as shown), the power factor can be reduced to increase generator losses at the required mechanical damping frequencies. Such operation does not result in steady state losses, but rather only losses required to damp torsional oscillations. - In further embodiments, the
controller 120 is configured to control a power factor of thegenerator 114 so as to provide torsional damping of thegenerator 114, e.g. by decreasing the power factor and creating losses internal to windings of thegenerator 114 and connecting cables. - Referring now to
FIG. 10 , it should be understood that the advantages described above may also be suitable for additional power systems, in addition to thegas turbine engine 10 of an aircraft power system as described herein. For example, additional electrical power systems that may utilize the torsional damping features of the present disclosure may include gas turbine engines, wind turbines, steam turbines, or any other suitable generator-driven system. For example, as shown inFIG. 10 , a schematic diagram of anelectrical power system 150 having improved torsional damping according to the present disclosure is illustrated. More specifically, as shown, theelectrical power system 150 includes afirst inertia system 152 connected to asecond inertia system 154 via ashaft 156. Further, as shown, thefirst inertia system 152 is larger than thesecond inertia system 154. For example, in certain embodiments, thefirst inertia system 152 may be a generator, whereas thesecond inertia system 154 may include a generator driver, including but not limited to a low-pressure shaft system, a high-pressure shaft system, an intermediate shaft system, one or more rotor blades (optionally coupled to a gearbox), or any other suitable generator-driving component. - Thus, the
electrical power system 150 may include atorsional damper 158 configured to dampen torsional oscillations between the first andsecond inertia systems second inertia system 154 may have a negative ratio of delta torque and delta speed, i.e. may have negative damping. Thus, thetorsional damper 158 may be configured to correct the negative damping of thesecond inertia system 154. Alternatively, thetorsional damper 158 may be configured to provide damping for forced excitations introduced to thesystems - In additional embodiments, the
electrical power system 150 includes acontroller 160 configured to provide additional damping control for the first andsecond inertia systems FIG. 11 , a flow diagram of one embodiment of amethod 200 of operating a gas turbine engine. As shown at 202, themethod 200 includes pressurizing air via acompressor 24 of thegas turbine engine 10. As shown at 204, themethod 200 includes providing the pressurized air to acombustion chamber 62 from thecompressor 24. As shown at 206, themethod 200 includes injecting fuel into pressurized air within thecombustion chamber 62 and igniting the fuel so as to raise a temperature and energy level of the pressurized air. As shown at 208, themethod 200 includes providing combustion products from thecombustion chamber 62 to the turbine (e.g.turbines 106, 108) coupled to agenerator 114. As shown at 210, themethod 200 also includes damping torsional oscillations of thegenerator 114 via atorsional damper 116 and additional damping provided by agenerator controller 120. - In one embodiment, the step of damping torsional oscillations of the
generator 114 via thetorsional damper 116 may further include providing at least one of amechanical damper 117 or anelectrical damper 124. More specifically, in certain embodiments, the step of damping torsional oscillations of thegenerator 114 via thetorsional damper 116 may include positioning themechanical damper 117 circumferentially around the shaft 118 (FIG. 2 ). - In another embodiment, as shown in
FIG. 7 , themethod 200 may include integrating theelectrical damper 124 into thepower converter 122. More specifically, as mentioned, theelectrical damper 124 may include aresistor 125. Thus, in such embodiments, themethod 200 may include controlling, via thecontroller 120, theresistor 125 so as to prohibit thegenerator 114 from having a constant power load at frequencies of torsional interaction. - In additional embodiments, the
method 200 may include operatively coupling apower bus damper 126 with thepower converter 122 and/or thecontroller 120. Thus, thepower bus damper 126 is configured to prohibit thegenerator 114 from having a constant power load. More specifically, as described herein, thepower bus damper 126 may include anactive load 128, a controlledresistive load 130, abus damper 132, anenergy storage device 134, or similar, or combinations thereof. - In yet another embodiment, the
method 200 may include controlling a power factor of thegenerator 114 so as to provide torsional damping of thegenerator 114, e.g. by decreasing the power factor and creating losses internal to windings of thegenerator 114 or connecting cables. - It should also be understood that although the use of the gas
turbine engine assembly 100 has been described herein, thetorsional damper 160 may be used with any type of turbo-machinery and the like. Thus, the combination of any or all of the damping components and/or features described herein can be used to provide positive generator damping, e.g. at specific frequencies, wide frequency ranges, and may be adjustable. - This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Claims (21)
1. A gas turbine engine assembly, comprising:
a compressor configured to increase pressure of incoming air;
a combustion chamber configured to receive a pressurized air stream from the compressor, wherein fuel is injected into the pressurized air stream and ignited so as to raise a temperature and energy level of the pressurized air;
a turbine operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber;
a generator coupled to a shaft system of the turbine via a shaft;
a mechanical torsional damper, integrated with the generator, configured to dampen torsional oscillations of the shaft system of the generator; and
a controller configured to provide additional damping control to the generator.
