WO2017189566A2 - Moteur à turbine à gaz industriel à deux bobines pourvu d'aubes de guidage d'entrée variables - Google Patents

Moteur à turbine à gaz industriel à deux bobines pourvu d'aubes de guidage d'entrée variables Download PDF

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Publication number
WO2017189566A2
WO2017189566A2 PCT/US2017/029401 US2017029401W WO2017189566A2 WO 2017189566 A2 WO2017189566 A2 WO 2017189566A2 US 2017029401 W US2017029401 W US 2017029401W WO 2017189566 A2 WO2017189566 A2 WO 2017189566A2
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WO
WIPO (PCT)
Prior art keywords
airfoil
turbine
spool
inlet guide
variable inlet
Prior art date
Application number
PCT/US2017/029401
Other languages
English (en)
Other versions
WO2017189566A3 (fr
Inventor
Stephen E. MURRAY
Joseph D. BROSTMEYER
Russell B. Jones
Barry J. BROWN
Justin T. CEJKA
Original Assignee
Florida Turbine Technologies, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US15/137,248 external-priority patent/US20170342854A1/en
Priority claimed from US15/174,051 external-priority patent/US10208619B2/en
Application filed by Florida Turbine Technologies, Inc. filed Critical Florida Turbine Technologies, Inc.
Priority to KR1020187034161A priority Critical patent/KR20190003626A/ko
Priority to EP17721939.1A priority patent/EP3449100A2/fr
Priority to CN201780038624.4A priority patent/CN109415948A/zh
Publication of WO2017189566A2 publication Critical patent/WO2017189566A2/fr
Publication of WO2017189566A3 publication Critical patent/WO2017189566A3/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • 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
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/48—Control of fuel supply conjointly with another control of the plant
    • F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
    • F02C9/54—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by throttling the working fluid, by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • 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
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator
    • 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
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • 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
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

Definitions

  • the present invention relates generally to a twin spool industrial gas turbine engine, and more specifically to an industrial gas turbine engine with a second spool having a variable inlet guide vane assembly for the low pressure turbine.
  • a large frame, heavy duty industrial gas turbine engine is used in a power plant to drive an electric generator and produce electrical power.
  • the electrical power grid operates at 60 Hertz and thus the industrial engine drives a 60 Hertz electric generator that operates at 3,600 rpm.
  • the engine directly drives the electric generator without using a gear box in order to increase efficiency of the engine, since a gear box would reduce the efficiency around 1%.
  • a typical industrial gas turbine engine of 300MW is designed to operate at the 3,600 rpm to be in synchronous speed with the 60 Hertz electric generator.
  • the engine is designed to produce the largest mass flow through the engine and thus produce the maximum power.
  • the industrial engine is designed for what is referred to as an ISO day, which for example would be at a certain outside air or ambient temperature of 60 degrees F.
  • variable angle vanes are used to vary the mass flow through compressor and turbine passages. Compared to fixed airfoils that have integral outer and inner end walls, variable vanes have leakage areas between the airfoil and the end walls. These leakage paths create undesirable aerodynamic losses. The larger the desired swing angle of the airfoil, the bigger the challenge to minimize these gaps.
  • the cycle benefit for having an adjustable vane throat greatly outweighs the leakage debits.
  • Variable inlet guide vanes are used in both a compressor and a turbine.
  • the structure for a turbine variable inlet guide vane is different than for the compressor variable inlet guide vane.
  • the flow path is decreasing in height as the compressed air passing through the stages of the compressor increases in pressure.
  • the radial or spanwise height of the trailing edge of the vane decreases in the flow direction of the compressed air. This is the opposite in a turbine where the compressed gas is increasing or expanding in the flow direction.
  • the spanwise height of the vane at the trailing edge is increasing in height.
  • aerodynamic forces acting on the airfoil are considered to select the optimum rotation axis.
  • the airfoil center of pressure is the location where the moments are zero.
