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

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 a flow direction, a compressor (11), a combustor (12), and a compressor-driven turbine (13), and a ventilation air distribution system adapted to separate two branch ventilation flows: a first ventilation flow flowing downstream from a central portion of the gas turbine (10) toward an exhaust gas outlet (16) of the gas turbine (10), and a second ventilation flow flowing upstream from the central portion of the gas turbine (10) toward an ambient air inlet (14) of the gas turbine (10).

Description

[Technical Field]

[0001] The present disclosure relates to a system and method for ventilating a gas turbine package, particularly a gas turbine package comprising a gas turbine including a compressor, a combustor, and a compressor-driven turbine, surrounded by an enclosure, wherein ventilation within the gas turbine enclosure is split into two separate flows, each venting a first portion of the gas turbine downstream of the combustion chamber and surrounding the turbine, and a second portion of the gas turbine upstream of the combustion chamber and surrounding the compressor, and also including a fuel gas supply line through which a fuel flow is delivered to the combustor. [Background technology]

[0002] In a gas turbine, atmospheric air is brought to a higher pressure by flowing through a rotary compressor, then mixed with fuel in a combustor and ignited, generating hot gases that enter the turbine and generate shaft work output, which is used to drive the rotary compressor. Unused energy appears in the exhaust gases, which can be reused for external work, such as spinning a fan, a propeller, or a second, independent turbine (known as a power turbine), which can be connected to an electrical generator.

[0003] Gas turbines are typically equipped with an enclosure slightly larger than the turbine itself to protect the surrounding environment from the heat and noise levels emitted by the turbine. However, this insulation maintains high temperatures within the enclosure, which can lead to overheating and malfunction of the gas turbine and ultimately to costly shutdowns. To ensure sufficient cooling of the gas turbine, a gas turbine enclosure ventilation system is typically used. The ventilation system also provides the ability to dilute any fuel leaks into the enclosure, which could create potentially explosive gas mixtures, by continuously purging areas where gases may accumulate and transporting the potentially explosive gas mixtures out of the enclosure. The presence of explosive gases, for example, caused by a leak in the gas turbine's fuel supply line piping, carries a significant risk of explosion because such explosive gases could come into contact with the hot surfaces of the gas turbine and autoignition of the gases could occur.

[0004] As a result, the configuration of compartment ventilation systems is a critical requirement in the gas turbine industry to minimize the risk of explosion.

[0005] Currently, current technology ventilation systems are based on the principle of diluting the concentration of any potentially explosive gases within the enclosure. Commonly used ventilation systems provide ventilation air that enters the enclosure from the same side as the air directed to the compressor and exits from the same side as the turbine exhaust, allowing the same air filters to be used for both air flows and requiring shorter pipes. This approach allows for dilution of potential fuel gas leaks. However, because the ventilation air flow travels from the compressor to the turbine, potential fuel leaks from the fuel supply line will be attracted to the turbine's hot surfaces, and the risk of self-ignition is reduced, but not eliminated, by dilution.

[0006] According to an alternative solution of the current state of the art, a ventilation system is provided in which ventilation air enters the enclosure from the exhaust gas outlet side of the gas turbine, i.e., the turbine section of the gas turbine, downstream of the combustion chamber, and exits the gas turbine from the ambient air inlet side, i.e., the compressor section of the gas turbine. This approach allows the ventilation air flow to attract possible fuel leakage from the fuel supply line to the compressor section of the gas turbine, whose surfaces are less hot than those of the turbine, thereby reducing the risk of contact between the fuel and the hot surfaces of the turbine. However, even this approach is not sufficient to completely eliminate the risk of contact between the fuel and the hot surfaces of the turbine.

[0007] Therefore, improved systems and methods for ventilating gas turbine enclosures to address the problem of contact between possible fuel leaks and the hot surfaces of the turbine and the subsequent risk of auto-ignition of current art systems would be beneficial and welcome in the art.

