JP2011516780A - Turbine equipment - Google Patents

Abstract

  The present invention relates to a method for changing a gas turbine engine 37 to a turbine engine 33 equipped with a combined gas / steam turbine apparatus. The invention also relates to an improvement on a turbine device 1, in particular turbine blades 7, 17, 9, 19, comprising a gas turbine part 2 and a steam turbine part 4 arranged coaxially. Furthermore, a method for adjusting a turbine engine comprising such a turbine arrangement is proposed.

Description

  The present invention relates to an improvement in a turbine apparatus that includes a gas turbine portion and a steam turbine portion arranged coaxially. The invention further relates to a method for regulating a turbine engine comprising such a turbine arrangement.

  Gas turbine engines are used in many situations to convert the chemical energy of a fuel into mechanical energy. In this case, the gas turbine is driven by a gas flow generated by the combustion of fuel. A gas turbine typically drives a compressor, compresses air, and supplies a greater amount of oxygen to the combustion chamber.

  In general, an advantage of a gas turbine engine is that the engine can deliver high power at low weight. Conventionally, there is a drawback that the efficiency, that is, the utilization rate of chemical energy of fuel is low.

  A highly efficient turbine arrangement comprising a coaxial gas turbine part and a steam turbine part is known from Swedish patent SE530142C2, US provisional patent application 60/969997 and PCT application PCT / SE2008 / 050258.

  As described in the prior art described above, such turbine equipment can replace conventional turbines in many applications. When existing gas turbine engines are modified to install turbine equipment with coaxial gas turbine and steam turbine sections, certain design considerations are taken into account to maximize utilization. There must be.

Swedish patent SE530142C2 US Provisional Patent Application No. 60/969997 PCT Application No. PCT / SE2008 / 050258

  It is an object of the present invention to provide a method for optimizing an improved turbine engine in a turbine arrangement that includes a coaxially arranged gas turbine portion and a steam turbine portion.

  This object is achieved by a method of changing a gas turbine engine to a turbine engine with a combined gas / steam turbine arrangement. Here, the gas turbine engine includes a compressor, a combustion chamber supplied with air from the compressor, a compression turbine, and a power turbine. The compression turbine drives the compressor and the output turbine provides power. A compression turbine is a gas turbine that includes a plurality of gas stages. Upon modification, the compression turbine is replaced with a turbine arrangement that includes a gas turbine portion and a steam turbine portion. The gas turbine portion and the steam turbine portion are arranged coaxially. At this time, the number of stages of the gas turbine portion in the turbine apparatus is selected to be smaller than the number of stages of the compressed turbine to be replaced. Furthermore, the number of stages in the steam turbine section is greater than the number of stages in the gas turbine section configured in the turbine apparatus.

  By reducing the gas stages in the compression turbine, a greater amount of energy for the power turbine remains in the combustion gas. Further, the steam pressure at the inlet of the steam portion of the compression turbine can be higher than the gas pressure at the inlet of the gas portion of the compression turbine. Thus, the output sharing of the steam turbine portion can be increased.

  The invention further relates to the problem of increasing the utilization of a turbine arrangement comprising a gas turbine part and a steam turbine part arranged coaxially. Also, efficient cooling of the turbine blade is desired.

  This is obtained by the turbine blades comprising a gas turbine part and a steam turbine part arranged coaxially. The turbine blade includes a channel in the blade. The channel is configured to direct steam from the steam turbine portion to the gas turbine portion and back to the steam turbine portion. As a result, a simple blade configuration, efficient blade cooling, and energy supply to the steam turbine section are also achieved.

  This object is also achieved by a turbine vane for a turbine arrangement comprising a gas turbine part, a coaxially arranged steam turbine part and a steam generator. In this case, the turbine vane includes a steam channel. The steam channel is configured to direct steam from the steam generator through the gas turbine section to the steam turbine section. In this way, the stationary blade is efficiently cooled.

  In a turbine apparatus having a gas turbine portion and a steam turbine portion arranged coaxially, it is desirable to release air from the hub of the turbine apparatus. This can be achieved by an air channel configured to direct air from the hub through the steam turbine portion to the gas turbine portion.

  In a turbine arrangement with coaxially arranged gas turbine portions and steam turbine portions, the same blades extend through both portions, thus increasing the load on the turbine blades. This problem can be solved by introducing a partition that separates the gas turbine section from the steam turbine section. When the gas turbine rotor blade is attached to the partition wall, the centrifugal force resulting from the rotation of the gas turbine rotor blade is partially supported and canceled by the partition wall.