  • the rotation axis placed through the center of pressure yields no additional forces over friction to articulate the vane. This center of pressure can vary on position when the stagger angle of the airfoil is changed.
  • a large frame heavy duty industrial gas turbine engine capable of operating within a broad range of outside air temperature while still maintaining full power output in order to drive an electric generator as full power.
  • the industrial gas turbine engine includes a high spool with a separately operable low spool or turbocharger that produces compressed air supplied to the high pressure compressor of the high spool.
  • the high spool includes a high pressure compressor, a combustor, and a high pressure turbine that directly drives an electric generator and operates continuously at a speed synchronous with the local electrical power grid, such as 60 Hertz or 50 hertz, to produce electrical power.
  • the low spool or turbocharger includes a low pressure turbine that drives a low pressure compressor.
  • the HPC, the LPT, and the LPC each includes a variable inlet guide vane assembly so that the speed of the electric generator can be operated continuously at the synchronous speed under various ambient temperatures by regulating one or more of the variable inlet guide vane assemblies.
  • the low spool or turbocharger is designed to operate at a higher speed than the normal operating speed of the engine at the designed for ambient temperature conditions. For a hot day (above the normal ambient temperature design condition), the low spool will need to operate at a higher speed in order to supply a higher mass flow to the high spool in order to operate at the synchronous speed of the generator during the hot day conditions.
  • the industrial engine of the present invention is capable of operating at twice the power output as any known industrial gas turbine engine.
  • the largest known industrial engine for the 60 hertz market has a maximum power output of around 350 MW and for the 50 hertz market at around 500 MW.
  • the twin spool turbocharged industrial gas turbine engine of the present invention can produce in excess of 500 MW for the 60 hertz engine and in excess of 720 MW for the 50 hertz engine.
  • variable inlet guide assembly for a gas turbine engine, such as an industrial gas turbine engine having a low pressure turbine
  • the variable inlet guide vane assembly includes guide vanes having airfoils that extend between large diameter outer and inner buttons in which the airfoil trailing edge extends into the two buttons so that no gap is formed between the trailing edge and the turbine housing.
  • the airfoil has a center of rotation that is located aft or downstream from an aerodynamic center of pressure which will decrease any gap from forming in the movement of the airfoil from an open position to a closed position and thus increase a performance of the turbine.
  • a large frame heavy duty industrial gas turbine engine for electrical power production includes: a high spool with a high pressure compressor, a combustor, and a high pressure turbine; an electric generator directly driven by the high spool at a speed synchronous with a local electrical power grid to produce electrical power; a low spool with a low pressure turbine and a low pressure compressor, the low spool and the high spool being connected such that turbine exhaust from the high pressure turbine drives the low pressure turbine; a compressed air line connecting the low pressure compressor to the high pressure compressor to supply compressed air to the high pressure compressor; a first variable inlet guide vane assembly for the low pressure turbine; and a second variable inlet guide vane assembly for the low pressure compressor, the variable inlet guide vane assembly for the low pressure turbine regulating a power output to drive the low pressure compressor so
  • the large frame heavy duty industrial gas turbine engine further includes third variable inlet guide vane assembly for the high pressure compressor.
  • the low spool is designed to operate at a speed higher than required for a standard iso operating temperature so that the normal mass flow will flow through the engine at hot day conditions and drive the electric generator at full power.
  • the low spool does not rotate within the high spool.
  • the electric generator is a 60 hertz generator and the industrial gas turbine engine is capable of producing 500 MW.
  • the electric generator is a 50 hertz generator and the industrial gas turbine engine is capable of producing 720 MW.
  • a turbine with a variable inlet guide vane assembly for a gas turbine engine includes: a variable inlet guide vane located upstream in a flow direction of a rotor blade of the turbine, the variable inlet guide vane having an airfoil, an upper button, and a lower button, the airfoil extending between the upper button and the lower button, the airfoil having a leading edge, a trailing edge, an aerodynamic center of pressure, and a center of rotation, the center of rotation being located downstream in a flow direction of the aerodynamic center of pressure of the airfoil.
