WO2000039441A1 - Apparatus and method to increase turbine power - Google Patents
Apparatus and method to increase turbine power Download PDFInfo
- Publication number
- WO2000039441A1 WO2000039441A1 PCT/US1999/030413 US9930413W WO0039441A1 WO 2000039441 A1 WO2000039441 A1 WO 2000039441A1 US 9930413 W US9930413 W US 9930413W WO 0039441 A1 WO0039441 A1 WO 0039441A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- compressor
- turbine
- shaft
- generating system
- power generating
- Prior art date
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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
- 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
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
-
- 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
- F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
-
- 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
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/211—Heat transfer, e.g. cooling by intercooling, e.g. during a compression cycle
Definitions
- This invention relates generally to turbines, including microturbines, and more particularly to a method and apparatus to increase the power output of a turbine.
- Microturbines are multi-fuel, modular distributed power generation units having multiple applications. They do not require the installation of expensive infrastructure to deliver power to end-users. Thus, in parts of the world lacking the transmission and distribution lines of a basic electric infrastructure, commercialization of microturbines will be an enabling application. In the United States and other countries already having a suitable electric infrastructure, distributed generation units allow consumers of electricity to choose the most cost-effective method of electric service. In many instances microtubrines may be more cost effective than grid power owing to such considerations as energy rates or transmission line losses. In addition to primary power generation, microturbines also offer an efficient way to supply back-up power or uninterruptible power. Other applications exist as well, such as the use of flare gas and landfill gas to generate power. They may also be used to remove harmful chemicals from air that becomes polluted as a result of a manufacturing process.
- microturbine designs utilize low pressure ratio cycles (3-4 Pr (P e xit/Pini e t)), and rely primarily on recuperation to increase thermodynamic efficiency.
- the microturbine In order to increase the power of a microturbine beyond that which can be achieved with increased firing temperature (which, typically, results in a 10-15% increase in power, at the sacrifice of component life), the microturbine must be scaled to a larger aerodynamic flow size.
- scaling is costly, and, while providing additional power, does little if anything to increase system efficiency.
- Farrell, et al. discloses systems that include a low-pressure compressor, a high- pressure compressor downstream of the low-pressure compressor, a combustor, a high-pressure turbine downstream of the combustor, and a low-pressure turbine downstream of the high-pressure turbine.
- systems of this type include dual concentric shafts, wherein the high pressure turbine drives the high pressure compressor via a first shaft and the low pressure turbine drives the low pressure compressor by a second shaft (which passes through the first shaft).
- Farrell, et al. purport to improve on this design by eliminating the dual concentric shafts and driving both the high pressure compressor and the low pressure compressor with the high speed turbine.
- the high-pressure compressor is driven directly; the low-pressure compressor via a speed-reducing gearbox. Farrell, et al., also incorporate an intercooler between the low pressure compressor and the high speed pressure compressor to reduce the power of the high pressure compressor by, approximately, the amount of power required to run the low pressure compressor.
- Wc Wa (VTr 1 )/Pr 1 ,
- Wc is the corrected flow at the exit of the first stage of compression
- Wa is the actual physical flow
- Tn is the temperature ratio across the first stage of compression
- Pr-i is the pressure ratio across the first stage of compression.
- the optimum shaft speed is determined using design conventions that are well understood in the field.
- the ratio of corrected flows W 1 /W 2 in this case Wa/Wc
- the optimum shaft speeds for the two compressors becomes progressively dissimilar.
- Increasing the first stage pressure ratio makes this effect worse.
- increasing the first stage temperature ratio can help to reduce the dissimilarity between optimum shaft speeds by a small amount
- a first stage temperature ratio increase also has the consequence of reducing the first stage thermodynamic efficiency, which reduces overall engine efficiency.
- Intercooling increases power and offers the capability of increasing engine efficiency by reducing the temperature from the discharge of the first compression stage before the inlet to the second compression stage.
- This temperature reduction has, at least, three notable consequences. First, it reduces the cold side recuperator inlet temperature, allowing the recuperator to run cooler even at higher cycle pressure ratios. Second, the temperature reduction substantially increases the dissimilarity between optimum shaft speeds, which can necessitate the use of a gearbox or another mechanism to turn the first and second stage compressors at different speeds. Third, it reduces the work of compression.
