EP4655494A1 - A gas turbine package ventilation system and a method for ventilating a gas turbine package - Google Patents

A gas turbine package ventilation system and a method for ventilating a gas turbine package

Info

Publication number
EP4655494A1
EP4655494A1 EP24708677.0A EP24708677A EP4655494A1 EP 4655494 A1 EP4655494 A1 EP 4655494A1 EP 24708677 A EP24708677 A EP 24708677A EP 4655494 A1 EP4655494 A1 EP 4655494A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
downstream
ventilation
air inlet
upstream
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP24708677.0A
Other languages
German (de)
French (fr)
Inventor
Gabriele LUCHERINI
Stefano MINOTTI
Stefano Rossin
Andrea TANGANELLI
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nuovo Pignone Technologie SRL
Original Assignee
Nuovo Pignone Technologie SRL
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 Technologie SRL filed Critical Nuovo Pignone Technologie SRL
Publication of EP4655494A1 publication Critical patent/EP4655494A1/en
Pending legal-status Critical Current

Links

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
    • F02C7/12—Cooling of plants
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F01D25/145—Thermally insulated casings
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F02C7/24—Heat or noise insulation
    • 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
    • F02C7/24—Heat or noise insulation
    • F02C7/25—Fire protection or prevention
    • 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
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/605—Venting into the ambient atmosphere or the like
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/608—Aeration, ventilation, dehumidification or moisture removal of closed spaces

