WO2021049051A1

WO2021049051A1 - Gas turbine

Info

Publication number: WO2021049051A1
Application number: PCT/JP2020/001803
Authority: WO
Inventors: 真治藤田; 敏史貫野; 浩平羽田野; 石川　博司; 光黒崎
Original assignee: 三菱重工業株式会社
Priority date: 2019-09-11
Filing date: 2020-01-21
Publication date: 2021-03-18
Also published as: JP2021042714A

Abstract

This gas turbine is provided with: a gas turbine cabin through the inside of which a working fluid flows; and a heat conductive member which is formed from a material having a higher heat conduction than the gas turbine cabin, and which is embedded into the gas turbine cabin in such a way that only a portion thereof comes into contact with the working fluid. Heat in the working fluid propagates to the heat conductive member through said portion. The heat subsequently propagates to other parts of the gas turbine cabin through the heat conductive member. As a result, temperature gradients arising between a plurality of regions of the gas turbine cabin can be made gentle. In this way, thermal stresses generated in the gas turbine cabin can be alleviated, and the possibility of gaps arising between flanges provided along the outer surface of the gas turbine cabin can be reduced.

Description

gas turbine

The present disclosure relates to gas turbines.
The present application claims priority based on Japanese Patent Application No. 2019-165505 filed in Japan on September 11, 2019, the contents of which are incorporated herein by reference.

The gas turbine is equipped with a compressor, a combustor, and a turbine. The compressor compresses the outside air to produce high pressure air. The combustor mixes fuel with high-pressure air and burns it to generate high-temperature solid-pressure combustion gas. The turbine is rotationally driven by the combustion gas. Further, the passenger compartment (casing) of the compressor and the passenger compartment of the turbine are integrally connected to form a gas turbine passenger compartment. The combustor is installed between the compressor cabin and the turbine cabin.

During operation of the gas turbine, high-temperature working fluid flows along the inner surface of the gas turbine cabin. In particular, a working fluid of about 1500 ° C. flows on the downstream side of the combustor as an example. Therefore, in the region extending from the compressor cabin to the turbine casing, a temperature gradient is formed with the downstream portion of the combustor (turbine inlet) as the apex. In order to improve the performance of the gas turbine, it is important to raise the temperature of the working fluid at the turbine inlet.

On the other hand, when the above-mentioned temperature gradient is formed, a difference in thermal deformation (thermal strain) occurs between each region. As a result, there is a possibility that a gap may be generated between the flanges provided along the outer surface of the gas turbine vehicle interior, or a large thermal stress may be generated in the vicinity of the flange.

Therefore, for example, as described in Patent Document 1 below, a technique has been proposed in which the outer surface of a gas turbine is covered with a heat conductive member such as graphene to promote heat transfer and make the temperature gradient gentle.

JP-A-2017-129132

However, in the apparatus described in Patent Document 1, the heat conductive member merely covers the outer surface of the gas turbine. Therefore, the heat of the working fluid is not positively transferred to the heat conductive member. As a result, a steep temperature gradient is still formed in the gas turbine cabin. This may hinder the stable operation of the gas turbine.

The present disclosure has been made to solve the above problems, and an object of the present disclosure is to provide a gas turbine capable of more stable operation.

In order to solve the above problems, the gas turbine according to the present disclosure is formed of a gas turbine casing in which a working fluid flows inside and a material having a higher thermal conductivity than that of the gas turbine casing, and only a part of the gas turbine is formed. A heat conductive member embedded in the interior of the gas turbine vehicle so as to come into contact with the working fluid is provided.

According to the present disclosure, it is possible to provide a gas turbine capable of more stable operation.