  • the trailing edge of the airfoil is located inward in an airfoil chordwise direction from an outer radius of the upper and lower buttons.
  • the trailing edge of the airfoil extends into each of the upper button and the lower button such that no gap is formed between the trailing edge of the airfoil and a static structure of the turbine (such as the turbine housing) in which leakage can flow.
  • an airfoil for a turbine variable inlet guide vane assembly includes: a leading edge, a trailing edge, an aerodynamic center of pressure, and a center of rotation, the airfoil center of rotation being aft of the airfoil aerodynamic center of pressure, the airfoil extending between the outer button and the inner button, and an outer radius of each of the inner and outer buttons being greater than a distance of the airfoil trailing edge from the airfoil center of rotation in a chordwise direction of the airfoil.
  • the outer radius of each of the inner and outer buttons is less than a distance of the airfoil leading edge from the airfoil center of rotation in a chordwise direction of the airfoil.
  • FIG. 1 shows a cross section view of a twin spool industrial gas turbine engine with variable inlet guide vanes according to the present invention
  • FIG. 2 shows the turbocharged industrial gas turbine engine of FIG. 1 in a combined cycle power plant with a HRSG
  • FIG. 3 shows an isometric view of a variable geometry vane with the rotational axis behind the airfoil center of pressure with the vane having three different positions according to the present invention
  • FIG. 4 shows a top view of two adjacent variable guide vanes in the open airfoil position, the nominal airfoil position, and the closed airfoil position of the present invention
  • FIG. 5 shows a side view of the turbine variable inlet guide vane with the outer diameter and the inner diameter gaps between the endwalls according to the present invention
  • FIG. 6 shows a close-up view of the guide vane airfoil and the upper button arrangement of the present invention.
  • FIG. 7 shows a close-up view of the guide vane airfoil and the lower button arrangement of the present invention.
  • the present invention is a twin spool industrial gas turbine engine 5 (referred to herein for simplicity as the engine 5) used for electrical power production where the engine 5 can operate at full power even on a hot day when the air temperature is well above the engine design temperature.
  • FIG. 1 shows the engine 5 with a high spool that directly drives (that is, drives without a gear box) an electric generator 55 which operates at 60 Hertz for the United States market or 50 Hertz for the European market.
  • the high spool includes a high pressure compressor (HPC) 51 connected by the high spool shaft 50 to a high pressure turbine (HPT) 52.
  • HPT high pressure turbine
  • a high pressure combustor 53 is connected between the HPC 51 and the HPT 52.
  • a variable inlet guide vane (IGV) assembly 57 is positioned upstream of the high pressure compressor 51.
  • the twin spool turbocharged industrial gas turbine engine 5 of the present invention can produce in excess of 500 MW for the 60 hertz engine and in excess of 720 MW for the 50 hertz engine.
  • the present invention is also a variable inlet guide vane for a turbine in which a rotational axis of the airfoil is located aft of the aerodynamic center of pressure on the airfoil in order to eliminate leakage gaps at the two endwalls. This is done to articulate the turbine vane at the entrance of a low pressure turbine on an axis well aft of the aerodynamic center of pressure. The use of this aft places rotation axis in combination with large diameter end wall buttons, minimized the clearance gaps of the OD and ID interface of the airfoil to end walls. By placing rotation center aft of the aerodynamic center of pressure leakage gap over aft portion of airfoil is minimized. For a given leakage gap, leakage flow amount and performance loss per unit flow is larger at aft portion of turbine airfoil due to high airfoil velocities than in front portion.
  • a low spool with a low pressure turbine (LPT) 61 is connected by the low spool shaft 60 to a low pressure compressor (LPC) 62.
  • the low spool functions as a turbocharger for the high spool.
  • a first variable inlet guide vane assembly 58 is positioned upstream of the LPT 61.
  • a second variable inlet guide vane assembly 64 is positioned upstream of the LPC 62.
  • the high spool can operate separately from the low spool since the high spool does not rotate outside (that is, concentric with) of the low spool, as in a typical twin spool gas turbine engine, such as those that power an aircraft.