Definitions

  • the present disclosure concerns a system and a method of ventilating a gas turbine package.
  • Embodiments disclosed herein specifically concern gas turbine packages comprising a gas turbine, including a compressor, a combustor and a compressor driving turbine, and surrounded by an enclosure, wherein ventilation inside the gas turbine enclosure is split into two separate flows, respectively ventilating a first portion of the gas turbine, downstream the combustion chamber, surrounding the turbine, and a second portion of the gas turbine, upstream the combustion chamber, surrounding the compressor and also including a fuel gas supply line through which a fuel stream is routed to the combustor.
  • Gas turbines are commonly provided with an enclosure, which is barely larger than the turbine itself, with the aim of protecting the surroundings from the heat and noise level emitted from the turbine.
  • this insulation keeps the temperature in the enclosure high, which may lead to overheating and malfunctioning of the gas turbine and finally to a cost intensive shut down.
  • a ventilation system of the gas turbine enclosure is commonly used.
  • the ventilation system also provides the capability to dilute any leak of fuel into the enclosure, which can produce potentially explosive gas mixtures, by continually purging potential gas build up areas and transferring potentially explosive gas mixtures out of the enclosure.
  • the presence of explosive gases caused for example by leakages in the gas turbine fuel supply line piping, involves a serious risk of explosions, because such explosive gases can enter in contact with the gas turbine hot surfaces, wherein auto-ignition of the gases can occur.
  • the ventilation systems of the current art are based on the principle of diluting any possible explosive gas concentration inside the enclosure.
  • Commonly used ventilation systems provide for ventilation air entering the enclosure from the same side of air directed to the compressor and exiting from the same side of the exhaust gas of the turbine, so that the same air filters can be used for both air flows and shorter pipes are needed. This approach allows for dilution of possible fuel gas leaks.
  • the ventilation air flow proceeds from the compressor to the turbine, possible fuel leaks from the fuel feed line are drawn to the hot surfaces of the turbine, the risk of auto ignition being reduced because of the dilution, but not removed.
  • ventilation systems wherein ventilation air enters the enclosure from the side of outlet of the exhaust gas of the gas turbine, namely the turbine portion of the gas turbine, downstream the combustion chamber, and exits from the side of inlet of fresh air to the gas turbine, namely the compressor portion of the gas turbine.
  • This approach allows the ventilation air flow to draw possible fuel leaks from the fuel feed line to the compressor portion of the gas turbine, the surfaces of the compressor being less hot than those of the turbine, the risk of contact of the fuel with the hot surfaces of the turbine being consequently reduced.
  • this approach is sufficient to completely remove the risk of contact of the fuel with the hot surface of the turbine.
  • an improved system and method for ventilating a gas turbine enclosure to address the issues of contact between possible fuel leaks and hot surfaces of the turbine and the subsequent risk of auto ignition of the systems of the current art would be beneficial and would be welcomed in the technology.
  • such improved system and method for ventilating a gas turbine enclosure should be much more efficient than the prior art systems and methods, in order to be suitable for gas turbines using hydrogen, or other highly reactive gases, as fuel, such highly reactive fuels involving an even higher risk of auto ignition of fuel leaks in contact with hot surfaces of the gas turbine.
  • the subject matter disclosed herein is directed to a gas turbine package ventilation system comprising an enclosure surrounding a gas turbine, the gas turbine including, in the direction of the flow, a compressor, a combustor and a compressor driving turbine.
  • the ventilation air distribution system is adapted to separate two divergent ventilation flows: a first ventilation flow, flowing from a central portion of the gas turbine towards an exhaust gas outlet portion of the gas turbine, and a second ventilation flow, flowing from a central portion of the gas turbine towards a fresh air inlet portion of the gas turbine.
  • the enclosure of the gas turbine is divided into two portions, a first portion or downstream portion of the gas turbine, this downstream portion surrounding the turbine, downstream the combustor, i.e. the hottest portion of the gas turbine and a second portion or upstream portion of the gas turbine, surrounding the compressor and the combustor of the gas turbine.
  • the upstream portion of the gas turbine also includes the fuel supply line, the second ventilation flow drawing any possible fuel leak away from the hot portion of the gas turbine.
  • the subject matter disclosed herein concerns a method for ventilating a gas turbine package comprising an enclosure surrounding a gas turbine, the gas turbine including a compressor, a combustor and a turbine.
  • the method comprises the steps of: splitting ventilation air inside the enclosure into two separate flows, namely a first ventilation flow and a second ventilation flow; directing the first ventilation flow towards a first portion of the enclosure, surrounding the turbine of the gas turbine, downstream the combustor, and directing the second ventilation flow towards the compressor of the gas turbine, upstream the combustor, and towards a fuel supply line through which a fuel stream is routed to the combustor.
  • a further aspect of the present disclosure is drawn to a gas turbine package ventilation system wherein the first and the second portions of the enclosure of the gas turbine are separated by separation means, dividing the enclosure into a first compartment, surrounding the gas turbine downstream the combustor, and a second compartment, upstream the first compartment, surrounding the combustor and the compressor of the gas turbine and also including the fuel supply line.
  • the separation means can include a wall or a plate arranged between the first compartment and the second compartment.
  • a still further aspect of the present disclosure is drawn to a gas turbine package ventilation system comprising two perforated walls or plates arranged between the first compartment and the second compartment and defining an interspace. Ventilation air enters the interspace through a ventilation inlet and two separate flows, namely a first flow directed to the first compartment and a second flow directed to the second compartment exit the interspace through openings in each of the perforated walls or plates defining the interspace.
  • ventilation air arriving from the ventilation inlet pressurizes the interspace, avoiding any possible reverse flow from one of the enclosure compartments to the interspace and to the other enclosure compartment.
  • Fig.1 illustrates a schematic of a gas turbine ventilation package including a ventilation air distribution system adapted to separate two divergent ventilation flows;
  • Fig.2 illustrates a schematic of a gas turbine ventilation package including a ventilation air distribution system and separation means of the gas turbine enclosure
  • Fig.3 illustrates a schematic of a gas turbine ventilation package including a ventilation air distribution system and separation means of the gas turbine enclosure defining a pressurized cavity mechanically separating the gas turbine enclosure into a first compartment and a second compartment;
  • Fig.4 illustrates a flow chart of a method for ventilating a gas turbine package according to the present disclosure.
  • a ventilation system which includes a ventilation air distribution system adapted to split the ventilation air into two separate flows, respectively adapted to ventilate a gas turbine first portion, downstream the gas turbine combustor and a gas turbine second portion, upstream the first portion.
  • the gas turbine package ventilation system can additionally comprise separation means, for example a wall or a plate, to divide the enclosure into two separate compartments, respectively a first compartment, surrounding the gas turbine downstream the combustor, and a second compartment, surrounding the compressor and the combustor.
  • separation means for example a wall or a plate, to divide the enclosure into two separate compartments, respectively a first compartment, surrounding the gas turbine downstream the combustor, and a second compartment, surrounding the compressor and the combustor.
  • Fig.l shows a schematic of a gas turbine 10, surrounded by an enclosure 20.
