WO2011073350A1 - Procédé et système de refroidissement pour des composants spécifiques dans une turbine à gaz et turbine associée - Google Patents

Procédé et système de refroidissement pour des composants spécifiques dans une turbine à gaz et turbine associée Download PDF

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Publication number
WO2011073350A1
WO2011073350A1 PCT/EP2010/069976 EP2010069976W WO2011073350A1 WO 2011073350 A1 WO2011073350 A1 WO 2011073350A1 EP 2010069976 W EP2010069976 W EP 2010069976W WO 2011073350 A1 WO2011073350 A1 WO 2011073350A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling fluid
cooling
turbine
gas turbine
temperature
Prior art date
Application number
PCT/EP2010/069976
Other languages
English (en)
Inventor
Michele D'ercole
Roberto De Prosperis
Original Assignee
Nuovo Pignone S.P.A
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nuovo Pignone S.P.A filed Critical Nuovo Pignone S.P.A
Publication of WO2011073350A1 publication Critical patent/WO2011073350A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • F01D17/085—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure to temperature
    • 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
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/112—Purpose of the control system to prolong engine life by limiting temperatures
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature

Definitions

  • the hereby described construction techniques genencally indicate a method and a specific system to cool specific components exposed to high temperatures in a gas turbine; they also regard a gas turbine which includes such a cooling system.
  • a gas turbine comprises - in its main features - an axial compressor, several combustion chambers and an expansion turbine, enclosed within a pressurized box. Air from the atmosphere enters into the compressor and is compressed to be fed into the combustion chamber, where it reacts with a combustible to form a gas at high temperature (typically around 1000 -1300 °C); the hot gas is then fed into the expansion turbine along an expansion course where it expands activating blades to transform its own thermal energy into mechanical energy.
  • the materials with which the combustion chamber is built need a powerful cooler to avoid breakage. They are subjected to extremely high temperatures in this area of the machine. The cooling of the expansion turbine components directly subjected to the high temperature gas is also particularly critical for the efficiency and reliability of the machine.
  • the turbine's maximum distributable power basically depends on the maximum temperature attainable by the process gas which is substantially limited by the resistance of the materials of which the components in direct contact with the gas are made. It is therefore extremely important to correctly cool these components to increase the maximum distributable power while decreasing the probability of breakage, which would be potentially catastrophic for the machine.
  • the temperature of the process gas decreases along the expansion course, thus the components subjected to the highest temperatures are arranged upstream from the expansion course in proximity to the combustion chamber. In fact, if these components are not cooled, they deteriorate much faster than components not directly subjected to the hot gas, even when made with special materials with or without thermal barriers such as metals, superalloys or other materials.
  • an operating method for a gas turbine including at least the following stages is the object of the invention: a - compress a working fluid by means of a compressor; b - overheat the above mentioned working fluid by means of a combustion chamber; c - expand the overheated working fluid by means of an expansion turbine to generate energy; d - insert a cooling fluid under pressure in at least one of the wheel spaces of the above mentioned expansion turbine; e - adjust the quantity of the above mentioned cooling fluid so that the temperature of one of the above mentioned wheel spaces (S1-S4) will be within the acceptable range to ensure the resistance of the materials and at the same time to reduce the quantity of fluid involved to enhance the thermal performances of the gas turbine under specific operating situations.
  • the disc cavity (or wheel space) is understood to mean, in short, either the space between the stator structure and the support disk of the blades of the expansion turbine, or the space between a support disk and the adjacent disk; therefore it includes, in general, all the components or parts of the machine that are shown, please see also the description below.
  • the working fluid is usually created by sucking air from the atmosphere into the compressor; the overheated working fluid, therefore, results in a mix of atmosphere air and combustion gas at high temperature.