It is a schematic diagram which shows the structure of the gas turbine which concerns on 1st Embodiment of this disclosure. It is sectional drawing of the gas turbine vehicle interior which concerns on 1st Embodiment of this disclosure as seen from the axial direction. It is sectional drawing of the gas turbine vehicle interior which concerns on 1st Embodiment of this disclosure as seen from the circumferential direction. It is sectional drawing of the gas turbine vehicle interior which concerns on 2nd Embodiment of this disclosure as seen from the axial direction. It is sectional drawing of the gas turbine vehicle interior which concerns on 3rd Embodiment of this disclosure as seen from the axial direction. It is sectional drawing of the gas turbine vehicle interior which concerns on 4th Embodiment of this disclosure as seen from the axial direction. It is sectional drawing which shows the attachment structure of the outer surface heat conduction member which concerns on 4th Embodiment of this disclosure.

Hereinafter, embodiments to which the present invention has been applied will be described in detail with reference to the drawings.
<First Embodiment>
Hereinafter, the gas turbine 100 according to the first embodiment of the present disclosure will be described with reference to FIGS. 1 to 3. As shown in FIG. 1 or 2, the gas turbine 100 includes a compressor 1, a combustor 2, a turbine 3, and a heat conductive member M (see FIG. 2).

Compressor 1 takes in outside air and compresses it to generate high-pressure air. The compressor 1 has a compressor rotor 11 extending along the axis O, and a tubular compressor cabin 12 that covers the compressor rotor 11 from the outer peripheral side. A plurality of combustors 2 are attached to a portion on the downstream side of the compressor cabin 12. The combustor 2 mixes fuel with the high-pressure air supplied from the compressor 1 and burns the fuel to generate high-temperature and high-pressure combustion gas. A turbine 3 is provided on the downstream side of the combustor 2. The turbine 3 is rotationally driven by the combustion gas. The turbine 3 has a turbine rotor 31 extending along the axis O, and a tubular turbine casing 32 that covers the turbine rotor 31 from the outer peripheral side.

The compressor rotor 11 and the turbine rotor 31 are integrally connected on the axis O to form the gas turbine rotor 90 (rotor). Similarly, the compressor casing 12 and the turbine casing 32 are coaxially connected with the axis O as the center to form the gas turbine casing 91. The gas turbine rotor 90 can rotate integrally around the axis O inside the gas turbine casing 91.

Next, the configuration of the gas turbine passenger compartment 91 will be described in detail. The gas turbine casing 91 is divided into two portions (upper half passenger compartment U and lower half passenger compartment L) in a horizontal plane including the axis O. The upper half-chamber U has a semi-cylindrical upper half-chamber main body Uh and a flange F (upper half flange Fu) integrally formed with the upper half-chamber main body Uh. The upper half passenger compartment main body Uh has a semi-cylindrical shape that is convex upward. That is, the upper half passenger compartment main body Uh opens downward. The upper half flange Fu has a plate shape extending in a horizontal plane along the edge of the opening in the upper half passenger compartment main body Uh.

The lower half-chamber L has a semi-cylindrical lower half-chamber main body Lh and a flange F (lower half flange Fl) integrally formed with the lower half-chamber main body Lh. The lower half-cabin body Lh has a semi-cylindrical shape that is convex downward. That is, the lower half passenger compartment main body Lh opens downward. The lower half flange Fl has a plate shape extending in a horizontal plane along the edge of the opening in the lower half passenger compartment main body Lh. The gas turbine casing 91 forms an integral cylindrical shape by aligning (contacting) the flanges F with each other in a horizontal plane. Specifically, as shown in FIG. 2, the upper half-chamber U and the lower half-chamber L are connected to each other by inserting the bolt B into the through holes formed in the upper half flange Fu and the lower half flange Fl. Will be done.

As shown in FIGS. 2 and 3, a heat conductive member M is sandwiched between the upper half flange Fu and the lower half flange Fl. As shown in FIG. 2, an upper half recess R1 recessed upward is formed on the lower surface of the upper half flange Fu, and a lower half recess R2 recessed downward is formed on the upper surface of the lower flange Fl. ing. A plate-shaped heat conductive member M is embedded in the space defined by the upper half recess R1 and the lower half recess R2.