- Farrell, et al. disclose the use of a gearbox between the first and second stages to reduce the shaft speed of the first stage relative to the second.
- 4,896,499 to Rice discloses the use of a separate low pressure compressor-turbine spool concentrically positioned within a high pressure compressor-turbine spool, the two spools running at different speeds to allow the low pressure compressor to run slower than the high pressure compressor.
- the present invention is designed to allow a large increase in power (i.e., 3-10 times greater than an existing microturbine), while providing cycle efficiency improvements (i.e., 10%- 15%) at a relatively low cost and without requiring scaling of such a microturbine. It is an additional object of the invention to increase the power output and efficiency of a conventional microturbine power generating system while reducing the system's cost per unit power. It is still another object of the invention to provide a method for improving a conventional turbine power generating system by integrating a supercharging compressor stage on the same shaft as the high-pressure compressor stage.
- Another object of the invention is to provide a supercharging stage to a conventional turbine power generating system or a microturbine power generating system, by the addition of a low pressure compressor to the same shaft as the high pressure compressor, wherein the low pressure compressor and high pressure compressor are of dissimilar (unlike each other) flow types.
- Still another object of the invention is to improve a conventional microturbine by adding a supercharging stage and intercooling, using a minimal number of additional components.
- the low-pressure super-charging compressor is a mixed flow compressor and the high-pressure compressor is a centrifugal flow compressor.
- the low-pressure compressor includes one or more axial flow compressors and the high-pressure compressor includes a centrifugal flow compressor.
- Use of mixed flow or axial flow compressors in the low pressure compression stage also overcomes the mechanical limitations that would exist with centrifugal compressors, if such centrifugal compressors were used on the same shaft as a supercharging stage of a state-of-the art microturbine today. With intercooling, a centrifugal compressor would not be able to withstand the rotational speed required if it were to be integrated on the same shaft as the high- pressure compressor in a microturbine.
- FIG. 1 is a block diagram depicting air flow through a microturbine power generation system constructed in accordance with the present invention
- FIG. 2 is a schematic of the microturbine power generating system constructed in accordance with the present invention
- FIG. 3 is a partial cross-section of a two stage centrifugal compressor
- FIG. 4 is a partial cross-section of a mixed flow compressor/centrifugal compressor, with intercooling; and FIG. 5 is a partially cut-away, partially schematic side view of a microturbine power generation system constructed in accordance with the present invention.
- the microturbine power generation system 11 intakes ambient air via a supercharging compressor stage 13.
- This supercharging compressor stage 13 increases engine airflow by approximately two to four times. Airflow to the microturbine compressor stage 17 needs to be the same, excluding insignificant losses due to any air leakage. Thus, if a 3:1 pressure ratio supercharging stage is used, and the exit flow matches the inlet of the microturbine compressor stage 17, three times the air is used as compared to a microturbine compressor stage not preceded by a supercharging compressor stage.
- the compressed airflow is directed from supercharging compressor stage
- intercooler 15 where it is cooled to near ambient conditions.
- the cooled air then proceeds to the inlet (not shown) of compressor 17 of microturbine 19.
- the air is further compressed in compressor 17, then preheated in cold side passages (not shown) of a recuperator 21 with exhaust heat, and further heated in the combustor 23, where fuel is mixed with the air and the resulting fuel-air mixture combusted.
- the hot combustion gas is then expanded through a radial turbine 25.
- the gas then passes through the power spool turbine 27, which extracts work from the gas.
- the extracted work in one embodiment, is transferred to an electrical machine 29 (e.g., a high-speed permanent magnet generator) where electricity is generated.
- an electrical machine 29 e.g., a high-speed permanent magnet generator
- the work could, alternately, be transferred into mechanical work via known means such as rotating components (e.g., a drive train), or via compressions means.
- the hot gas then passes through hot side passages (also not shown) of recuperator 21 where the waste heat is extracted from the flow before it is exhausted to the atmosphere.
- intercooler 15 typically includes a fan and motor 31.
- microturbine 19 also includes a starter motor 33.
- starter motor 33, compressor 17 and turbine 25 are all mounted on the same shaft 35.
- supercharging compressor 13 is also mounted to shaft 35, so that each revolution of turbine 25 produces a like revolution in compressor 17, motor 33 and supercharging compressor 13.