  • the gas turbine is comprised of a compressor 11, a combustor 12 and a compressor driving turbine 13. Air enters the compressor 11 through an air collector 14, or air inlet 14, and flows through the compressor 1 1 towards the combustor 12, while its pressure is increased.
  • Air enters the compressor 11 through an air collector 14, or air inlet 14, and flows through the compressor 1 1 towards the combustor 12, while its pressure is increased.
  • compressed air is mixed with a fuel gas (or vapor or droplets), entering the combustor 12 through a fuel supply line 15.
  • the gas mixture of air and fuel is then ignited in the combustor 12, its temperature and pressure being additionally increased.
  • the high temperature and high pressure combusted gas mixture enters the turbine 13, wherein its potential energy is exploited to produce kinetic energy, the exhaust gas is then collected through an exhaust gas collector 16 or exhaust gas outlet 16.
  • the gas turbine package ventilation system includes two ventilation air inlet conduits 21, 22, namely a downstream ventilation air inlet conduit 21 and an upstream ventilation air inlet conduit 22.
  • the downstream ventilation air inlet conduit 21 is arranged in a central portion of the gas turbine enclosure 20, downstream the combustor 12, and comprises a plurality of first openings 23 directed towards the exhaust gas outlet 16 of the gas turbine 10.
  • the upstream ventilation air inlet conduit 22 is arranged in a central portion of the gas turbine enclosure 20, upstream the downstream ventilation air inlet conduit 21, and comprises a plurality of second openings 24 directed towards the air inlet 14 of the gas turbine 10.
  • the gas turbine package ventilation system includes two ventilation air outlet conduits 25, 26, namely a downstream ventilation air outlet conduit 25 and an upstream ventilation air outlet conduit 26.
  • the gas turbine package ventilation system operates as follows.
  • the ventila- tion air inside the enclosure 20 is splitted into two separate flows, namely a first ventilation flow or downstream ventilation flow and a second ventilation flow or upstream ventilation flow.
  • the downstream ventilation flow is directed from a central portion of the enclosure 20, wherein it is conveyed through the downstream ventilation air inlet conduit 21, towards a downstream portion of the enclosure 20, surrounding the turbine 13, downstream the combustor 12, and towards the downstream ventilation air outlet conduit 25.
  • the upstream ventilation flow is directed from a central portion of the enclosure 20, wherein it is conveyed through the upstream ventilation air inlet conduit 22, towards an upstream portion of the enclosure 20, surrounding the compressor 11, the combustor 12 and the fuel supply line 15, through which a fuel stream is routed to the combustor 12.
  • any possible leak of fuel from the fuel supply line 15 is diluted and drawn upstream by the upstream ventilation flow. Therefore, any contact between the fuel and the turbine hot surfaces is prevented.
  • the downstream ventilation flow is kept separate from the upstream ventilation flow, to ventilate the turbine.
  • any possible leakage of the fuel towards the downstream portion of the enclosure 20 is additionally diluted.
  • Possible alternative embodiments of the gas turbine ventilation system described with reference to figure 1 can include, for example, a system comprising only one ventilation air inlet conduit, which is arranged in a central portion of the gas turbine enclosure 20, downstream the combustor 12, and which comprises a plurality of downstream openings, i.e. openings directed towards the exhaust gas outlet 16 of the gas turbine 10 and a plurality of upstream openings, i.e. openings directed towards the fresh air inlet 14 of the gas turbine 10.
  • Another alternative embodiment can include two or more ventilation air inlet conduits, each conduit comprising both downstream openings and upstream openings, the ventilation air inlet conduits being arranged on different sides of the central portion of the gas turbine enclosure 20.
  • Still another alternative embodiment can include one ventilation air inlet conduit, comprising both downstream openings and upstream openings, which is arranged around the central portion of the gas turbine enclosure.
  • such ventilation air inlet conduit can be arranged along a substantially circular path around the central portion of the gas turbine enclosure 20.
  • Another alternative embodiment can include two or more ventilation air inlet conduits, each conduit comprising both downstream openings and upstream openings and each conduit arranged around the central portion of the gas turbine, wherein the two or more ventilation air inlet conduits are arranged at different radial distances from a central axis of the gas turbine.
  • Fig.2 illustrates another embodiment of a ventilation system.
  • the same reference numbers designate the same or corresponding parts, elements or components already illustrated in Fig.l and described above, and which will not be described again.
  • the ventilation system shown with reference to figure 2 includes a downstream ventilation air inlet conduit 21’ and an upstream ventilation air inlet conduit 22’, and a separation wall or plate 27 is arranged between the downstream ventilation air inlet conduit 21’ and the upstream ventilation air inlet conduit 22’.
  • the separation plate 27 divides the enclosure 20’ into two separate compartments, a downstream compartment 28 and an upstream compartment 29.
  • the embodiment shown with reference to figure 2 ensures an even better separation between any possible fuel leaks and the hot surfaces of the gas turbine.
  • the separation is further increased by maintaining the pressure inside the downstream compartment 28 higher than the pressure inside the upstream compartment 29.
  • FIG.3 a further embodiment of a ventilation system is shown in Fig.3.
  • the same reference numbers designate the same or corresponding parts, elements or components already illustrated in Fig. 1 and Fig.2 and described above, and which will not be described again.
  • the ventilation system shown with reference to figure 3 includes two perforated plates 30, 31 that are arranged in a central portion of the gas turbine enclosure 20”, downstream the combustor 12, namely a downstream perforated plate 30 and an upstream perforated plate 31.
  • the perforated plates 30, 31 divide the enclosure 20” into a downstream compartment 28 and an upstream compartment 29.
  • the perforated plates 30, 31 are spaced from each other, to define an interspace 32 between the downstream perforated plate 30 and the upstream perforated plate 31.
  • the interspace 32 is connected with a ventilation air inlet 33.
  • the downstream perforated plate 30 comprises a plurality of downstream openings 34 directed towards the downstream compartment 28 and the upstream perforated plate 31 comprises a plurality of upstream openings 35 directed towards the upstream compartment 29.
  • the gas turbine package ventilation system shown with reference to figure 3 operates as follows.
  • the ventilation air entering the interspace 32 is splitted into two separate flows, namely a downstream ventilation flow and an upstream ventilation flow, by passing through the downstream openings 34 and the upstream openings 35.
  • the ventilation air inlet 33, the downstream openings 34 and the upstream openings 35 are dimensioned to ensure the pressure inside the interspace 32 is higher than the pressure inside the downstream compartment 28, so that any possible fuel leak from the fuel supply line 15 is prevented from entering the downstream compartment 28 and from contacting the hot surfaces of the turbine 13.
  • FIG. 4 shows a flowchart summarizing the method disclosed herein for ventilating a gas turbine package.
  • the method shown with reference to figure 4 includes the steps of: splitting 40 ventilation air inside the enclosure 20 into two separate flows, namely a first ventilation flow and a second ventilation flow; directing 50 the first ventilation flow towards a first portion of the enclosure 20 or downstream portion of the enclosure 20, surrounding the turbine 13 of the gas turbine 10, downstream the combustor 12, and
  • the method can comprise a preliminary step of separating the enclosure into two separate compartments, a downstream compartment 28, surrounding the turbine 13 of the gas turbine 10, downstream the combustor 12, and an upstream compartment 29, surrounding the compressor 11 and the combustor 12 of the gas turbine 10, and the fuel gas supply line 15.
  • a step is provided of maintaining the pressure inside the hot compartment 28 higher than the pressure inside the cold compartment 29.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel Cell (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Ventilation (AREA)
  • Packaging Of Machine Parts And Wound Products (AREA)