2. (canceled)
3. The gas turbine engine assembly of claim 1 , wherein the mechanical torsional damper comprises a viscous damper.
4. (canceled)
5. The gas turbine engine assembly of claim 2 , further comprising a power converter comprising one or more electrical circuits, wherein the electrical damper comprises a resistor integrated into one of the electrical circuits of the power converter.
6. The gas turbine engine assembly of claim 5 , wherein the controller is configured to control the resistor so as to prohibit the generator from having a constant power load at frequencies of torsional interaction.
7. The gas turbine engine assembly of claim 5 , further comprising a power bus damper configured to prohibit the generator from having a constant power load at frequencies of torsional interaction.
8. The gas turbine engine assembly of claim 7 , wherein the power bus damper comprises at least one of an active load, a controlled resistive load, or an energy storage device.
9. The gas turbine engine assembly of claim 1 , wherein the controller is configured to control a power factor of the generator so as to provide torsional damping of the generator by decreasing the power factor and creating losses internal to windings of the generator and connecting cables.
10. An electrical power system, comprising:
a first inertia system connected to a second inertia system via a shaft, the first inertia system being larger than the second inertia system, the second inertia system comprising a negative ratio of delta torque and delta speed; and
a torsional damper configured to dampen torsional oscillations between the first and second inertia systems.
11. The electrical power system of claim 10 , further comprising a controller configured to provide additional damping control for the first and second inertia systems.
12. The electrical power system of claim 11 , wherein the electrical power system comprises at least one of gas turbine engine, a wind turbine, or a steam turbine.
13. The electrical power system of claim 12 , wherein the first inertia system comprises a generator and the second inertia system comprises a generator driver, the generator driver comprising at least one of a low-pressure shaft system, a high-pressure shaft system, or one or more rotor blades.
14.-20. (canceled)
21. The electrical power system of claim 13 , wherein the torsional damper comprises at least one of a mechanical damper or an electrical damper.
22. The electrical power system of claim 21 , wherein the mechanical damper comprises a viscous damper.
23. The electrical power system of claim 22 , wherein the viscous damper is positioned circumferentially around the shaft.
24. The electrical power system of claim 23 , wherein the viscous damper is positioned circumferentially around the shaft.
25. The electrical power system of claim 13 , further comprising a power converter comprising one or more electrical circuits, wherein the electrical damper comprises a resistor integrated into one of the electrical circuits of the power converter.
26. The electrical power system of claim 25 , wherein the controller is configured to control the resistor so as to prohibit the generator from having a constant power load at frequencies of torsional interaction.
27. The electrical power system of claim 26 , further comprising a power bus damper configured to prohibit the generator from having a constant power load at frequencies of torsional interaction, wherein the power bus damper comprises at least one of an active load, a controlled resistive load, or an energy storage device.