  Furthermore, according to the present invention, the utilization of a turbine apparatus comprising a gas turbine portion and a steam turbine portion arranged coaxially by using steam turbine blades and gas turbine blades of different cross sections. Can be increased. In addition, the cross section of the steam turbine blade can be optimized for the steam flow in the steam turbine section, and the cross section of the gas turbine blade can be optimized for the gas flow in the gas turbine section. It can be optimized.

  The steam turbine blade may be divided into first and second blade portions, thereby forming a flow-through channel in the blade. Alternatively, the steam turbine blades are of a smaller cross-section, thereby allowing more steam turbine blades to be placed than gas turbine blades.

  Efficient cooling of the blades is ensured by a method of adjusting a turbine engine that includes a compressor, a combustion chamber, a compression turbine, and a power turbine. A compression turbine and / or power turbine is a turbine arrangement that includes a gas turbine portion and a steam turbine portion disposed coaxially. The compression turbine and / or power turbine further includes a moving blade and a stationary blade with a fluid channel and a steam generator. The steam generator generates steam toward the fluid channel to cool the blades and drive the steam turbine portion. According to this method, the compressed air from the compressor is guided to the blades of the turbine device at the time of start-up.

  Efficient cooling is also ensured and overspeed operation is prevented, and when stopped, the steam supply to the steam turbine part of the turbine unit is shut off and a relatively small amount of air is directed from the compressor to the steam turbine part of the turbine unit. It is burned.

  The present invention will now be described in further detail with reference to the accompanying drawings.

1 is an axial sectional view of a known turbine device 1 including a gas turbine part 2 and a steam turbine part 4. 1 is a schematic diagram showing a turbine engine 37 including a compressor 45, a combustion chamber 43, a compression turbine 31, and a power turbine 41. FIG. It is a figure which shows the conventional compression turbine 31 and the output turbine 41. FIG. FIG. 2 shows a modified compression turbine 32 and power turbine 41 comprising a gas turbine part 2 and a steam turbine part 4. FIG. 3 shows a modified compression turbine 33 and output turbine 41 with optimized number of stages of the gas turbine section 2 and the steam turbine section 4 in the compression turbine 33. FIG. 2 shows turbine blades 7, 17 including channels 101, 103 that direct steam from steam turbine section 4 to gas turbine section 2 and back to steam turbine section 4. FIG. 2 shows a turbine vane 9, 19 including a steam channel 201 for supplying steam to the steam turbine part 4 of the turbine apparatus and an air channel 203 for directing air from the hub 205 of the turbine apparatus to the gas turbine part 2. FIG. 2 is a view showing a plurality of turbine rotor blades 7, 17 and a partition wall 301 disposed between the gas turbine portion 2 and the steam turbine portion 4. FIG. 2 shows two alternatives for designing a steam turbine blade when different sections are used for the steam turbine blade and the gas turbine blade. 1 is a block diagram illustrating a method for adjusting a turbine engine with a turbine apparatus having a gas portion and a steam portion. FIG.

  Neither the drawings nor the following description should limit the scope of the invention. Throughout the drawings, the same reference numerals are used for the same components.

  FIG. 1 shows a turbine apparatus 1 including a gas turbine part 2 and a steam turbine part 4. The gas turbine part 2 and the steam turbine part 4 are arranged coaxially. This principle is known from Swedish Patent No. SE530142C2, US Provisional Patent Application No. 60/969997 and PCT Application No. PCT / SE2008 / 050258.

  Combustion gas from the combustion chamber enters the gas turbine portion 2 of the turbine device 1 (indicated by arrow 3). In FIG. 1, the combustion gas passes from left to right through the gas turbine section 2 (indicated by arrows 3 and 5). Thereby, the gas acts on the plurality of gas turbine blades 7 to drive the turbine shaft 6. The gas turbine portion 2 also includes a plurality of guide vanes or gas turbine vanes 9. The moving blades 7 and the stationary blades 9 are intermittently disposed along the turbine axis 11 in the longitudinal direction.

  A fluid channel 13 is disposed in the gas turbine blade 7 and the gas turbine vane 9. The fluid flow in the channel 13 absorbs heat from the combustion gases in the gas turbine section 2. The fluid channel 13 is led to the inlet 15 of the steam turbine part 4. In this way, the temperature of the fluid passing through the gas turbine part 2 increases and high pressure fluid is injected into the inlet 15 of the steam turbine part 4. At this point, the fluid is typically in a vapor state.