Abstract

A gas turbine package ventilation system is disclosed. The gas turbine package ventilation system comprises an enclosure (20, 20', 20'') surrounding a gas turbine (10), the gas turbine (10) including, in the direction of flow: a compressor (11), a combustor (12) and a compressor driving turbine (13), wherein a ventilation air distribution system is adapted to separate two divergent ventilation flows, a first ventilation flow, flowing downstream from a central portion of the gas turbine (10) towards an exhaust gas outlet (16) of the gas turbine (10), and a second ventilation flow, flowing upstream from a central portion of the gas turbine (10) towards a fresh air inlet (14) of the gas turbine (10).

Description

A gas turbine package ventilation system and a method for ventilating a gas turbine package
Description
TECHNICAL FIELD
[0001] The present disclosure concerns a system and a method of ventilating a gas turbine package. Embodiments disclosed herein specifically concern gas turbine packages comprising a gas turbine, including a compressor, a combustor and a compressor driving turbine, and surrounded by an enclosure, wherein ventilation inside the gas turbine enclosure is split into two separate flows, respectively ventilating a first portion of the gas turbine, downstream the combustion chamber, surrounding the turbine, and a second portion of the gas turbine, upstream the combustion chamber, surrounding the compressor and also including a fuel gas supply line through which a fuel stream is routed to the combustor.
BACKGROUND ART
[0002] In a gas turbine, atmospheric air is brought to a higher pressure by flowing through a rotating compressor and then mixed with a fuel and ignited in a combustor to generate a high temperature gas; such high temperature pressurized gas enters a turbine, producing a shaft work output, used to drive the rotating compressor. Unused energy comes out in the exhaust gases that can be repurposed for external work, such as rotating a second, independent turbine (known as a power turbine) that can be connected to a fan, propeller, or electrical generator.
[0003] Gas turbines are commonly provided with an enclosure, which is barely larger than the turbine itself, with the aim of protecting the surroundings from the heat and noise level emitted from the turbine. However, this insulation keeps the temperature in the enclosure high, which may lead to overheating and malfunctioning of the gas turbine and finally to a cost intensive shut down. In order to guarantee a sufficient cooling of the gas turbine, a ventilation system of the gas turbine enclosure is commonly used. The ventilation system also provides the capability to dilute any leak of fuel into the enclosure, which can produce potentially explosive gas mixtures, by continually purging potential gas build up areas and transferring potentially explosive gas mixtures out of the enclosure. The presence of explosive gases, caused for example by leakages in the gas turbine fuel supply line piping, involves a serious risk of explosions, because such explosive gases can enter in contact with the gas turbine hot surfaces, wherein auto-ignition of the gases can occur.
[0004] As a consequence, the configuration of the compartment ventilation system is an important requirement in the gas turbine industry in order to minimize the risk of explosions.
[0005] At present, the ventilation systems of the current art are based on the principle of diluting any possible explosive gas concentration inside the enclosure. Commonly used ventilation systems provide for ventilation air entering the enclosure from the same side of air directed to the compressor and exiting from the same side of the exhaust gas of the turbine, so that the same air filters can be used for both air flows and shorter pipes are needed. This approach allows for dilution of possible fuel gas leaks. However, since the ventilation air flow proceeds from the compressor to the turbine, possible fuel leaks from the fuel feed line are drawn to the hot surfaces of the turbine, the risk of auto ignition being reduced because of the dilution, but not removed.
[0006] According to an alternative solution of the current art, ventilation systems are provided wherein ventilation air enters the enclosure from the side of outlet of the exhaust gas of the gas turbine, namely the turbine portion of the gas turbine, downstream the combustion chamber, and exits from the side of inlet of fresh air to the gas turbine, namely the compressor portion of the gas turbine. This approach allows the ventilation air flow to draw possible fuel leaks from the fuel feed line to the compressor portion of the gas turbine, the surfaces of the compressor being less hot than those of the turbine, the risk of contact of the fuel with the hot surfaces of the turbine being consequently reduced. However, not even this approach is sufficient to completely remove the risk of contact of the fuel with the hot surface of the turbine.
[0007] Accordingly, an improved system and method for ventilating a gas turbine enclosure to address the issues of contact between possible fuel leaks and hot surfaces of the turbine and the subsequent risk of auto ignition of the systems of the current art would be beneficial and would be welcomed in the technology. [0008] In particular, such improved system and method for ventilating a gas turbine enclosure should be much more efficient than the prior art systems and methods, in order to be suitable for gas turbines using hydrogen, or other highly reactive gases, as fuel, such highly reactive fuels involving an even higher risk of auto ignition of fuel leaks in contact with hot surfaces of the gas turbine. In fact, at present, it is becoming more and more frequent the use of hydrogen as fuel of newly construed or revamped gas turbines previously working with a different fuel.
SUMMARY
[0009] In one aspect, the subject matter disclosed herein is directed to a gas turbine package ventilation system comprising an enclosure surrounding a gas turbine, the gas turbine including, in the direction of the flow, a compressor, a combustor and a compressor driving turbine. The ventilation air distribution system is adapted to separate two divergent ventilation flows: a first ventilation flow, flowing from a central portion of the gas turbine towards an exhaust gas outlet portion of the gas turbine, and a second ventilation flow, flowing from a central portion of the gas turbine towards a fresh air inlet portion of the gas turbine. As a consequence of the separation of the two divergent ventilation flows, the enclosure of the gas turbine is divided into two portions, a first portion or downstream portion of the gas turbine, this downstream portion surrounding the turbine, downstream the combustor, i.e. the hottest portion of the gas turbine and a second portion or upstream portion of the gas turbine, surrounding the compressor and the combustor of the gas turbine. The upstream portion of the gas turbine also includes the fuel supply line, the second ventilation flow drawing any possible fuel leak away from the hot portion of the gas turbine.