Priority Applications (10)
Application Number | Priority Date | Filing Date | Title |
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US14/920,993 US20170114664A1 (en) | 2015-10-23 | 2015-10-23 | Torsional damping for gas turbine engines |
US15/018,966 US9938853B2 (en) | 2015-10-23 | 2016-02-09 | Torsional damping for gas turbine engines |
JP2016198602A JP6438926B2 (en) | 2015-10-23 | 2016-10-07 | Torsional damping for gas turbine engines |
CA2945248A CA2945248C (en) | 2015-10-23 | 2016-10-13 | Torsional damping for gas turbine engines |
CN201610913787.XA CN107013330B (en) | 2015-10-23 | 2016-10-20 | Gas turbine assembly and its operation method, electic power system |
EP16194769.2A EP3159573B1 (en) | 2015-10-23 | 2016-10-20 | Torsional damping for gas turbine engines |
BR102016024577-0A BR102016024577A2 (en) | 2015-10-23 | 2016-10-21 | GAS TURBINE ENGINE ASSEMBLY, ELECTRICAL POWER SYSTEM AND OPERATING METHOD FOR GAS TURBINE ENGINE ASSEMBLY |
US15/491,638 US11346243B2 (en) | 2015-10-23 | 2017-04-19 | Torsional damping for gas turbine engines |
US17/749,805 US11802492B2 (en) | 2015-10-23 | 2022-05-20 | Torsional damping for gas turbine engines |
US18/483,696 US20240044261A1 (en) | 2015-10-23 | 2023-10-10 | Torsional damping for gas turbine engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US14/920,993 US20170114664A1 (en) | 2015-10-23 | 2015-10-23 | Torsional damping for gas turbine engines |
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US15/018,966 Continuation US9938853B2 (en) | 2015-10-23 | 2016-02-09 | Torsional damping for gas turbine engines |
US15/491,638 Division US11346243B2 (en) | 2015-10-23 | 2017-04-19 | Torsional damping for gas turbine engines |
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US20170114664A1 true US20170114664A1 (en) | 2017-04-27 |
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US15/491,638 Active 2037-11-26 US11346243B2 (en) | 2015-10-23 | 2017-04-19 | Torsional damping for gas turbine engines |
US17/749,805 Active US11802492B2 (en) | 2015-10-23 | 2022-05-20 | Torsional damping for gas turbine engines |
US18/483,696 Pending US20240044261A1 (en) | 2015-10-23 | 2023-10-10 | Torsional damping for gas turbine engines |
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US15/491,638 Active 2037-11-26 US11346243B2 (en) | 2015-10-23 | 2017-04-19 | Torsional damping for gas turbine engines |
US17/749,805 Active US11802492B2 (en) | 2015-10-23 | 2022-05-20 | Torsional damping for gas turbine engines |
US18/483,696 Pending US20240044261A1 (en) | 2015-10-23 | 2023-10-10 | Torsional damping for gas turbine engines |
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US (4) | US20170114664A1 (en) |
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US20180278188A1 (en) * | 2017-03-23 | 2018-09-27 | Ge Aviation Systems, Llc | Torsional damping for generators |
US11097849B2 (en) | 2018-09-10 | 2021-08-24 | General Electric Company | Aircraft having an aft engine |
US11261787B2 (en) * | 2018-06-22 | 2022-03-01 | General Electric Company | Aircraft anti-icing system |
US11316458B2 (en) * | 2019-10-23 | 2022-04-26 | Rolls-Royce Plc | Turboelectric generator system |
US20220154588A1 (en) * | 2019-04-05 | 2022-05-19 | Nuovo Pignone Tecnologie - S.R.L. | Steam turbine with rotatable stator blades |
US11539316B2 (en) | 2019-07-30 | 2022-12-27 | General Electric Company | Active stability control of compression systems utilizing electric machines |
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US9938853B2 (en) | 2015-10-23 | 2018-04-10 | General Electric Company | Torsional damping for gas turbine engines |
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Also Published As
Publication number | Publication date |
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US20220282637A1 (en) | 2022-09-08 |
US11346243B2 (en) | 2022-05-31 |
US20240044261A1 (en) | 2024-02-08 |
US11802492B2 (en) | 2023-10-31 |
US20170222518A1 (en) | 2017-08-03 |
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