  The steam turbine part 4 is arranged radially inward of the gas turbine part 2 as can be seen from FIG. Steam passes from the left to the right through the steam turbine section 4 (indicated by the arrow at the steam inlet 15 and the arrow 16). Thereby, steam acts on the plurality of steam turbine blades 17 to drive the turbine shaft 6. Thus, both steam and combustion gas drive the same turbine shaft 6. The steam turbine portion 4 further includes a plurality of guide vanes or steam turbine vanes 19. As with the gas turbine section 2, the steam turbine blade 17 and the steam turbine stationary blade 19 are arranged intermittently.

  The moving blades 7 and 17 are attached to the rotor 21, and the stationary blades 9 and 19 are attached to the stationary portion 23.

  In the schematic diagram of FIG. 1, the most upstream blades are rotor blades 7 and 17. Following that, the stationary blades 9 and 19 are formed. This situation can be reversed. That is, the most upstream blade can be a stationary blade (see FIG. 3).

  Reference is now made to FIGS. One aspect of the invention relates to a method for changing a gas turbine engine 37 to a turbine engine with a combined gas / steam turbine device 33. This can increase the utilization of the turbine engine including the gas turbine 31.

  The conventional gas turbine 35 of the turbine engine 37 can be divided into a compression turbine 31 and a power turbine 41, respectively. The compression turbine 31 is driven by the combustion gas from the combustion chamber 43, and as a result, drives the compressor 45 that supplies air to the combustion chamber 43. The output turbine 41 is disposed downstream of the compression turbine 31 and converts the remaining energy of the combustion gas into shaft power. In this connection, the compression turbine 31 may be connected to the compressor 45 by a first turbine shaft 47. The output turbine 41 may be connected to a generator or transmission box (not shown) via a second turbine shaft 49. Such a turbine engine is commonly referred to as a twin-spool engine.

  The compression turbine 31 of the present embodiment is initially a two-stage gas turbine. That is, the compression turbine 31 includes two sets of axially separated gas turbine blades (see FIG. 3a). In FIGS. 3 a, 3 b and 3 c, the gas turbine stage is indicated as G and the steam turbine stage is indicated as S.

  A direct way to increase the output of the turbine engine 37 is to change both the compression turbine 31 and the output turbine 41 to a turbine apparatus 1 with a gas turbine part 2 and a coaxial steam turbine part 4. Is to replace. The result of such a change is shown in FIG. At this time, the compression turbine 32 includes two gas stages G and two steam stages S. However, the increased output of the compression turbine 32 is not required to drive the compressor 45 and is therefore not optimally utilized.

  The method of the present invention for increasing the power of the turbine engine 37 is shown in FIG. 3c. Here, a compression turbine 33 including one gas turbine stage G and three steam turbine stages S is used. By introducing a three-stage steam turbine section 4, one of the gas stages is redundant. One gas stage G and three steam stages S are sufficient to generate the output required by the compressor. Thus, one of the gas turbine stages of the compression turbines 31, 32 can be removed. Removal of one turbine stage means removal of one blade and one stator blade.

  When the existing turbine engine 37 is changed in this way, that is, when the configuration of FIG. 3a is changed to the configuration of FIG. 3c, the gas temperature and gas pressure at the outlet of the compression turbine 33 are increased. As a result, the gas temperature and gas pressure at the inlet of the output turbine 41 increase. Thereby, the output turbine 41 can generate more output.

  In a turbine apparatus 1 comprising a gas turbine section 2 and a steam turbine section 4 arranged coaxially, the gas pressure in the gas turbine section 2 is changed along the longitudinal turbine axis 11 to the steam in the steam turbine section 4. It is desirable to configure the device to be essentially equal to the pressure. If the gas turbine part 2 and the steam turbine part 4 are arranged with their inlets and outlets aligned axially (see FIG. 1), the respective gas and steam pressures must match. However, as described with reference to FIGS. 3b and 3c, the number of gas turbine stages and the number of steam turbine stages can be varied. For example, more steam turbine stages than gas turbine stages can be used if desired (FIG. 3c).