[0010] In another aspect, the subject matter disclosed herein concerns a method for ventilating a gas turbine package comprising an enclosure surrounding a gas turbine, the gas turbine including a compressor, a combustor and a turbine. The method comprises the steps of: splitting ventilation air inside the enclosure into two separate flows, namely a first ventilation flow and a second ventilation flow; directing the first ventilation flow towards a first portion of the enclosure, surrounding the turbine of the gas turbine, downstream the combustor, and directing the second ventilation flow towards the compressor of the gas turbine, upstream the combustor, and towards a fuel supply line through which a fuel stream is routed to the combustor.
[0011] A further aspect of the present disclosure is drawn to a gas turbine package ventilation system wherein the first and the second portions of the enclosure of the gas turbine are separated by separation means, dividing the enclosure into a first compartment, surrounding the gas turbine downstream the combustor, and a second compartment, upstream the first compartment, surrounding the combustor and the compressor of the gas turbine and also including the fuel supply line. The separation means can include a wall or a plate arranged between the first compartment and the second compartment.
[0012] A still further aspect of the present disclosure is drawn to a gas turbine package ventilation system comprising two perforated walls or plates arranged between the first compartment and the second compartment and defining an interspace. Ventilation air enters the interspace through a ventilation inlet and two separate flows, namely a first flow directed to the first compartment and a second flow directed to the second compartment exit the interspace through openings in each of the perforated walls or plates defining the interspace. In particular, ventilation air arriving from the ventilation inlet pressurizes the interspace, avoiding any possible reverse flow from one of the enclosure compartments to the interspace and to the other enclosure compartment.
BRIEF DESCRIPTION OF THE DRAWINGS
[0013] A more complete appreciation of the disclosed embodiments of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings, wherein:
Fig.1 illustrates a schematic of a gas turbine ventilation package including a ventilation air distribution system adapted to separate two divergent ventilation flows;
Fig.2 illustrates a schematic of a gas turbine ventilation package including a ventilation air distribution system and separation means of the gas turbine enclosure; Fig.3 illustrates a schematic of a gas turbine ventilation package including a ventilation air distribution system and separation means of the gas turbine enclosure defining a pressurized cavity mechanically separating the gas turbine enclosure into a first compartment and a second compartment; and
Fig.4 illustrates a flow chart of a method for ventilating a gas turbine package according to the present disclosure.
DETAILED DESCRIPTION OF EMBODIMENTS
[0014] According to one aspect, the present subject matter is directed to systems and methods for ventilating a gas turbine package and avoiding the risk of auto-ignition of a possible fuel leak as a consequence of the contact of the fuel with hot surfaces of the turbine portion of the gas turbine. Specifically, in several embodiments disclosed herein a ventilation system is provided, which includes a ventilation air distribution system adapted to split the ventilation air into two separate flows, respectively adapted to ventilate a gas turbine first portion, downstream the gas turbine combustor and a gas turbine second portion, upstream the first portion.
[0015] The gas turbine package ventilation system can additionally comprise separation means, for example a wall or a plate, to divide the enclosure into two separate compartments, respectively a first compartment, surrounding the gas turbine downstream the combustor, and a second compartment, surrounding the compressor and the combustor.
[0016] Reference now will be made in detail to embodiments of the disclosure, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the disclosure, not limitation of the disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the disclosure. Reference throughout the specification to "one embodiment" or "an embodiment" or “some embodiments” means that the particular feature, structure or characteristic described in connection with an embodiment is included in at least one embodiment of the subject matter disclosed. Thus, the appearance of the phrase "in one embodiment" or "in an embodiment" or "in some embodiments" in various places throughout the specification is not necessarily referring to the same embodiment(s). Further, the particular features, structures or characteristics may be combined in any suitable manner in one or more embodiments.
[0017] When introducing elements of various embodiments the articles “a”, “an”, “the”, and “said” are intended to mean that there are one or more of the elements. The terms “comprising”, “including”, and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements.
[0018] Referring now to the drawings, Fig.l shows a schematic of a gas turbine 10, surrounded by an enclosure 20. The gas turbine is comprised of a compressor 11, a combustor 12 and a compressor driving turbine 13. Air enters the compressor 11 through an air collector 14, or air inlet 14, and flows through the compressor 1 1 towards the combustor 12, while its pressure is increased. Inside the combustor 12, compressed air is mixed with a fuel gas (or vapor or droplets), entering the combustor 12 through a fuel supply line 15. The gas mixture of air and fuel is then ignited in the combustor 12, its temperature and pressure being additionally increased. The high temperature and high pressure combusted gas mixture enters the turbine 13, wherein its potential energy is exploited to produce kinetic energy, the exhaust gas is then collected through an exhaust gas collector 16 or exhaust gas outlet 16.
[0019] Always with reference to figure 1, in addition to the enclosure 20, the gas turbine package ventilation system includes two ventilation air inlet conduits 21, 22, namely a downstream ventilation air inlet conduit 21 and an upstream ventilation air inlet conduit 22. The downstream ventilation air inlet conduit 21 is arranged in a central portion of the gas turbine enclosure 20, downstream the combustor 12, and comprises a plurality of first openings 23 directed towards the exhaust gas outlet 16 of the gas turbine 10. The upstream ventilation air inlet conduit 22 is arranged in a central portion of the gas turbine enclosure 20, upstream the downstream ventilation air inlet conduit 21, and comprises a plurality of second openings 24 directed towards the air inlet 14 of the gas turbine 10. Finally, the gas turbine package ventilation system includes two ventilation air outlet conduits 25, 26, namely a downstream ventilation air outlet conduit 25 and an upstream ventilation air outlet conduit 26.
[0020] The gas turbine package ventilation system operates as follows. The ventila- tion air inside the enclosure 20 is splitted into two separate flows, namely a first ventilation flow or downstream ventilation flow and a second ventilation flow or upstream ventilation flow. The downstream ventilation flow is directed from a central portion of the enclosure 20, wherein it is conveyed through the downstream ventilation air inlet conduit 21, towards a downstream portion of the enclosure 20, surrounding the turbine 13, downstream the combustor 12, and towards the downstream ventilation air outlet conduit 25. The upstream ventilation flow is directed from a central portion of the enclosure 20, wherein it is conveyed through the upstream ventilation air inlet conduit 22, towards an upstream portion of the enclosure 20, surrounding the compressor 11, the combustor 12 and the fuel supply line 15, through which a fuel stream is routed to the combustor 12. Finally the upstream ventilation flow exits from the enclosure 20 through the upstream ventilation air outlet conduit 26.