Further, as shown in FIG. 3, a part of the heat conductive member M is exposed inside the gas turbine casing 91 to form an exposed portion P. The heat of the working fluid flowing inside the gas turbine casing 91 propagates to the entire heat conductive member M through the exposed portion P. The portion other than the exposed portion P is embedded inside the upper half flange Fu or the lower half flange Fl. Further, the heat conductive member M extends in the axis O direction as a whole. That is, the heat input to the heat conductive member M through the exposed portion P propagates in the axis O direction through the heat conductive member M.

Further, the exposed portion P is in contact with the working fluid in a relatively high temperature region in the gas turbine cabin 91. As an example, it is desirable that the exposed portion P is arranged on the downstream side of the combustor 2 (that is, the inlet of the turbine 3) in the gas turbine cabin 91. It is desirable that the other parts of the heat conductive member M other than the exposed part P are buried in a relatively low temperature region in the gas turbine vehicle interior 91.

The heat conductive member M is made of a material having a higher thermal conductivity than the material forming the gas turbine passenger compartment 91. Specifically, graphene, a composite material containing carbon and copper, and a composite material containing copper and diamond are preferably used as such a material. These materials can be molded into a plate shape and exhibit a relatively high thermal conductivity.

(Action effect)
Next, the operation of the gas turbine 100 will be described. In operating the gas turbine 100, first, the gas turbine rotor 90 is rotationally driven by an external power source (electric motor or the like). As the gas turbine rotor 90 rotates, the compressor 1 takes in outside air to generate high-pressure air. The combustor 2 mixes fuel with this high-pressure air and burns it to generate high-temperature and high-pressure combustion gas. The turbine 3 is rotationally driven by this combustion gas. The continuous occurrence of such a cycle causes the gas turbine 100 to operate. The rotational energy of the gas turbine rotor 90 is taken out from the shaft end and used for driving a generator or the like, for example.

Here, during the operation of the gas turbine 100, a high-temperature working fluid flows along the inner surface of the gas turbine cabin 91. In particular, a working fluid of about 1500 ° C. flows on the downstream side of the combustor 2 as an example. Therefore, in the region extending from the compressor cabin 12 to the turbine casing 32, a temperature gradient is formed with the downstream portion (turbine inlet) of the combustor 2 as the apex. In order to improve the performance of the gas turbine 100, it is important to raise the temperature of the working fluid at the turbine inlet.

Therefore, in the present embodiment, the heat conductive member M is provided inside the gas turbine casing 91. Further, the exposed portion P, which is a part of the heat conductive member M, is in contact with the working fluid. Therefore, the heat of the working fluid propagates to the heat conductive member M through the exposed portion P. After that, the above heat propagates to other parts of the gas turbine casing 91 through the heat conductive member M. As a result, the temperature gradient generated between the plurality of regions in the gas turbine passenger compartment 91 can be made gentle. As a result, the thermal stress generated in the gas turbine passenger compartment 91 can be relaxed. Therefore, the gas turbine 100 can be operated more stably.

Here, in the gas turbine 100, the temperature of the working fluid changes along the axis O. According to the above configuration, since the heat conductive member M extends in the axis O direction, the temperature gradient due to the temperature difference of the working fluid in the axis O direction can be made gentle.

According to the above configuration, since the heat conductive member M is sandwiched between the flanges F, the temperature gradient in the extending region of the flange F can be made gentle. On the other hand, when the heat conductive member M is not provided, a steep temperature gradient is formed in the extending region of the flange F, and as a result, a gap based on the difference in the amount of thermal deformation is generated between the flanges F. There is a risk that it will end up. However, according to the above configuration, the possibility of such thermal deformation occurring can be reduced.

According to the above configuration, heat in a relatively high temperature region can be propagated to a relatively low temperature region through a part of the heat conductive member M (exposed portion P). For example, the position of the downstream side (inlet of the turbine) of the combustor 2 in the gas turbine cabin 91 corresponds to this as a high temperature region, and the outlet side of the turbine 3 and the inlet side of the compressor 1 correspond to this as a low temperature region. ..

<Second embodiment>
Next, the second embodiment of the present disclosure will be described with reference to FIG. The same components as those in the first embodiment are designated by the same reference numerals, and detailed description thereof will be omitted. As shown in the figure, in the present embodiment, the configuration of the heat conductive member Mt is different from that of the first embodiment.