- the depicted microturbine 19 also includes a fuel valve 37, a fuel line 39 connecting valve 37 with combustor 23, and a fuel line 41 (which connects to the source of fuel).
- supercharging compressor 13 is a high efficiency transonic mixed-flow compressor of the type disclosed in U.S. patent No. 4,678,398 to Dodge, et al., the disclosure of which is incorporated by reference, although other mixed flow compressors may be used.
- N S N (Q/(H)- 75 ), wherein N s is the specific speed; N the rpm of the shaft; Q the inlet volume flow/exit volume flow; and (H) '75 , the enthalpy of compression, equals Cp (T) BTU/lbm, wherein T is the temperature rise (T ex .t - T in i e t) and Cp the specific heat.
- the aft stage is driven to a lower than desired specific speed which translates to smaller than desired inlet and exit areas.
- This effect on geometry is shown in Figure 3.
- This divergence in specific speed, and resulting effect on blading geometry limits the practical pressure ratio that can be achieved.
- the blading 51 (shaded) in the forward stage has a less than desired radius change in the tip, and the blading 53 (shaded) in the aft stage has small blade passages and a long meridional flow length which exacerbate friction and clearance losses.
- Ns (aft stage) drops to approximately 35 as indicated by the dashed area in Figure 3.
- mixed flow compressor of supercharging compressor stage 13 includes an inlet 61 , disk 63, a diffusion section 65, and a scroll 69.
- Disk 63 includes a plurality of blades 67.
- Scroll 69 is ducted to intercooler 15.
- Centrifugal compressor of microturbine compressor stage 17 includes plenum 71 , disk 73, diffuser 75 and scroll 77.
- Plenum 71 receives air from intercooler 15.
- Disk 73 includes blades 79 and splitter blades 81.
- Scroll 77 is connected to recuperator 21. Ideal specific speeds are 65 for the centrifugal compressor and 100 for the mixed flow compressor.
- the supercharging compressor stage 13 depicted in Figure 4 also has the appropriate optimal pressure ratio of 3:1 to supercharge the intercooled centrifugal microturbine compressor stage 17 with a single stage.
- the exit of supercharging compressor stage 13 in the depicted embodiment is somewhat outboard, which facilitates collection in scroll 69 for ducting to intercooler 15.
- duct refers to a channel, scroll, diffuser, pipe, or tube, and includes known systems for directing air or gas flow or allowing the passage of air or gas through a power generating system. "Ducting" means a duct or system of ducts.
- microturbine 19 is conveniently a modification of a microturbine such as one now being commercialized by Honeywell Power Systems Inc. under the brand name
- Parallon TM 75 In this embodiment, the original radial turbine 25 of the Parallon TM 75 now drives supercharging compressor 13 as well as the original microturbine compressor 17.
- the electrical starter/generator on and around the original microturbine shaft 35 is replaced by starter motor 33 and the larger electrical generator 29 is mounted on and around the added shaft 47.
- Intercooler 15 drops the temperature between the stages of compression (13 and 17) by about 150 to 200 degrees F (65.6 to 93.3 degrees Celcius), reducing by approximately 25% the power required to compress the air and enabling original single stage radial turbine 25 to have sufficient power to drive both compression stages, without requiring additional stages.
- Power turbine 27 which is either axial, radial or mixed flow, is coupled to the rotating portion of generator 29 via shaft 47.
- Turbine 27 is coupled to microturbine 19 via suitable ducting, an example of which is illustrated in Figure 5.
- the generator 29 can be a ring-wound, two-pole toothless (TPTL) brushless permanent magnet electric machine having a permanent magnet rotor and stator windings, or other suitable magnet electric machine having a permanent magnet rotor and stator.
- the rotor is rotatable relative to the stator windings.
- the shaft power generated by the rotating power turbine 27 is used to rotate the rotor, which is attached to shaft 47. When the rotor is rotated by the turbine power, an alternating current is induced in the stator windings.
- the speed of the turbine 27 can be varied in accordance with external energy demands placed on system 11. Variations in the speed of shaft 47 will produce a variation in the frequency (i.e., wild frequencies) of the alternating current generated by the electrical generator 29. Regardless of the frequency of the ac power generated by electrical generator 29, the ac power can be rectified to dc power and then inverted by a rectifier/inverter (not shown) to produce ac power having the desired fixed frequency and quality. Accordingly, when less power is required, the turbine speed can be reduced without affecting the frequency of the ac output.