[0021] As a consequence, any possible leak of fuel from the fuel supply line 15 is diluted and drawn upstream by the upstream ventilation flow. Therefore, any contact between the fuel and the turbine hot surfaces is prevented. The downstream ventilation flow is kept separate from the upstream ventilation flow, to ventilate the turbine. Moreover, any possible leakage of the fuel towards the downstream portion of the enclosure 20 is additionally diluted.
[0022] Possible alternative embodiments of the gas turbine ventilation system described with reference to figure 1 can include, for example, a system comprising only one ventilation air inlet conduit, which is arranged in a central portion of the gas turbine enclosure 20, downstream the combustor 12, and which comprises a plurality of downstream openings, i.e. openings directed towards the exhaust gas outlet 16 of the gas turbine 10 and a plurality of upstream openings, i.e. openings directed towards the fresh air inlet 14 of the gas turbine 10.
[0023] Another alternative embodiment can include two or more ventilation air inlet conduits, each conduit comprising both downstream openings and upstream openings, the ventilation air inlet conduits being arranged on different sides of the central portion of the gas turbine enclosure 20.
[0024] Still another alternative embodiment can include one ventilation air inlet conduit, comprising both downstream openings and upstream openings, which is arranged around the central portion of the gas turbine enclosure. In particular, such ventilation air inlet conduit can be arranged along a substantially circular path around the central portion of the gas turbine enclosure 20.
[0025] Another alternative embodiment can include two or more ventilation air inlet conduits, each conduit comprising both downstream openings and upstream openings and each conduit arranged around the central portion of the gas turbine, wherein the two or more ventilation air inlet conduits are arranged at different radial distances from a central axis of the gas turbine.
[0026] With continuing reference to Fig.1 , Fig.2 illustrates another embodiment of a ventilation system. The same reference numbers designate the same or corresponding parts, elements or components already illustrated in Fig.l and described above, and which will not be described again.
[0027] In particular, the ventilation system shown with reference to figure 2 includes a downstream ventilation air inlet conduit 21’ and an upstream ventilation air inlet conduit 22’, and a separation wall or plate 27 is arranged between the downstream ventilation air inlet conduit 21’ and the upstream ventilation air inlet conduit 22’. The separation plate 27 divides the enclosure 20’ into two separate compartments, a downstream compartment 28 and an upstream compartment 29. The embodiment shown with reference to figure 2 ensures an even better separation between any possible fuel leaks and the hot surfaces of the gas turbine. Preferably, the separation is further increased by maintaining the pressure inside the downstream compartment 28 higher than the pressure inside the upstream compartment 29.
[0028] Finally, with continuing reference to Figs 1 and 2, a further embodiment of a ventilation system is shown in Fig.3. The same reference numbers designate the same or corresponding parts, elements or components already illustrated in Fig. 1 and Fig.2 and described above, and which will not be described again.
[0029] In particular, the ventilation system shown with reference to figure 3 includes two perforated plates 30, 31 that are arranged in a central portion of the gas turbine enclosure 20”, downstream the combustor 12, namely a downstream perforated plate 30 and an upstream perforated plate 31. The perforated plates 30, 31 divide the enclosure 20” into a downstream compartment 28 and an upstream compartment 29. The perforated plates 30, 31 are spaced from each other, to define an interspace 32 between the downstream perforated plate 30 and the upstream perforated plate 31. The interspace 32 is connected with a ventilation air inlet 33. The downstream perforated plate 30 comprises a plurality of downstream openings 34 directed towards the downstream compartment 28 and the upstream perforated plate 31 comprises a plurality of upstream openings 35 directed towards the upstream compartment 29.
[0030] The gas turbine package ventilation system shown with reference to figure 3 operates as follows. The ventilation air entering the interspace 32 is splitted into two separate flows, namely a downstream ventilation flow and an upstream ventilation flow, by passing through the downstream openings 34 and the upstream openings 35. At the same time, the ventilation air inlet 33, the downstream openings 34 and the upstream openings 35 are dimensioned to ensure the pressure inside the interspace 32 is higher than the pressure inside the downstream compartment 28, so that any possible fuel leak from the fuel supply line 15 is prevented from entering the downstream compartment 28 and from contacting the hot surfaces of the turbine 13.
[0031] Fig. 4 shows a flowchart summarizing the method disclosed herein for ventilating a gas turbine package. In particular, the method shown with reference to figure 4 includes the steps of: splitting 40 ventilation air inside the enclosure 20 into two separate flows, namely a first ventilation flow and a second ventilation flow; directing 50 the first ventilation flow towards a first portion of the enclosure 20 or downstream portion of the enclosure 20, surrounding the turbine 13 of the gas turbine 10, downstream the combustor 12, and
- directing 60 the second ventilation flow towards a second portion of the enclosure 20 or upstream portion of the enclosure 20, surrounding the compressor 11 and the combustor 12 of the gas turbine 10, and a fuel supply line 15 through which a fuel stream is routed to the combustor 12.
[0032] In particular, the method can comprise a preliminary step of separating the enclosure into two separate compartments, a downstream compartment 28, surrounding the turbine 13 of the gas turbine 10, downstream the combustor 12, and an upstream compartment 29, surrounding the compressor 11 and the combustor 12 of the gas turbine 10, and the fuel gas supply line 15. [0033] Finally, according to the method for ventilating a gas turbine package disclosed herein, a step is provided of maintaining the pressure inside the hot compartment 28 higher than the pressure inside the cold compartment 29.
[0034] While the invention has been described in terms of various specific embodi- ments, it will be apparent to those of ordinary skill in the art that many modifications, changes, and omissions are possible without departing form the spirt and scope of the claims. In addition, unless specified otherwise herein, the order or sequence of any process or method steps may be varied or re-sequenced according to alternative embodiments. Barzand & Zanardo Roma S.p.A