The heat conductive member M is arranged in a through hole H for inserting a bolt B formed in the flange F (upper half flange Fu, lower half flange Fl). The heat conductive member Mt has a cylindrical shape extending along the inner peripheral surface of the through hole H. The outer peripheral surface of the heat conductive member Mt is in contact with the inner peripheral surface of the through hole H without a gap. That is, the outer diameter dimension of the heat conductive member Mt is set to the same value as or slightly smaller than the inner diameter dimension of the through hole H. At the lower end of the through hole H, a protruding portion Pr that protrudes toward the inner peripheral side is formed. The heat conductive member Mt is supported by the protruding portion Pr so as not to fall off from below. In this embodiment, a gap is formed between the inner peripheral surface of the heat conductive member Mt and the outer peripheral surface of the bolt B. On the other hand, it is also possible to adopt a configuration that does not form this gap.

Further, an upper half recess R1 that is recessed upward is formed on the lower surface of the upper half flange Fu, and a lower half recess R2 that is recessed downward is formed on the upper surface of the lower half flange Fl. When the upper half flange Fu and the lower half flange Fl are combined, a gap G is formed by the upper half recess R1 and the lower half recess R2. The gap G communicates the inside of the gas turbine casing 91 with the outer peripheral surface of the heat conductive member Mt. That is, a part of the working fluid comes into contact with the heat conductive member Mt through this gap G.

According to the above configuration, the tubular heat conductive member Mt is inserted into the through hole H of the flange F. As a result, heat transfer between the flanges F is promoted, and the temperature gradient formed between the flanges F can be made gentle. On the other hand, if the heat conductive member Mt is not provided, a steep temperature gradient is formed between the flanges F, and as a result, a gap based on the difference in the amount of thermal deformation may occur between the flanges F. There is. However, according to the above configuration, the possibility of such thermal deformation occurring can be reduced.

Further, according to the above configuration, a gap is formed between the heat conductive member Mt and the bolt B. As a result, the heat propagated from the working fluid to the heat conductive member Mt can be propagated only to the flange F without propagating to the bolt B. As a result, the temperature gradient between the flanges F can be made gentle.

<Third Embodiment>
Subsequently, the third embodiment of the present disclosure will be described with reference to FIG. The same components as those in the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. As shown in the figure, in the present embodiment, in addition to the heat conductive member M described in the first embodiment, an outer heat conductive member Mb is further provided on the outer surface of the gas turbine casing 91 (flange F). ..

The outer heat conductive member Mb has a plate shape extending from the upper half flange Fu to the lower half flange Fl. The outer heat conductive member Mb is in contact with the outer surface (the surface facing the horizontal direction) of these flanges F without a gap. Further, the outer heat conductive member Mb extends in the axis O direction along the outer surface. That is, the heat conductive member Mb extends to a relatively high temperature region and a relatively low temperature region in the gas turbine casing 91. As an example, it is desirable that one end of the outer heat conductive member Mb in the axis O direction is arranged on the downstream side of the combustor 2 (that is, the inlet of the turbine 3) in the gas turbine cabin 91.

According to the above configuration, heat can be transferred from the high temperature region to the low temperature region of the gas turbine cabin 91 by the outer surface heat conductive member Mb. As a result, the temperature gradient generated in the gas turbine passenger compartment 91 can be made even gentler.

<Fourth Embodiment>
Next, the fourth embodiment of the present disclosure will be described with reference to FIGS. 6 and 7. The same components as those in the above embodiments are designated by the same reference numerals, and detailed description thereof will be omitted. As shown in FIG. 6, in the present embodiment, in addition to the heat conductive member M described in the first embodiment, a connecting heat conductive member Mc is further provided on the outer surface of the gas turbine vehicle interior 91.