[0008] In particular, such improved systems and methods for ventilating gas turbine enclosures need to be more efficient than prior art systems and methods in order to be suitable for gas turbines that use hydrogen or other highly reactive gases as fuel, which carry a higher risk of auto-ignition of fuel leaks that come into contact with the hot surfaces of the gas turbine. In fact, hydrogen is now being used more frequently as a fuel in new or retrofit gas turbines that previously operated on different fuels. Summary of the Invention

[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 a flow direction, a compressor, a combustor, and a compressor-driven turbine. The ventilation air distribution system is adapted to separate two branch ventilation flows: a first ventilation flow flowing from a central portion of the gas turbine toward an exhaust gas outlet portion of the gas turbine and a second ventilation flow flowing from the central portion of the gas turbine toward an ambient air inlet portion of the gas turbine. As a result of the separation of the two branch ventilation flows, the gas turbine enclosure is divided into two portions: a first portion or downstream portion of the gas turbine that surrounds the turbine downstream of the combustor, i.e., the hottest portion of the gas turbine; and a second portion or upstream portion of the gas turbine that surrounds the compressor and combustor of the gas turbine. The upstream portion of the gas turbine also includes a fuel supply line, and the second ventilation flow directs any possible fuel leaks away from the hot portions of the gas turbine.

[0010] In another aspect, the subject matter disclosed herein relates to 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 comprising: - dividing the ventilation air in the enclosure into two separate flows, namely a first ventilation flow and a second ventilation flow; directing a first ventilation flow downstream of the combustor toward a first portion of an enclosure surrounding a turbine of the gas turbine; - directing the second ventilation flow upstream of the combustor towards a compressor of the gas turbine and towards a fuel supply line through which a fuel flow is delivered to the combustor.

[0011] A further aspect of the present disclosure relates to a gas turbine package ventilation system, wherein first and second portions of an enclosure of the gas turbine are separated by a separation means dividing the enclosure into a first section surrounding the gas turbine downstream of the combustor and a second section upstream of the first section surrounding the combustor and compressor of the gas turbine and also including a fuel supply line, The separation means may include a wall or plate disposed between the first section and the second section.

[0012] Yet another aspect of the present disclosure relates to a gas turbine package ventilation system including two perforated walls or plates disposed between a first compartment and a second compartment and defining a gap. Ventilation air enters the gap through a ventilation inlet and exits the gap with two separate flows, a first flow directed toward the first compartment and a second flow directed toward the second compartment, through openings in each of the perforated walls or plates defining the gap. In particular, the ventilation air arriving from the ventilation inlet pressurizes the gap and avoids any possible backflow from one of the enclosure compartments into the gap and into the other enclosure compartment. [Brief explanation of the drawings]

[0013] A more complete understanding of the disclosed embodiments of this invention and many of the attendant advantages thereof will be readily obtained as the same become better understood by reference to the following detailed description when considered in connection with the accompanying drawings. [Figure 1] 1 illustrates a schematic diagram of a gas turbine ventilation package including a ventilation air distribution system adapted to separate two branch ventilation flows. [Figure 2] 1 illustrates a schematic diagram of a gas turbine ventilation package including a ventilation air distribution system and a separation means for a gas turbine enclosure. [Figure 3]1 illustrates a schematic diagram of a gas turbine ventilation package including a ventilation air distribution system and a separation means of a gas turbine enclosure that defines a pressurized cavity that mechanically separates the gas turbine enclosure into a first compartment and a second compartment. [Figure 4] 1 illustrates a flow diagram of a method for ventilating a gas turbine package according to the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0014] According to one aspect, the present subject matter is directed to a system and method for ventilating a gas turbine package and avoiding the risk of possible auto-ignition of a fuel leak as a result of contact of the fuel with a hot surface of a turbine section of the gas turbine. Specifically, in some embodiments disclosed herein, a ventilation system is provided, the ventilation system including a ventilation air distribution system adapted to separate ventilation air into two separate flows, the two separate flows adapted to ventilate a first portion of the gas turbine downstream of a gas turbine combustor and a second portion of the gas turbine upstream of the first portion, respectively.

[0015] The gas turbine package ventilation system may additionally include a separating means, e.g., a wall or plate, for dividing the enclosure into two separate compartments: a first compartment surrounding the gas turbine downstream of the combustor, and a second compartment surrounding the compressor and combustor.