Claims

1. Gas turbine package ventilation system comprising an enclosure (20; 20’; 20”) surrounding a gas turbine (10), the gas turbine (10) including, in the direction of flow: a fresh air inlet (14), a compressor (11), a combustor (12) with a fuel supply line (15), a compressor driving turbine (13) and an exhaust gas outlet (16), the enclosure (20; 20’; 20”) comprising a central portion, downstream the fuel supply line (15), an upstream portion surrounding the fresh air inlet (14), the compressor (11), the combustor (12) and the fuel supply line (15) and a downstream portion surrounding the compressor driving turbine (13) and the exhaust gas outlet (16), wherein at least one ventilation air inlet conduit (21, 22; 21’, 22’; 33) is arranged in the central portion of the enclosure (20; 20’; 20”), at least one upstream ventilation air outlet conduit (26) is arranged in the upstream portion of the enclosure (20; 20’; 20”) and at least one downstream ventilation air outlet conduit (25) is arranged in the downstream portion of the enclosure (20; 20’; 20”) and wherein a ventilation air distribution system is adapted to separate the ventilation air from the at least one ventilation air inlet conduit (21, 22; 21’, 22’; 33) into two divergent ventilation flows, a first ventilation flow, which flows through the downstream portion of the enclosure (20; 20’; 20”) from the central portion of the gas turbine (10) towards the exhaust gas outlet (16) of the gas turbine (10) and to the downstream ventilation air outlet conduit (25), and a second ventilation flow, which flows through the upstream portion of the enclosure (20; 20’; 20”) from a central portion of the gas turbine (10) towards a fresh air inlet (14) of the gas turbine (10) and to the upstream ventilation air outlet conduit (26).
2. Gas turbine package ventilation system according to claim 1, wherein the at least one ventilation air inlet conduit (21) comprises a plurality of first openings (23) directed towards the exhaust gas outlet (16) of the gas turbine (10) and a plurality of second openings (24) directed towards the fresh air inlet (14) of the gas turbine (10).
3. Gas turbine package ventilation system according to claim 2, wherein two or more ventilation air inlet conduits (21) are arranged on different sides of the central portion of the gas turbine (10).
4. Gas turbine package ventilation system according to claim 2, wherein the at least one ventilation air inlet conduit (21) is arranged around the central portion of the gas turbine (10).
5. Gas turbine package ventilation system according to claim 4, wherein the at least one ventilation air inlet conduit (21) is arranged along a substantially circular path around the central portion of the gas turbine (10).
6. Gas turbine package ventilation system according to claim 4 or 5, wherein two or more ventilation air inlet conduits (21) are arranged at different radial distances from a central axis of the gas turbine (10).
7. Gas turbine package ventilation system according to claim 1, wherein the ventilation air distribution system comprises at least a first ventilation air inlet conduit (21, 21’), or downstream ventilation air inlet conduit (21, 21 ’), and at least a second ventilation air inlet conduit (22, 22’), or upstream ventilation air inlet conduit (22, 22’), the downstream ventilation air inlet conduit (21, 21’) being arranged in a central portion of the gas turbine enclosure (20, 20’), downstream the fuel supply line (15), and comprising a plurality of first openings (23) directed towards the exhaust gas outlet (16) of the gas turbine (10), and the upstream ventilation air inlet conduit (22, 22’) being arranged in a central portion of the gas turbine enclosure (20, 20’), upstream the downstream ventilation air inlet conduit (21, 21’), and comprising a plurality of second openings (24) directed towards the fresh air inlet (14) of the gas turbine (10).
8. Gas turbine package ventilation system according to claim 7, wherein two or more downstream ventilation air inlet conduits (21, 21’) and two or more upstream ventilation air inlet conduits (22, 22’) are arranged on different sides of the central portion of the gas turbine enclosure (20, 20’).
9. Gas turbine package ventilation system according to claim 7, wherein the at least one downstream ventilation air inlet conduit (21, 21’) and the at least one upstream ventilation air inlet conduit (22, 22’) are arranged around the central portion of the gas turbine enclosure (20, 20’).
10. Gas turbine package ventilation system according to claim 9, wherein the at least one downstream ventilation air inlet conduit (21, 21’) and the at least one upstream ventilation air inlet conduit (22, 22’) are arranged along a respective substantially circular path around the central portion of the gas turbine enclosure (20, 20’).
11. Gas turbine package ventilation system according to claim 9 or 10, wherein two or more downstream ventilation air inlet conduits (21, 21’) and two or more upstream ventilation air inlet conduits (22, 22’) are arranged at different radial distances from a central axis of the gas turbine (20, 20’).