  • the adjustment stage (e) is included, which is activated during operational situations entailing partial loads, or in working conditions during which the machinery does not constantly work at the maximum possible power, whether this is due to a fault of the specific installation or to environmental conditions, such as, for example, when only a small part of the distributable power is required, or when sudden environmental temperature changes occur, or during the start-up of the machine and many others.
  • a gas turbine specifically designed to work constantly on full load, to provide the maximum quantity of energy available through an essentially constant outtake, such as the turbines used to guide electric generators.
  • the operation conditions actually correspond to the conditions during startup or during the turning off procedure of the machine or while an incidental extemporary machine blockage occurs.
  • turbines are designed specifically to work not at full load to supply variable quantities of energy outtake, such as the turbines used as aero motors or the ones used to activate a piece of machinery working at a variable load (a compressor or otherwise).
  • a cooling system is included, aimed at feeding a cooling fluid under pressure in the wheel spaces of the expansion turbine, at adjusting the above mentioned cooling fluid to keep the temperature in the wheel spaces between the acceptable range; the adjustment is established based on the resistance of the materials and it aims at reducing the quantity of fluid involved to enhance the thermal performances of the piece of machinery as a whole.
  • the present invention concerns a gas turbine comprising a cooling system of the type described above.
  • Figure 1 is a schematic view in longitudinal section of a part of a machinery following an embodiment of the invention
  • Figure 2 shows an enlarged detail of Figure 1 ;
  • Figure 3 shows an enlarged detail of Figure 2.
  • a turbine in which the same numbers correspond to the same parts in all the different figures, a turbine is indicated with 1, see Fig.l, and it comprises - in its main features - an axial compressor 3, several combustion chambers 5 and an expansion turbine 6, formed by a first part, the so called “high pressure” one 7 and another part, the so called “low pressure” one 9, enclosed in a pressurized box 8 , eventually made out of one or several combined shells.
  • An high pressure expansion turbine 7 is, generally speaking, the section of the turbine in which the initial stage of the gas expansion takes place at the top of the expansion process positioned near the combustion chambers 5, for multi shaft machinery.
  • a low pressure expansion turbine 9 is, generally speaking, the section of the turbine in which the final stage of the gas expansion takes place at the end of the expansion process, in a multi shaft piece of machinery
  • a high pressure expansion turbine 7 is generically composed of one or more lines of stator blades 13S and rotor blades engaging the compressor 3 through a first shaft 17 rotating around axis XI; the low pressure expansion turbine 9 is also composed of one or more stator blades 15S and rotor blades 15R - please see also Fig.2 - and it engages an external piece of machinery (usually a power generator or a compressor, but not exclusively), which is not shown in the drawings for the sake of simplicity, through a second shaft 18, coaxial with the first shaft 17. Experts in the specific field will know that it is possible to have only one continuous shaft instead of the first and the second one 17, 18 both described in the text, based on the specific machine created.
  • the rotor blades 13R of the expansion turbine 7 are mechanically connected to shaft 17 through specifically shaped rotor discs 17A while the stator blades 13S are mounted on the specific stator discs 17B, the latter being shaped and moving jointly to shaft 17; discs 17A and 17B are mounted one after the other and they are coupled firmly to create a single rotating entity.
  • the rotor blades 15R in the low pressure expansion turbine 9 are mechanically connected to shaft 18 by specifically shaped rotating discs 18 A.
  • the stator blades 15S of turbine 9 are in turn mounted on the specific shaped stator discs 18B jointly with shaft 18; discs 18A and 18B are mounted one after the other and they are mechanically connected together, please see also the description below.
  • the feeding stage of a first preferred embodiment (d) is created introducing the cooling fluid under pressure through channels 21, 23 and 25 which tap it from the compressor 3 and introduce it - please see fig. 2 - in at least one wheel space SI, S2, S3 and respectively S4 of the low pressure turbine 9.
  • Fig.1 also shows a thermal shield 29 that is generally designed to divide the high pressure expansion turbine 7 from the low pressure expansion turbine 9 needed due to the pressure of the gas along the expansion course 11. This shield 29 might not be there, when the project specifications do not require it.