[0016] Reference will now be made in detail to the embodiments of the present disclosure, one or more examples of which are illustrated in the Figures. Each example is provided by way of explanation of the disclosure, not as a limitation of the disclosure. Indeed, 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. References throughout this specification to "one embodiment" or "an embodiment" or "some embodiments" mean that a particular feature, structure, or characteristic described in connection with an embodiment is included in at least one embodiment of the disclosed subject matter. Thus, the appearances of the phrases "in one embodiment," "in an embodiment," or "in some embodiments" in various places throughout the specification are not necessarily all referring to the same embodiment. Furthermore, particular features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0017] When presenting 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 non-exclusive and mean that there may be additional elements other than the listed elements.

[0018] Referring now to the drawings, FIG. 1 shows a schematic diagram of a gas turbine 10 surrounded by an enclosure 20. The gas turbine is composed of a compressor 11, a combustor 12, and a compressor-driven turbine 13. Air, increasing in pressure, enters the compressor 11 through an air collector 14 or air inlet 14 and flows through the compressor 11 toward a combustor 12. Inside the combustor 12, the compressed air is mixed with fuel gas (or steam or liquid droplets) that enters the combustor 12 through a fuel supply line 15. The air and fuel gas mixture is then ignited in the combustor 12, further increasing its temperature and pressure. The high-temperature, high-pressure combustion gas mixture enters the turbine 13, where its potential energy is utilized to generate kinetic energy, and the exhaust gases are then collected through an exhaust gas collector 16 or exhaust gas outlet 16.

[0019] 1 , in addition to the enclosure 20, the gas turbine package ventilation system includes two ventilation air inlet ducts 21, 22, namely, the downstream ventilation air inlet duct 21 and the upstream ventilation air inlet duct 22. The downstream ventilation air inlet duct 21 is located in a central portion of the gas turbine enclosure 20 downstream of the combustor 12 and includes a plurality of first openings 23 oriented toward the exhaust gas outlet 16 of the gas turbine 10. The upstream ventilation air inlet duct 22 is located in a central portion of the gas turbine enclosure 20 upstream of the downstream ventilation air inlet duct 21 and includes a plurality of second openings 24 oriented toward the air inlet 14 of the gas turbine 10. Finally, the gas turbine package ventilation system includes two ventilation air outlet ducts 25, 26, namely, the downstream ventilation air outlet duct 25 and the upstream ventilation air outlet duct 26.

[0020] The gas turbine package ventilation system operates as follows: ventilation air within the enclosure 20 is separated into two separate flows: a first or downstream ventilation flow and a second or upstream ventilation flow. The downstream ventilation flow is directed from a central portion of the enclosure 20 and conveyed through a downstream ventilation air inlet duct 21 toward a downstream portion of the enclosure 20 that surrounds the turbine 13 downstream of the combustor 12 and toward a downstream ventilation air outlet duct 25. The upstream ventilation flow is directed from the central portion of the enclosure 20 and conveyed through an upstream ventilation air inlet duct 22 toward an upstream portion of the enclosure 20 that surrounds the compressor 11, combustor 12, and fuel supply line 15 through which fuel flow is delivered to the combustor 12. Finally, the upstream ventilation flow exits the enclosure 20 through an upstream ventilation air outlet duct 26.

[0021] As a result, any possible leakage of fuel from the fuel supply line 15 is diluted by the upstream ventilation flow and drawn upstream, thus preventing any contact between the fuel and the turbine hot surfaces. The downstream ventilation flow is kept separate from the upstream ventilation flow and ventilates the turbine. Additionally, any possible leakage of fuel towards the downstream portion of the enclosure 20 is further diluted.

[0022] A possible alternative embodiment of the gas turbine ventilation system described with reference to FIG. 1 may include, for example, a system having only one ventilation air inlet duct located in a central portion of the gas turbine enclosure 20, downstream of the combustor 12, and having a plurality of downstream openings, i.e., openings directed toward the exhaust gas outlet 16 of the gas turbine 10, and a plurality of upstream openings, i.e., openings directed toward the fresh air inlet 14 of the gas turbine 10.

[0023] Another alternative embodiment may include two or more ventilation air inlet ducts, each duct having both a downstream opening and an upstream opening, with the ventilation air inlet ducts located on different sides of the central portion of the gas turbine enclosure 20.