  • the high spool directly drives the electric generator 55 at a speed that his synchronous with a speed of a local electrical power grid to produce electrical power.
  • the LPC 62 includes an outlet volute 63 into which the compressed air flows from the LPC 62.
  • the compressor outlet volute 63 is connected to an inlet volute 56 of the HPC 51 through a compressed air line 67, such as a tube, conduit, or pipe.
  • FIG. 2 shows the twin spool turbocharged industrial gas turbine engine of FIG. 1 in a combined cycle power plant where a heat recovery steam generator (HRSG) 40 is used to produce steam from the exhaust from the low pressure turbine (LPT) 61 that is then used to drive a second electric generator 38.
  • HRSG heat recovery steam generator
  • Hot turbine exhaust flow from the LPT 61 flows through line 68 and into the HRSG 40 to produce steam that flows through a high pressure steam turbine 36 and then a low pressure steam turbine 37 that both drive the second electric generator 38.
  • the cooler exhaust from the HRSG 40 flows out of a stack 41 that is connected to the HRSG 40.
  • a first intercooler 65 can be used to cool the compressed air from the low pressure compressor (LPC) 62 in the compressed air line 67 with a flow control valve 66.
  • LPC low pressure compressor
  • a turbine airfoil cooling circuit can also be used in which some of the compressed air from the LPC 62 is passed through a second intercooler 71 and then a cooling circuit compressor 72 driven by a motor 73 to increase the pressure so that the turbine airfoil 76 can be cooled by the flow of compressed air therethrough and have enough pressure left over to flow into the high pressure combustor 53.
  • the compressed air line 75 between the cooling circuit compressor 72 and the turbine airfoil 76 and the compressed air line 77 between the turbine airfoil 76 and the high pressure combustor 53 channel the cooling air to and from the air cooled turbine airfoils, such as the stator vanes, respectively.
  • a boost compressor 78 with flow control valve 80 can be used to pressurize air for the high pressure compressor (HPC) 51.
  • compressed air from the HPC 51 flows into the high pressure combustor 53, where fuel is burned to produce a hot gas stream that flows into the high pressure turbine (HPT) 52.
  • Hot exhaust from the HPT 52 then flows into the LPT 61 that is used to drive the LPC 62.
  • Compressed air from the LPC 62 flows through the compressed air line 67 and into the inlet of the HPC 51 (for example, into the inlet volute 56).
  • the high spool drives the electric generator 55 and thereby produces electricity.
  • the three sets of variable inlet guide vanes 57, 58, 64 are used to regulatethe flow of compressed air into the HPC 51, LPT 61, and LPC 62, respectively.
  • the high spool is used to drive the electric generator 55 and thus operates continuously (3,600 rpm for a 60 Hertz engine or 3,000 rpm for a 50 Hertz engine) during different ambient temperatures at the designed speed of the electric generator 55.
  • the low spool with the LPC 62 is operated at a higher speed so that more compressed air is passed into the HPC 51 to keep the power output consistent.
  • the IGV assembly 58 to the LPT 61 can be closed to increase the pressure ratio across the LPT 61 and therefore increase the output power of the LPT 61 to drive the LPC 62 at the higher speed and produce more compressed air for the HPC 51.
  • a key component of this invention is to design the LPT 61 so that its physical speed
  • the low spool is designed to operate at a higher speed than the normal speed at the designed for ambient temperature conditions.
  • the low spool is designed to operate at the 90 degrees F condition as well as the 60 degrees F condition so that the low spool can operate at the higher speed during the hot days (90 degrees F) so that the high spool can operate at full power.
  • the arrangements of the IGV assemblies 57, 58, 64 and their operation can be used to produce a constant mass flow through the high spool so that the full power of the engine 5 is used to drive the electric generator 55.
  • the LPC 62 and LPT 61 of the engine 5 are designed for a physical speed higher than required for the standard ISO operating temperature (60 degrees F) so that the normal mass flow will flow through the engine at hot day conditions and drive the electric generator 55 at full power.