The connecting heat conductive member Mc is between the upper half-chamber body Uh and the upper half flange Fu facing upward, and between the lower half-chamber body Lh and the lower half-chamber Fl, respectively. It is provided. Each connecting heat conductive member Mc has an arcuate cross section when viewed from the axis O direction. That is, a space V for accommodating the bolt B is formed on the inner peripheral side of the connecting heat conductive member Mc. Further, although not shown in detail, the connection heat conductive member Mc is formed with an opening for allowing a tool or the like to reach the bolt B.

Further, as shown in FIG. 7, the connecting heat conductive member Mc is fixed to the flange F together with the bolt B by the fixture J. The fixture J has a first portion J1 extending in the vertical direction, a second portion J2 extending in the radial direction with respect to the axis O, and a third portion J3 connecting the first portion J1 and the second portion J2. There is. The upper end of the first part J1 is embedded in the vicinity of the upper end of the connecting heat conductive member Mc. The radial outer end of the second portion J2 is embedded near the lower end of the connecting heat conductive member Mc. A hole through which the bolt B can be inserted is formed in the third portion J3. Therefore, by tightening the bolt B with the third portion sandwiched between the bolt B and the flange F, the connecting heat conductive member Mc and the fixture J are fixed to the flange F.

Generally, the flange F has a larger wall thickness than other parts in the gas turbine passenger compartment 91. Therefore, when the operation of the gas turbine 100 is started, the temperature of the other portion rises before the flange F. According to the above configuration, the connection heat conductive member Mc promotes the transfer of heat from the upper half-chamber U or the lower half-chamber L toward the flange F. Thereby, the temperature gradient between the flange F and the other portion can be made gentle.

The embodiments of the present disclosure have been described above. It is possible to make various changes and modifications to the above configuration as long as it does not deviate from the gist of the present disclosure.

<Additional notes>
The gas turbine described in each embodiment is grasped as follows, for example.

(1) The gas turbine 100 according to the first aspect is formed of a gas turbine casing 91 in which a working fluid flows inside and a material having a higher thermal conductivity than that of the gas turbine casing 91, and only a part of the gas turbine 100 is formed. A heat conductive member M embedded inside the gas turbine casing 91 so as to come into contact with the working fluid is provided.

According to the above configuration, a heat conductive member is provided inside the gas turbine passenger compartment 91. Further, a part of the heat conductive member M is in contact with the working fluid. Therefore, the heat of the working fluid propagates to the heat conductive member M via the part thereof. After that, the above heat propagates to other parts of the gas turbine casing 91 through the heat conductive member M. As a result, the temperature gradient generated between the plurality of regions in the gas turbine passenger compartment 91 can be made gentle. As a result, the thermal stress generated in the gas turbine passenger compartment 91 can be relaxed.

(2) The gas turbine 100 according to the second aspect further includes a rotor 90 rotatably provided around the axis O inside the gas turbine casing 91, and the heat conductive member M is the gas turbine vehicle. Inside the chamber 91, it extends in the direction of the axis O.

In the gas turbine 100, the temperature of the working fluid changes along the axis O of the rotor 90. According to the above configuration, since the heat conductive member M extends in the axis O direction, the temperature gradient due to the temperature difference of the working fluid in the axis O direction can be made gentle.

(3) In the gas turbine 100 according to the third aspect, the gas turbine casing 91 has an upper half casing U and a lower half casing L that are coupled by aligning flanges F with each other, and the heat. The conductive member M is sandwiched between the flanges F.

(4) In the gas turbine 100 according to the fourth aspect, the part of the heat conductive member M comes into contact with the working fluid in a relatively high temperature region in the gas turbine cabin 91, and the heat conductive member The other part of M is buried in a relatively low temperature region in the gas turbine cabin 91.

According to the above configuration, heat in a relatively high temperature region can be propagated to a relatively low temperature region through a part of the heat conductive member M. For example, the position of the downstream side (inlet of the turbine 3) of the combustor 2 in the gas turbine cabin 91 corresponds to this as a high temperature region, and the outlet side of the turbine 3 and the inlet side of the compressor correspond to this as a low temperature region. ..