[0024] Yet another alternative embodiment may include a single ventilation air inlet duct with both downstream and upstream openings, which is positioned about a central portion of the gas turbine enclosure. In particular, such a ventilation air inlet duct may be positioned along a substantially circular path about the central portion of the gas turbine enclosure 20.

[0025] Another alternative embodiment may include two or more ventilation air inlet ducts, each duct having both a downstream opening and an upstream opening, each duct positioned about a central portion of the gas turbine, and the two or more ventilation air inlet ducts positioned at different radial distances from a central axis of the gas turbine.

[0026] With continuing reference to Figure 1, Figure 2 illustrates another embodiment of a ventilation system. Like reference numerals represent the same or corresponding parts, elements, or components already illustrated in Figure 1 and described above, and will not be described again here.

[0027] In particular, the ventilation system shown with reference to Figure 2 includes a downstream ventilation air inlet duct 21' and an upstream ventilation air inlet duct 22', with a separation wall or plate 27 disposed between the downstream ventilation air inlet duct 21' and the upstream ventilation air inlet duct 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 even better isolation between any possible fuel leaks and the hot surfaces of the gas turbine. Preferably, this isolation is further increased by maintaining a higher pressure in the downstream compartment 28 than in the upstream compartment 29.

[0028] Finally, with continued reference to Figures 1 and 2, a further embodiment of a ventilation system is shown in Figure 3. Like reference numerals represent the same or corresponding parts, elements, or components already illustrated in Figures 1 and 2 and described above, and will not be described again here.

[0029] In particular, the ventilation system shown with reference to FIG. 3 includes two perforated plates 30, 31, namely, a downstream perforated plate 30 and an upstream perforated plate 31, located in a central portion of the gas turbine enclosure 20″, downstream of the combustor 12. The perforated plates 30, 31 divide the enclosure 20″ into a downstream section 28 and an upstream section 29. The perforated plates 30, 31 are spaced apart from one another to define a gap 32 between the downstream perforated plate 30 and the upstream perforated plate 31. The gap 32 is connected to a ventilation air inlet 33. The downstream perforated plate 30 includes a plurality of downstream openings 34 oriented toward the downstream section 28, and the upstream perforated plate 31 includes a plurality of upstream openings 35 oriented toward the upstream section 29.

[0030] The gas turbine package ventilation system shown with reference to Figure 3 operates as follows: ventilation air entering gap 32 is split into two separate flows, a downstream ventilation flow and an upstream ventilation flow, by passing through downstream opening 34 and upstream opening 35. At the same time, ventilation air inlet 33, downstream opening 34 and upstream opening 35 are sized to ensure that the pressure in gap 32 is higher than the pressure in downstream section 28, thereby preventing any possible fuel leakage from fuel supply line 15 from entering downstream section 28 and contacting the hot surface of turbine 13.

[0031] 4 illustrates a flow diagram summarizing the method disclosed herein for ventilating a gas turbine package. Specifically, the method illustrated with reference to FIG. 4 includes: - dividing (40) the ventilation air in the enclosure 20 into two separate flows, namely a first ventilation flow and a second ventilation flow; directing (50) a first ventilation flow downstream of the combustor 12 towards a first part of the enclosure 20 or a downstream part of the enclosure 20 surrounding the turbine 13 of the gas turbine 10; - Directing (60) the second ventilation flow towards a second portion of the enclosure 20 or an upstream portion of the enclosure 20 that surrounds the compressor 11 and combustor 12 of the gas turbine 10 and the fuel supply line 15 through which the fuel flow is delivered to the combustor 12.

[0032] In particular, the method may include a preliminary step of separating the enclosure into two separate sections: a downstream section 28 that surrounds the turbine 13 of the gas turbine 10 downstream of the combustor 12, and an upstream section 29 that surrounds the compressor 11 and combustor 12 of the gas turbine 10, as well as the fuel gas supply line 15.

[0033] Finally, the method of ventilating a gas turbine package disclosed herein provides for maintaining a pressure in the hot compartment 28 greater than the pressure in the cold compartment 29 .