  • the flow through the engine 5 is maintained at ISO day levels by varying the IGV assemblies 57, 58, 64 to increase the speed of the low spool relative to ISO day while maintaining the speed of the high spool at the electric generator design speed.
  • the engine 5 will operate at full power regardless of the ambient outside air temperature.
  • FIG. 3 shows an isometric view of a variable inlet guide vane 10 with the rotation axis behind the airfoil center of pressure.
  • FIG. 4 shows a mid-span section of the airfoils in FIG. 3 with circle radius indicating the throat area change as the vane angle is articulated about the selected vane rotation axis.
  • FIG. 5 shows the outer diameter and inner diameter gaps between the outer diameter and inner diameter end walls that are minimized for diverging turbine flow paths with variable guide vanes articulated with axis of rotation aft of the airfoil center of pressure.
  • FIG. 3 shows one of the airfoils in the variable inlet guide vane 10 for a turbine where the airfoil 11 extends between an outer or upper button 12 and an inner or lower button 13 with an adjustment shaft 14 extending out from the outer button 12.
  • the two buttons 12 and 13 are relatively large diameter buttons when compared to prior art buttons.
  • FIG. 3 shows the airfoil in one of three positions with the open airfoil position 11 A at one extreme, the closed airfoil position 11C at the other extreme, and the airfoil nominal position 1 IB in-between. Although all three positions are shown in FIG. 3, it will be understood that the airfoil 11 will be in one of the three positions shown at any one time.
  • the airfoil center of rotation (CR) is shown as the dashed line.
  • the variable inlet guide vane 10 may be used in a turbine, such as the LPT 61, and may be upstream in a flow direction of a rotor blade of the turbine.
  • FIG. 4 shows a top view of two adjacent airfoils in the turbine variable inlet guide vane assemblies with the airfoil shown in the three positions 11 A, 11B, and 11C.
  • the aerodynamic center of pressure (CP) and the center of rotation (CR) are shown for each of the two airfoils 11.
  • the center of rotation (CR) of each airfoil 11 is located aft of the aerodynamic center of pressure CP (that is, the CR is located downstream in a flow direction of the CP).
  • the spacing between adjacent airfoils 11 changes from DA to DC, where DA is the spacing between adjacent airfoils at the 11A position and DC is the spacing between adjacent airfoil at the 11C position. DA is greater than DC.
  • the spacing DB is the spacing between adjacent airfoils at the nominal position 1 IB.
  • the three circles in FIG. 4 represent a circle from the trailing edge with a radius equal to the spacing between adjacent airfoils at the various three positions 11A to 11C.
  • FIG. 5 shows one of the airfoils 11 of the turbine variable inlet guide vane assemblies of the present invention with the upper button 12 and the lower button 13 at the two ends of the airfoil 11 and mounted to a turbine housing or other turbine static structure 23.
  • the center of rotation (CR) is located aft of the aerodynamic center of pressure (CP) (that is, closer to the trailing edge TE of the airfoil 11 than to the leading edge LE of the airfoil 11). Because the airfoil 11 ends at the two buttons 12 and 13, as the airfoil 11 pivots from the open airfoil position 11A to the closed airfoil position 11C, no gap is formed between the airfoil trailing edge (TE) region and the button. As seen in FIG.
  • the airfoil trailing edge (TE) is located inward in a chordwise direction of the airfoil from the outer radius of each of the two buttons 12 and 13. Put another way, an outer radius of each of the inner 12 and outer 13 buttons is greater than a distance of the airfoil trailing edge (TE) from the airfoil center of rotation (CR) in a chordwise direction of the airfoil.
  • This is the structure that provides for elimination of any gaps between the trailing edge (TE) of the airfoil (11) and a static structure 23 of the turbine in which leakage can flow.
  • each of the buttons 12, 13 is less than a distance of the airfoil leading edge (LE) from the airfoil center of rotation (CR) in a chordwise direction of the airfoil.