(5) In the gas turbine 100 according to the fifth aspect, the gas turbine casing 91 has an upper half casing U and a lower half casing L that are coupled by aligning flanges F with each other, and has the heat. The conductive member Mt has a tubular shape that penetrates the pair of flanges F in the vertical direction and extends along the inner peripheral surface of the through hole H through which the bolt B is inserted, and is a part between the flanges F. A gap G is formed in the region of the above to communicate the inside of the gas turbine casing 91 and the outer peripheral surface of the heat conductive member Mt.

(6) In the gas turbine according to the sixth aspect, a gap is formed between the inner peripheral surface of the heat conductive member Mt and the outer peripheral surface of the bolt B.

According to the above configuration, the heat propagated from the working fluid to the heat conductive member Mt can be propagated only to the flange F without propagating to the bolt B. As a result, the temperature gradient between the flanges F can be made gentle.

(7) The gas turbine 100 according to the seventh aspect is provided on the outer surface of the gas turbine cabin 91, and extends from a relatively high temperature region to a relatively low temperature region in the gas turbine casing 91. A heat conductive member Mb is further provided.

(8) In the gas turbine 100 according to the eighth aspect, the gas turbine casing 91 has an upper chassis U and a lower chassis L which are coupled by matching flanges F to each other, and the above A connecting heat conductive member Mc extending from at least one outer surface of the half-chamber U and the lower half-chamber L to the flange F is further provided.

The present invention is applicable to gas turbines.

100 Gas Turbine 1 Compressor 2 Combustor 3 Turbine 11 Compressor Rotor 12 Compressor Car Room 31 Turbine Rotor 32 Turbine Car Room 90 Gas Turbine Rotor 91 Gas Turbine Car Room B Bolt F Flange Fl Lower Half Flange Fu Upper Half Flange G Gap H Through hole J Fixture J1 1st part J2 2nd part J3 3rd part L Lower half-chamber Lh Lower half-chamber body M, Mt Heat-conducting member Mb Outer heat-conducting member Mc Connection heat-conducting member O Axis P Exposed part Pr Projection Part R1 First recess R2 Second recess U Upper cab Uh Upper cab body V space

Claims

The gas turbine cabin where the working fluid flows inside, and
A gas turbine including a heat conductive member formed of a material having a higher thermal conductivity than that of the gas turbine vehicle interior and embedded in the gas turbine vehicle interior so that only a part of the material comes into contact with the working fluid.
Further, a rotor provided so as to be rotatable around the axis inside the gas turbine cabin is provided.
The gas turbine according to claim 1, wherein the heat conductive member extends in the axial direction inside the gas turbine vehicle interior.
The gas turbine cabin has an upper and lower cabins that are joined together by fitting flanges to each other.
The gas turbine according to claim 1 or 2, wherein the heat conductive member is sandwiched between the flanges.
The part of the heat conductive member comes into contact with the working fluid in a relatively hot region in the gas turbine cabin, and the other part of the heat conductive member is relatively cold in the gas turbine cabin. The gas turbine according to any one of claims 1 to 3, which is embedded in the area.
The gas turbine cabin has an upper and lower cabins that are joined together by fitting flanges to each other.
The heat conductive member has a tubular shape that penetrates the pair of flanges in the vertical direction and extends along the inner peripheral surface of the through hole through which a bolt is inserted.
The gas turbine according to claim 1, wherein a gap is formed in a part of the region between the flanges so as to communicate the inside of the gas turbine casing and the outer peripheral surface of the heat conductive member.
The gas turbine according to claim 5, wherein a gap is formed between the inner peripheral surface of the heat conductive member and the outer peripheral surface of the bolt.
Any one of claims 1 to 6, further comprising an outer heat conductive member provided on the outer surface of the gas turbine cabin and extending over a relatively high temperature region and a relatively low temperature region in the gas turbine casing. The gas turbine described in.
The gas turbine cabin has an upper and lower cabins that are joined together by fitting flanges to each other.
The gas turbine according to any one of claims 1 to 7, further comprising a connecting heat conductive member extending from the outer surface of at least one of the upper half passenger compartment and the lower half passenger compartment to the flange.