[0034] While the present invention has been described in terms of various specific embodiments, it will be apparent to those skilled in the art that many modifications, changes, and omissions can be made therein without departing from the spirit and scope of the claims. Additionally, unless otherwise specified herein, the order or sequence of any process or method steps may be varied or rearranged according to alternative embodiments. Barzano & Zanardo Roma SpA.

Claims

1. 1. A gas turbine package ventilation system comprising an enclosure (20, 20', 20'') surrounding a gas turbine (10), the gas turbine (10) including, in a flow direction, an outside air inlet (14), a compressor (11), a combustor (12) having a fuel supply line (15), a compressor-driven turbine (13), and an exhaust gas outlet (16), the enclosure (20, 20', 20'') including a central portion downstream of the fuel supply line (15) and the outside air inlet (14), an upstream portion surrounding the compressor (11), the combustor (12) and the fuel supply line (15), and a downstream portion surrounding the compressor-driven 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''), and at least one upstream ventilation air outlet conduit (26) is arranged in the central portion of the enclosure (20, 20', 20''). , 20′, 20″) and at least one downstream ventilation air outlet duct (25) is arranged in the downstream part of the enclosure (20, 20′, 20″), and a ventilation air distribution system distributes ventilation air from the at least one ventilation air inlet duct (21, 22; 21′, 22′; 33) through the downstream part of the enclosure (20, 20′, 20″) into two branched ventilation flows, a first ventilation flow flowing from the central portion toward the exhaust gas outlet (16) of the gas turbine (10) to the downstream ventilation air outlet duct (25) and a second ventilation flow flowing through the upstream portion of the enclosure (20, 20', 20'') from the central portion of the gas turbine (10) toward a fresh air inlet (14) of the gas turbine (10) to the upstream ventilation air outlet duct (26).

2. 2. The gas turbine package ventilation system of claim 1, wherein the at least one ventilation air inlet conduit comprises a plurality of first openings directed toward the exhaust gas outlet of the gas turbine and a plurality of second openings directed toward the fresh air inlet of the gas turbine.

3. The gas turbine package ventilation system of claim 2, wherein two or more ventilation air inlet ducts (21) are located on different sides of the central portion of the gas turbine (10).

4. The gas turbine package ventilation system of claim 2, wherein the at least one ventilation air inlet conduit (21) is disposed about the central portion of the gas turbine (10).

5. 5. The gas turbine package ventilation system of claim 4, wherein the at least one ventilation air inlet conduit (21) is disposed along a substantially circular path around the central portion of the gas turbine (10).

6. 6. The gas turbine package ventilation system of claim 4 or 5, wherein two or more ventilation air inlet conduits (21) are located at different radial distances from a central axis of the gas turbine (10).

7. The ventilation air distribution system comprises at least a first ventilation air inlet duct (21, 21') or downstream ventilation air inlet duct (21, 21') and at least a second ventilation air inlet duct (22, 22') or upstream ventilation air inlet duct (22, 22'), the downstream ventilation air inlet duct (21, 21') being arranged in a central part of the gas turbine enclosure (20, 20') downstream of the fuel supply line (15), and the exhaust air of the gas turbine (10) being arranged in a central part of the gas turbine enclosure (20, 20').

2. The gas turbine package ventilation system of claim 1, wherein the upstream ventilation air inlet duct is arranged in a central portion of the gas turbine enclosure upstream of the downstream ventilation air inlet duct and comprises a plurality of second openings directed towards the outside air inlet of the gas turbine.

8. 8. The gas turbine package ventilation system of claim 7, wherein two or more downstream ventilation air inlet ducts (21, 21') and two or more upstream ventilation air inlet ducts (22, 22') are located on different sides of the central portion of the gas turbine enclosure (20, 20').

9. 8. The gas turbine package ventilation system of claim 7, wherein the at least one downstream ventilation air inlet duct (21, 21') and the at least one upstream ventilation air inlet duct (22, 22') are arranged around the central portion of the gas turbine enclosure (20, 20').

10. 10. The gas turbine package ventilation system of claim 9, wherein the at least one downstream ventilation air inlet duct (21, 21') and the at least one upstream ventilation air inlet duct (22, 22') are arranged along respective substantially circular paths around the central portion of the gas turbine enclosure (20, 20').