  • Gaps 21 and 22 do exist in the leading edge regions of the airfoil 11 (and the gaps change from the airfoil positions 11 A to 11C) because the leading edge (LE) of the airfoil 11 is located outward in the chordwise direction of the airfoil from the outer radius of the two buttons 12 and 13.
  • no gap is formed between the trailing edge (TE) and the turbine housing or other turbine static structure 23
  • no leakage can flow across any gap (for example, across a gap 21, 22 between the leading edge (LE) and the turbine housing 23.
  • Gap leakage flow would be more critical in a turbine than in a compressor because of the hot gas temperature in the turbine. Hot gas leakage causes performance loss as well as short life for the parts due to erosion and thermal stress issues.
  • FIG. 6 shows the airfoil 11 at the upper button 12 with the airfoil extending from the button in which no gap is formed.
  • FIG. 7 shows a similar structural arrangement between the airfoil and the lower button 13. No gap is formed in the lower span on the TE either. Thus, as the airfoil pivots from the open to the closed position, no gaps are formed at the trailing edge regions in which leakage could flow.
  • a large frame heavy duty industrial gas turbine engine for electrical power production includes: a high spool with a high pressure compressor (51), a combustor (53), and a high pressure turbine (52); an electric generator (55) directly driven by the high spool at a speed synchronous with a local electrical power grid to produce electrical power; a low spool with a low pressure turbine (61) and a low pressure compressor (62), the low spool and the high spool being connected such that turbine exhaust from the high pressure turbine (52) drives the low pressure turbine (61); a compressed air line (67) connecting the low pressure compressor (62) to the high pressure compressor (51) to supply compressed air to the high pressure compressor (51); a first variable inlet guide vane assembly (58) for the low pressure turbine (61); and a second variable inlet guide vane assembly (64) for the low pressure compressor (62), the variable inlet guide vane assembly (58) for the low pressure turbine (61) regulating a power output to drive the low pressure compressor (62) so that the high spool can
  • the large frame heavy duty industrial gas turbine engine further includes third variable inlet guide vane assembly (57) for the high pressure compressor (51).
  • the low spool is designed to operate at a speed higher than required for a standard iso operating temperature so that the normal mass flow will flow through the engine (5) at hot day conditions and drive the electric generator (55) at full power.
  • the low spool does not rotate within the high spool.
  • the electric generator (55) is a 60 hertz generator and the industrial gas turbine engine (5) is capable of producing 500 MW.
  • the electric generator (55) is a 50 hertz generator and the industrial gas turbine engine (5) is capable of producing 720 MW.
  • a turbine with a variable inlet guide vane assembly for a gas turbine engine includes: a variable inlet guide vane (10) located upstream in a flow direction of a rotor blade of the turbine, the variable inlet guide vane (10) having an airfoil (11), an upper button (12), and a lower button (13), the airfoil (11) extending between the upper button (12) and the lower button (13), the airfoil (11) having a leading edge (LE), a trailing edge (TE), an aerodynamic center of pressure (CP), and a center of rotation (CR), the center of rotation (CR) being located downstream in a flow direction of the aerodynamic center of pressure (CP) of the airfoil (11).
  • the trailing edge (TE) of the airfoil (11) is located inward in an airfoil chordwise direction from an outer radius of the upper and lower buttons (12, 13).
  • the trailing edge (TE) of the airfoil (11) extends into each of the upper button (12) and the lower button (13) such that no gap is formed between the trailing edge (TE) of the airfoil (11) and a static structure of the turbine in which leakage can flow.
  • an airfoil (11) for a turbine variable inlet guide vane assembly includes: a leading edge (LE), a trailing edge (TE), an aerodynamic center of pressure (CP), and a center of rotation (CR), the airfoil center of rotation (CR) being aft of the airfoil aerodynamic center of pressure (CP), the airfoil (11) extending between the outer button (12) and the inner button (13), and an outer radius of each of the inner and outer buttons (12, 13) being greater than a distance of the airfoil trailing edge (TE) from the airfoil center of rotation (CR) in a chordwise direction of the airfoil (11).