  • This Figure shows a mechanical bearing 33 supporting the rotating shaft and a channel 35 that fluidly connects the flow from compressor 3 to a cavity 37 created coaxially within shaft 17, which is also in fluid connection with the rotating spaces of the high pressure expansion turbine 7 for constant cooling of the wheel spaces of the turbine 7 through the part of working fluid that is intercepted in channel 35 (arrow F9) without any type of adjustment or control.
  • many known cooling systems for components exposed to high temperatures may be used in combination with the present invention; they are not represented here for the sake of simplicity.
  • Fig.2 shows a zoomed in detail of the expansion turbine 9 of Fig.1 in which it is shown the first wheel space SI created between the thermal protector 29 and the first rotating disk 18 A; the second wheel space S2 created between the first rotating disc 18A and the first stator disc 18B; the third or last wheel space S3 created between the first stator disk 18B and the second rotating disk 18 A and the fourth and last wheel space S4 created between the second rotating disk 18A and the box 8. Wheel spaces S1-S4 are enclosed within the lateral walls of box 8.
  • the first channel 21 passes through a first stator blade 8S' drawn in box 8 and successively passes through the first stator blade 15S to enter the first wheel space SI of the same turbine 9;
  • the second channel 23 passes though a stator blade 8S" drawn in box 8 and afterwards it passes through the second stator blade 15S to enter, afterwards, in the second and then third wheel spaces S2 and S3 in the low pressure expansion turbine 9.
  • the third channel 25 is preferably designed to pass through box 8 and to be in fluid connection with the last wheel space S4. Please note that in the embodiment shown in the Figure, this last channel 25 does not pass through a stator cavity in box 8, but it reaches the back area 8P of the same box 8 which lacks such cavity.
  • stator blades 8S' and 8S of blades 13R, 13S and 15R, 15S of wheel spaces SI, S2 and S3 are drawn to give an example, and they can differ both in number and in shape according to the specification requirements for construction or use; for example, stator blades 8S' and 8S" might not be there and therefore blades 18S' and 16S" might be mounted directly onto box 8.
  • Channels 21, 23 and 25 might also be mounted on a previously established number of blades 13R, 13S or 15R, 15S based on specific design needs.
  • channels 21 and 23 do not open to the corresponding cavities 8S' and 8S": they might though, so that the cooling fluid will reach the specific cavities; in this last case, furthermore, the temperature of the fluid entering the wheel spaces SI , S2 and S3 might undergo variations or instabilities which in the end will make the process harder to monitor.
  • a first sensor 29A is placed in the first wheel space SI, in a position which it will allow to detect its highest temperature, preferably near the same blade 15S; a second and a third sensor 29b and 20C are placed inside the wheel spaces S2 and S3, also in this case, in such position that it will allow to detect the highest temperature while the machine is operative; a fourth sensor 29D is placed in a specific position within the wheel space S4.
  • the above mentioned sensors 29A-29D are connected electronically and they are monitored through the control unit C (please see also Fig.l).
  • the control unit C has the possibility to monitor directly and in real time the temperature variation in the wheel spaces S1-S4 and it also can manage the valves 27A-27C if needed.
  • control unit C receives the data from sensors 29E-29I from which it detects the variations in temperature of wheel spaces S1-S4 thus operating, if necessary, valves 27A-27C.
  • sensors 29A-29I It is also possible to design a different number or type of sensors 29A-29I, and it is also possible to use the sensors normally used based on the specific turbine. Please note that it is advisable to implement a direct temperature monitoring, because this choice implies lower installation and maintenance costs, and a faster and more reliable feedback from the system; an indirect monitoring can though be used as well, in case it were to be more convenient to use sensors or devices which are already included in the machine.
  • Fig.3 shows in detail the stator blade 15S which has an inferior extremity that is mounted on the superior extremity of the first stator disc 18B by means of a traditional labyrinth sealant 31 ; rotor blades 15R which have inserted flaps to limit the passage opening, between each wheel space S1-S4 and expansion channels 12, through which the cooling air is discharged (arrows F8). In some cases it is possible that the hot gas will enter these openings from the expansion stage, entering the wheel spaces S1-S4 as mentioned above.