11. 11. The gas turbine package ventilation system of claim 9 or 10, wherein two or more downstream ventilation air inlet ducts (21, 21') and two or more upstream ventilation air inlet ducts (22, 22') are positioned at different radial distances from a central axis of the gas turbine (20, 20').

12. 12. The gas turbine package ventilation system of claim 7, wherein a separation means (27) is arranged between the at least one downstream ventilation air inlet duct (21') and the at least one upstream ventilation air inlet duct (22'), the separation means (27) dividing the enclosure (20') into two separate compartments, a downstream compartment (28) and an upstream compartment (29).

13. The gas turbine package ventilation system of claim 12, wherein the separating means (27) comprises a wall or plate (27).

14. 14. A gas turbine package ventilation system according to claim 12 or 13, wherein the pressure in the downstream section (28) is greater than the pressure in the upstream section (29).

15. Two perforated walls or plates (30, 31) are arranged in a central portion of the gas turbine enclosure (20'') downstream of 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 sections (28, 29), the downstream section (28) and the upstream section (29), and a gap (32) separating the downstream perforated wall or plate 2. The gas turbine package ventilation system of claim 1, wherein a gap (32) exists between a downstream perforated wall or plate (31) and the upstream perforated wall (30), the gap (32) being connected to a ventilation air inlet (33), the downstream perforated wall (30) comprising a plurality of downstream openings (34) oriented towards the exhaust gas outlet (16) of the gas turbine (10), and the upstream perforated wall (31) comprising a plurality of upstream openings (35) oriented towards the fresh air inlet (14) of the gas turbine (10).

16. The gas turbine package ventilation system of claim 15, wherein the pressure in the gap (32) is greater than the pressure within both the downstream section (28) and the upstream section (29).

17. 1. A method for ventilating a gas turbine package comprising an enclosure (20, 20', 20'') surrounding a gas turbine (10), the gas turbine (10) including, in a flow direction, an outside air inlet (14), a compressor (11), a combustor (12) having a fuel supply line (15), a compressor-driven turbine (13), and an exhaust gas outlet (16), the enclosure (20, 20', 20'') surrounding a downstream central portion of the fuel supply line (15), the outside air inlet (14), the compressor (11), the combustor (12), and the fuel supply line (15). a central portion of the enclosure (20, 20', 20'') and a downstream portion surrounding the compressor-driven turbine (13) and the exhaust gas outlet (16), wherein at least one ventilation air inlet duct (21, 22; 21', 22'; 33) is arranged in the central portion of the enclosure (20, 20', 20''), at least one upstream ventilation air outlet duct (26) is arranged in the upstream portion of the enclosure (20, 20', 20''), and at least one downstream ventilation air outlet duct (25) is arranged in the downstream portion of the enclosure (20, 20', 20''), the method comprising: - dividing (40) the ventilation air in said enclosure (20, 20', 20'') into two separate flows, namely a first ventilation flow and a second ventilation flow; - directing (50) said first ventilation flow downstream of said fuel supply line (15) towards said downstream part of said enclosure (20, 20', 20'') surrounding said compressor-driven turbine (13) and an exhaust gas outlet (16) of said gas turbine (10) and into said downstream ventilation air outlet conduit (25); and directing (60) said second ventilation flow towards the upstream part of said enclosure (20, 20', 20'') surrounding said fresh air inlet (14) of said gas turbine, said compressor (11), said combustor (12) and said fuel supply line (15) through which a fuel gas flow is delivered to said combustor (12), and into said upstream ventilation air outlet conduit (26).

18. 18. The method for ventilating a gas turbine package according to claim 17, comprising a preliminary step of separating the enclosure (20', 20'') into two separate sections (28, 29), a downstream section (28) downstream of the combustor (12) and surrounding the turbine (13) of the gas turbine (10), and an upstream section (29) surrounding the compressor (11) and the combustor (12) of the gas turbine (10) and the fuel supply line (15).

19. 20. A method for ventilating a gas turbine package according to claim 18, comprising maintaining a pressure in the downstream section (28) greater than a pressure in the upstream section (29).

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