  • the outer radius of each of the inner and outer buttons (12, 13) is less than a distance of the airfoil leading edge (LE) from the airfoil center of rotation (CR) in a chordwise direction of the airfoil (11).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Control Of Turbines (AREA)

Abstract

Moteur à turbine à gaz industriel puissant à grand bâti qui produit deux fois plus de puissance que les moteurs industriels à bobine unique classiques et fonctionne à pleine puissance lors d'une journée chaude. Le moteur comprend une bobine haute entraînant directement un générateur électrique à une vitesse synchrone du réseau électrique, une bobine basse avec une turbine basse-pression (LPT) entraînant un compresseur basse-pression (LPC) à partir des gaz d'échappement provenant de la turbine haute-pression. La bobine basse peut fonctionner à une vitesse plus élevée que dans les conditions normales de température pour produire un débit massique élevé. Une turbine pourvue d'un ensemble IGV variable dans lequel des profils aérodynamiques d'aube s'étendent entre des boutons intérieur et extérieur, un centre de rotation de profil aérodynamique se situant à l'arrière d'un centre de pression aérodynamique de profil aérodynamique. Le bord de fuite (TE) de profil aérodynamique s'étend dans les deux boutons pour éliminer l'espace entre le TE de profil aérodynamique et une partie statique de la turbine.
PCT/US2017/029401 2015-11-02 2017-04-25 Moteur à turbine à gaz industriel à deux bobines pourvu d'aubes de guidage d'entrée variables WO2017189566A2 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
KR1020187034161A KR20190003626A (ko) 2015-11-02 2017-04-25 가변성 주입구 가이드 베인을 구비한 트윈 스풀 산업용 가스 터빈 엔진
EP17721939.1A EP3449100A2 (fr) 2016-04-25 2017-04-25 Moteur à turbine à gaz industriel à deux bobines pourvu d'aubes de guidage d'entrée variables
CN201780038624.4A CN109415948A (zh) 2015-11-19 2017-04-25 具有可变入口导向叶片的双卷轴工业燃气涡轮发动机

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US15/137,248 2016-04-25
US15/137,248 US20170342854A1 (en) 2015-11-19 2016-04-25 Twin spool industrial gas turbine engine with variable inlet guide vanes
US15/174,051 2016-06-06
US15/174,051 US10208619B2 (en) 2015-11-02 2016-06-06 Variable low turbine vane with aft rotation axis

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WO2017189566A2 true WO2017189566A2 (fr) 2017-11-02
WO2017189566A3 WO2017189566A3 (fr) 2017-12-28

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Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1053647A (fr) * 1952-04-05 1954-02-03 Snecma Perfectionnements aux propulseurs à turbine à gaz
FR1325261A (fr) * 1961-05-23 1963-04-26 Rolls Royce Machine à écoulement d'un fluide
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit
JP3605398B2 (ja) * 2002-02-26 2004-12-22 三菱重工業株式会社 可変容量ターボチャージャ
DE10307374A1 (de) * 2003-02-21 2004-09-02 Alstom Technology Ltd Verfahren zum Betrieb eines teilgeschlossenen, aufgeladenen Gasturbinenkreislaufs sowie Gasturbinensystem zur Durchführung des Verfahrens
US8007229B2 (en) * 2007-05-24 2011-08-30 United Technologies Corporation Variable area turbine vane arrangement
CH699804A1 (de) * 2008-10-29 2010-04-30 Alstom Technology Ltd Gasturbinenanlage mit Abgasrückführung sowie Verfahren zum Betrieb einer solchen Anlage.
US20160069264A1 (en) * 2013-07-22 2016-03-10 Joseph D. Brostmeyer Gas turbine engine with turbine cooling and combustor air preheating

Non-Patent Citations (1)

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Title
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WO2017189566A3 (fr) 2017-12-28
EP3449100A2 (fr) 2019-03-06

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