  • stator cavities 8S' and 8S" there are joint or fixed areas outside of box 8, which are not in direct contact with the gas used in the process and which can be enhanced by a mechanical sealing system - not shown in the Figure for the sake of simplicity - which avoids or limits any intake of hot gas; these stator cavities 8S' and 8S" can therefore include independent cooling systems. IT is not excluded that this invention will be used to cool, at least partially, also the stator cavities 8S' and 8S" according to specific applications or needs.
  • the working operations of the machine include a first starting stage, during which the same machine reaches gradually full capacity.
  • the sensors 29A-29I measure (directly or indirectly) the temperature in the wheels spaces S1-S4, which increases gradually until it reaches the level expected at full capacity, while the monitoring system C gradually increases the flow of the cooling liquid towards the wheel spaces S1-S4, based on the variation of the above mentioned temperature up to the full capacity temperature.
  • the cooling system will deliver a constant flow of the cooling fluid until when a variation of the temperature within at least one of the wheel spaces S1-S4, measured by one of the sensors 29A-29I will occur.
  • This temperature variation might occur when the value of the power generated by the machine is modified based on specific working needs, or when there are substantial variations of the environmental conditions (eg. between day and night in some spots of the world, or based on specific times during the year, summer and winter).
  • the cooling system regulates the flow of cooling fluid to keep the temperature of all wheel spaces S1-S4 within the pre-established range.
  • cooling fluid is introduced, under pressure, through a potential drainage system - not shown in the Figures for the sake of simplicity - in compressor 3, which is included in specific applications; this is also an economically convenient system, because it mainly uses the components which were planned to be used.
  • the cooling fluid is introduced through an external compression system - also not shown in the drawings.
  • cooling fluid feeding stage (d) might be carried out single handedly or in combination among them, based on the specific needs or on the specific machine used; it is also possible to include other types of feeding systems for the cooling fluid in the wheel spaces based on a specific application or machine.
  • the cooling fluid is introduced under pressure within the wheel spaces only in the high pressure expansion turbine 7, which is exposed to higher temperatures, slightly improving the whole performance of the machine. This setting is also very inexpensive.
  • the cooling fluid under pressure is introduced within the wheel spaces of a single shaft gas turbine.
  • the cooling system can be implemented in at least one of the expansion stages.
  • the optimized cooling of the wheel spaces allows to reduce the amount of cooling fluid while operating at partial loads, when not operating at full capacity or in specific environmental conditions, slightly increasing the thermal performance of the same expansion.
  • the cooling system described above is preferably implemented in combination with cooling systems known to enhance a high performance machine with a high thermal efficiency, such as rotor blades and stator blades cooling systems and those for mechanical bearings.
  • system described therein and therein claimed can also be implemented in combination with the traditional cooling systems for wheel spaces, which entail the inflow of a constant amount of cooling air according to particular applications; in this last case the beneficial performance consequences would be hindered.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention concerne un procédé de fonctionnement d'une turbine à gaz comprenant au moins les étapes suivantes consistant à : a - comprimer un liquide fonctionnel au moyen d'un compresseur (3) ; b - surchauffer le liquide fonctionnel susmentionné au moyen d'une chambre de combustion (5) ; c - effectuer l'expansion du liquide fonctionnel surchauffé au moyen d'une turbine d'expansion (6) pour générer de l'énergie ; d - introduire un liquide de refroidissement sous pression dans au moins un des espaces de roue (S1-S4) de la turbine d'expansion (6) susmentionnée ; e - ajuster la quantité du liquide de refroidissement susmentionné de sorte que la température d'au moins un des espaces de roue (S1-S4) susmentionnés soit comprise dans la plage acceptable pour assurer la résistance des matériaux et réduire en même temps la quantité de liquide impliquée, augmentant de ce fait les performances thermiques de la turbine à gaz dans des situations de fonctionnement spécifiques.
PCT/EP2010/069976 2009-12-19 2010-12-16 Procédé et système de refroidissement pour des composants spécifiques dans une turbine à gaz et turbine associée WO2011073350A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITCO2009A000069 2009-12-19
ITCO2009A000069A IT1399156B1 (it) 2009-12-19 2009-12-19 Metodo e sistema di raffreddamento per specifici componenti di una turbina a gas e relativa turbina.