12. Gas turbine package ventilation system according to any of claims 7-11, wherein separation means (27) are arranged between said at least one downstream ventilation air inlet conduit (21’) and said at least one upstream ventilation air inlet conduit (22’), the separation means (27) dividing the enclosure (20’) into two separate compartments, a downstream compartment (28) and an upstream compartment (29).
13. Gas turbine package ventilation system according to claim 12, wherein said separation means (27) comprise a wall or a plate (27).
14. Gas turbine package ventilation system according to claim 12 or 13, wherein the pressure inside the downstream compartment (28) is higher than the pressure inside the upstream compartment (29).
15. Gas turbine package ventilation system according to claim 1, wherein two perforated walls or plates (30, 31) are arranged in a central portion of the gas turbine enclosure (20”), downstream the combustor (12), the perforated walls or plates (30, 31) comprising a downstream perforated wall or plate (30) and an upstream perforated wall or plate (31), the perforated walls or plates (30, 31) dividing the enclosure (20”) into two separate compartments (28, 29), a downstream compartment (28) and an upstream compartment (29), an interspace (32) being present between the downstream perforated wall or plate (30) and the upstream perforated wall or plate (31), the interspace (32) being connected with a ventilation air inlet (33) and the downstream perforated wall (30) comprising a plurality of downstream openings (34) directed towards the exhaust gas outlet (16) of the gas turbine (10) and the upstream perforated wall (31) comprising a plurality of upstream openings (35) directed towards the fresh air inlet (14) of the gas turbine (10).
16. Gas turbine package ventilation system according to claim 15, wherein the pressure inside the interspace (32) is higher than the pressure inside both the downstream compartment (28) and the upstream compartment (29).
17. Method for ventilating a gas turbine package comprising an enclosure (20, 20’, 20”) surrounding a gas turbine (10), the gas turbine (10) including, in the direction of flow: a fresh air inlet (14), a compressor (11), a combustor (12) with a fuel supply line (15), a compressor driving turbine (13) and an exhaust gas outlet (16), wherein the enclosure (20; 20’; 20”) comprises a central portion, downstream the fuel supply line (15), an upstream portion surrounding the fresh air inlet (14), the compressor (11), the combustor (12) and the fuel supply line (15) and a downstream portion surrounding the compressor driving turbine (13) and exhaust gas outlet (16) and wherein at least one ventilation air inlet conduit (21, 22; 21’, 22’; 33) is arranged in the central portion of the enclosure (20; 20’; 20”), at least one upstream ventilation air outlet conduit (26) is arranged in the upstream portion of the enclosure (20; 20’; 20”) and at least one downstream ventilation air outlet conduit (25) is arranged in the downstream portion of the enclosure (20; 20’; 20”), the method comprising the steps of: splitting (40) ventilation air inside the enclosure (20; 20’; 20”) into two separate flows, namely a first ventilation flow and a second ventilation flow; directing (50) the first ventilation flow towards the downstream portion of the enclosure (20; 20’; 20”), surrounding the compressor driving turbine (13) and the exhaust gas outlet (16) of the gas turbine (10), downstream the fuel supply line (15), and to the downstream ventilation air outlet conduit (25), and directing (60) the second ventilation flow towards the upstream portion of the enclosure (20; 20’; 20”), surrounding the fresh air inlet (14), the compressor (11), the combustor (12) of the gas turbine, and the fuel supply line (15) through which a fuel gas stream is routed to the combustor (12) and to the upstream ventilation air outlet conduit (26).
18. Method for ventilating a gas turbine package according to claim 17, comprising a preliminary step of: separating the enclosure (20’, 20”) into two separate compartments (28, 29), a downstream compartment (28), surrounding the turbine (13) of the gas turbine (10), downstream the combustor (12), and an upstream compartment (29), surrounding the compressor (11) and the combustor (12) of the gas turbine (10), and the fuel supply line (15).
19. Method for ventilating a gas turbine package according to claim 18, comprising a step of maintaining the pressure inside the downstream compartment (28) higher than the pressure inside the upstream compartment (29).
EP24708677.0A 2023-02-23 2024-02-22 A gas turbine package ventilation system and a method for ventilating a gas turbine package Pending EP4655494A1 (en)

Applications Claiming Priority (2)

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IT102023000003156A IT202300003156A1 (en) 2023-02-23 2023-02-23 VENTILATION SYSTEM OF A GAS TURBINE COMPLEX AND METHOD OF VENTILATION OF A GAS TURBINE COMPLEX
PCT/EP2024/025086 WO2024175253A1 (en) 2023-02-23 2024-02-22 A gas turbine package ventilation system and a method for ventilating a gas turbine package

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US10240484B2 (en) * 2015-11-06 2019-03-26 General Electric Company Gas accumulation detection and ventilation in a gas turbine enclosure
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