- System 11 also includes an electrical control unit 91 , a variety of conventional temperature and pressure sensors, an inverter/rectifier, an electronic engine control, wiring harnesses, enclosure, bleed valves, insulation, and a control panel. For the purposes of this invention, these components may be chosen from a variety of conventional components of this nature; therefore they are not illustrated.
- system 11 can beneficially include a gas bearing circuit.
- shafts 35 and 47 are positioned at least partially within air journal bearings (also known as gas bearings) for support in the radial direction. The shafts 35 and 47 are also supported axially in such an embodiment by air thrust bearings.
- System 1 1 may also include a gas compressor loop, if low-pressure natural gas is used.
- a cooling loop may also be included for generator 29.
- microturbines While state of the art microturbines utilize centrifugal compressors in single compression stage cycles and therefore have no supercharging stage, the present invention also provides a solution to a mechanical barrier that a supercharging stage would otherwise present in microturbine construction and operation.
- the pressure ratio of single-stage compressed air to intake air is typically in the 3-5 range. If a conventional centrifugal compressor were to be used for a supercharging stage in such a microturbine, the wheel speed at the discharge of the rotor would have to be substantially greater than the wheel tip speed of the high pressure compressor. Such speed would be excessively high and would undoubtedly cause mechanical failure of the compressor.
- the present invention provides a method and construction for the successful integration of a supercharging compressor 13 onto the shaft of a conventional microturbine (which includes a single compressor stage, a single turbine stage, a permanent magnet rotor, and a single shaft that fixes each of the compressor, turbine and rotor relative to one another), and avoids mechanical failure of the supercharging compressor wheel.
- a conventional microturbine which includes a single compressor stage, a single turbine stage, a permanent magnet rotor, and a single shaft that fixes each of the compressor, turbine and rotor relative to one another
- the first stage compressor of the present invention is a mixed flow compressor or, alternatively, an axial flow compressor.
- Such compressors have a shortened exit blade height relative to centrifugal compressors, and thereby maintain a wheel tip speed in operation that is within the mechanical limits of the compressor.
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2000591314A JP2004512449A (en) | 1998-12-24 | 1999-12-21 | Apparatus and method for increasing turbine power |
EP99966491A EP1144826B1 (en) | 1998-12-24 | 1999-12-21 | Apparatus and method to increase turbine power |
AU22012/00A AU2201200A (en) | 1998-12-24 | 1999-12-21 | Apparatus and method to increase turbine power |
CA002356529A CA2356529C (en) | 1998-12-24 | 1999-12-21 | Apparatus and method to increase turbine power |
DE69930876T DE69930876T2 (en) | 1998-12-24 | 1999-12-21 | DEVICE AND METHOD FOR INCREASING THE PERFORMANCE OF A TURBINE |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11385198P | 1998-12-24 | 1998-12-24 | |
US60/113,851 | 1998-12-24 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2000039441A1 true WO2000039441A1 (en) | 2000-07-06 |
Family
ID=22351902
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US1999/030413 WO2000039441A1 (en) | 1998-12-24 | 1999-12-21 | Apparatus and method to increase turbine power |
Country Status (7)
Country | Link |
---|---|
US (1) | US6363706B1 (en) |
EP (1) | EP1144826B1 (en) |
JP (1) | JP2004512449A (en) |
AU (1) | AU2201200A (en) |
CA (1) | CA2356529C (en) |
DE (1) | DE69930876T2 (en) |
WO (1) | WO2000039441A1 (en) |
Cited By (5)
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WO2003029617A1 (en) * | 2001-10-01 | 2003-04-10 | Ingersoll-Rand Energy Systems Corporation | Spring mounted recuperator |