Publications (1)

Publication Number Publication Date
WO2011073350A1 true WO2011073350A1 (fr) 2011-06-23

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PCT/EP2010/069976 WO2011073350A1 (fr) 2009-12-19 2010-12-16 Procédé et système de refroidissement pour des composants spécifiques dans une turbine à gaz et turbine associée

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IT (1) IT1399156B1 (fr)
WO (1) WO2011073350A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013127995A1 (fr) * 2012-03-01 2013-09-06 Nuovo Pignone S.R.L. Procédé et système pour recommander une action d'opérateur
JP2021124052A (ja) * 2020-02-04 2021-08-30 東芝エネルギーシステムズ株式会社 軸流タービン

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4217755A (en) * 1978-12-04 1980-08-19 General Motors Corporation Cooling air control valve
EP0493111A1 (fr) * 1990-12-27 1992-07-01 United Technologies Corporation Turbine à gaz avec modulation de l'air de refroidissement
DE19824766A1 (de) * 1998-06-03 1999-12-09 Siemens Ag Gasturbine sowie Verfahren zur Kühlung einer Turbinenstufe
US20070137213A1 (en) * 2005-12-19 2007-06-21 General Electric Company Turbine wheelspace temperature control
EP1806478A2 (fr) * 2006-01-06 2007-07-11 General Electric Company Turbine à gaz et son système de refroidisssement

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4217755A (en) * 1978-12-04 1980-08-19 General Motors Corporation Cooling air control valve
EP0493111A1 (fr) * 1990-12-27 1992-07-01 United Technologies Corporation Turbine à gaz avec modulation de l'air de refroidissement
DE19824766A1 (de) * 1998-06-03 1999-12-09 Siemens Ag Gasturbine sowie Verfahren zur Kühlung einer Turbinenstufe
US20070137213A1 (en) * 2005-12-19 2007-06-21 General Electric Company Turbine wheelspace temperature control
EP1806478A2 (fr) * 2006-01-06 2007-07-11 General Electric Company Turbine à gaz et son système de refroidisssement

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013127995A1 (fr) * 2012-03-01 2013-09-06 Nuovo Pignone S.R.L. Procédé et système pour recommander une action d'opérateur
JP2015513636A (ja) * 2012-03-01 2015-05-14 ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ． オペレータの動作に助言するための方法およびシステム
US9274520B2 (en) 2012-03-01 2016-03-01 Nuovo Pignone Srl Method and system for condition monitoring of a group of plants
US9921577B2 (en) 2012-03-01 2018-03-20 Nuovo Pignone Srl Method and system for diagnostic rules for heavy duty gas turbines
RU2657047C2 (ru) * 2012-03-01 2018-06-09 Нуово Пиньоне С.р.л. Способ и система для рекомендации действий оператору
US10088839B2 (en) 2012-03-01 2018-10-02 Nuovo Pignone Srl Method and system for real-time performance degradation advisory for centrifugal compressors
JP2021124052A (ja) * 2020-02-04 2021-08-30 東芝エネルギーシステムズ株式会社 軸流タービン

Also Published As

Publication number Publication date
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