JP2005133724A (en) * | 2003-10-31 | 2005-05-26 | General Electric Co <Ge> | Method and apparatus for operating gas turbine engine |
JP2006519335A (en) * | 2003-02-28 | 2006-08-24 | マイクロタービン テクノロジー ビー.ブイ. | Small scale reaction turbine with integrated combustion chamber and rotor module |
FR3106620A1 (en) * | 2020-01-24 | 2021-07-30 | Psa Automobiles Sa | THERMODYNAMIC ENERGY PRODUCTION SYSTEM CONTAINING TWO TURBOMACHINES EACH PRESENT A DRIVE SHAFT |
US11339714B2 (en) | 2019-10-23 | 2022-05-24 | Rolls-Royce Plc | Gas turbine engine |
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US20050121532A1 (en) * | 2003-12-05 | 2005-06-09 | Reale Michael J. | System and method for district heating with intercooled gas turbine engine |
US6897578B1 (en) | 2003-12-08 | 2005-05-24 | Ingersoll-Rand Energy Systems Corporation | Integrated microturbine gearbox generator assembly |
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US7398642B2 (en) * | 2005-02-04 | 2008-07-15 | Siemens Power Generation, Inc. | Gas turbine system including vaporization of liquefied natural gas |
JP2006242162A (en) * | 2005-03-07 | 2006-09-14 | Hitachi Ltd | Twin shaft gas turbine system and output turbine unit |
CA2654462A1 (en) | 2006-06-08 | 2007-12-13 | Exro Technologies Inc. | Poly-phasic multi-coil generator |
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US7775031B2 (en) * | 2008-05-07 | 2010-08-17 | Wood Ryan S | Recuperator for aircraft turbine engines |
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US20130074511A1 (en) * | 2009-09-07 | 2013-03-28 | Irina Tanaeva | Method of operating a gas turbine and gas turbine |
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EP4324089A1 (en) | 2021-05-13 | 2024-02-21 | Exro Technologies Inc. | Method and apparatus to drive coils of a multiphase electric machine |
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1999
- 1999-12-17 US US09/466,342 patent/US6363706B1/en not_active Expired - Fee Related
- 1999-12-21 DE DE69930876T patent/DE69930876T2/en not_active Expired - Fee Related
- 1999-12-21 AU AU22012/00A patent/AU2201200A/en not_active Abandoned
- 1999-12-21 WO PCT/US1999/030413 patent/WO2000039441A1/en active IP Right Grant
- 1999-12-21 JP JP2000591314A patent/JP2004512449A/en active Pending
- 1999-12-21 EP EP99966491A patent/EP1144826B1/en not_active Expired - Lifetime
- 1999-12-21 CA CA002356529A patent/CA2356529C/en not_active Expired - Fee Related
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Cited By (9)
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WO2003029617A1 (en) * | 2001-10-01 | 2003-04-10 | Ingersoll-Rand Energy Systems Corporation | Spring mounted recuperator |
US6601392B2 (en) | 2001-10-01 | 2003-08-05 | Ingersoll-Rand Energy Systems Corporation | Spring mounted recuperator |
GB2396386A (en) * | 2001-10-01 | 2004-06-23 | Ingersoll Rand Energy Systems | Spring mounted recuperator |
GB2396386B (en) * | 2001-10-01 | 2005-08-24 | Ingersoll Rand Energy Systems | Spring mounted recuperator |
JP2006519335A (en) * | 2003-02-28 | 2006-08-24 | マイクロタービン テクノロジー ビー.ブイ. | Small scale reaction turbine with integrated combustion chamber and rotor module |
JP2005133724A (en) * | 2003-10-31 | 2005-05-26 | General Electric Co <Ge> | Method and apparatus for operating gas turbine engine |
US11339714B2 (en) | 2019-10-23 | 2022-05-24 | Rolls-Royce Plc | Gas turbine engine |
US11566562B2 (en) | 2019-10-23 | 2023-01-31 | Rolls-Royce Plc | Gas turbine engine |
FR3106620A1 (en) * | 2020-01-24 | 2021-07-30 | Psa Automobiles Sa | THERMODYNAMIC ENERGY PRODUCTION SYSTEM CONTAINING TWO TURBOMACHINES EACH PRESENT A DRIVE SHAFT |
Also Published As
Publication number | Publication date |
---|---|
EP1144826B1 (en) | 2006-04-12 |
AU2201200A (en) | 2000-07-31 |
DE69930876T2 (en) | 2006-11-30 |
CA2356529A1 (en) | 2000-07-06 |
CA2356529C (en) | 2009-11-10 |
JP2004512449A (en) | 2004-04-22 |
DE69930876D1 (en) | 2006-05-24 |
US6363706B1 (en) | 2002-04-02 |
EP1144826A1 (en) | 2001-10-17 |
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