  The combustion gas pressure in the combustion chamber 43 and thus the inlet pressure in the gas turbine section 2 is typically about 1.5 MPa. Therefore, the turbine apparatus 1 should be designed so that the inlet steam pressure of the steam turbine portion 4 is also about 1.5 MPa. However, as more steam turbine stages are added (FIG. 3c), the inlet steam pressure of the steam turbine portion 4 can rise to, for example, 5 MPa. Thereby, the output sharing of the steam turbine is significantly increased. Each turbine stage is accompanied by a pressure drop. Thus, with the added steam turbine stage, the steam pressure is lowered to the desired 1.5 MPa at the axial position where the inlet of the gas turbine part 2 is located.

  The vapor pressure is influenced by the configuration of the fluid channel 13. A separate steam generator can also be used to generate sufficient steam at a given pressure.

  The output turbine 41 of FIGS. 3b and 3c is a conventional gas turbine or a turbine arrangement 1 that includes a gas turbine portion 2 and a coaxial steam turbine portion 4 as shown here. be able to. If the output turbine 41 is a turbine device 1 including a gas turbine part 2 and a coaxial steam turbine part 4, the steam turbine part 4 is extended by adding a steam turbine stage to the end of the steam turbine part 4. can do. With such a configuration, more steam energy can be used.

  As shown in FIG. 3c, when the gas stage is removed, the inner wall 34 of the stationary part constitutes the outer wall for the steam turbine part not located radially inward of the gas turbine part. Can be arranged to The inner wall 34 of the stationary part may be held by a rod (not shown) extending radially inward from the stationary part wall. Similar solutions apply if additional steam stages are added before and / or after the turbine unit.

  FIG. 4 illustrates another aspect of the present invention. Assume a turbine apparatus 1 (FIG. 1) comprising a coaxial gas turbine portion 2 and a steam turbine portion 4. Here, the steam is guided from the steam turbine part 4 to the gas turbine part 2 by the channels 101, 103 in the blades 7, 17 and back to the steam turbine part 4. In this way, the blades 7 and 17 are cooled, and the steam in the steam turbine portion 4 is overheated. The flow through the channels 101, 103 is driven by the pressure difference between the leading and trailing edges of the wing.

  In the steam turbine portion 4, the steam enters the steam turbine blade 17 through the inlet opening 105 at the leading edge of the blade 17, that is, the upstream edge. Steam spreads radially outward in the longitudinal direction of the blades 7, 17 through the outer channel 101 from the steam turbine part 4 to the gas turbine part 2.

  While other embodiments are possible (see, eg, FIG. 7), in FIG. 4, the cross sections of the steam turbine blade 17 and the gas turbine blade 7 are equal. The outer channel 101 extends from the steam turbine blade 17 to the gas turbine blade 7. Within the gas turbine blade 7, the outer channel 101 is divided into a plurality of inner channels 103. The inner channel directs the steam radially inward and returns it to the steam turbine blade 17. The inner channel then terminates at the outlet opening 107. The outlet opening 107 is positioned at the rear edge of the steam turbine rotor blade 17, that is, the downstream edge. In this embodiment, one outer channel 101 and four inner channels 103 are used, but any desired flow geometry that provides high heat transfer can be used.

  In order to maximize heat transfer from the combustion gas to the gas turbine blade 7 and thus to maximize heat transfer to the steam flowing through the outer channel 101 and the inner channel 103, the channel is essentially: It extends along the entire length of the gas turbine blade 7.

  The arrangements 105, 101, 103, 107 for collecting heat from the gas turbine part 2 and supplying the heat to the steam turbine part 4 include the meaning that steam is injected at the inlet 15 of the steam turbine part 4. This steam can be generated in a separate steam generator as described below.

  Also, the configurations of 105, 101, 103, and 107 can be used in combination with the fluid channel 13 described above. In this case, each turbine blade 7, 17 includes an outer channel 101, an inner channel 103, and a fluid channel 13. Alternatively, the turbine blades 7, 17 comprise an outer channel 101 and an inner channel 103 as shown in FIG. 4, while only the turbine vanes 9, 19 comprise a fluid channel 13 as shown in FIG. You can also.

  FIG. 5 relates to yet another aspect of the present invention. This embodiment addresses, for example, the problem of cooling the stationary blades 9,19. In a turbine arrangement comprising a gas turbine part 2 and a steam turbine part 4 arranged coaxially (see FIG. 1), the stationary blades 9 in the gas turbine part 2 flow inside the blades 9 according to FIG. Can be cooled by steam. Steam flows through the gas turbine part 2 to the steam turbine part 4. For this purpose, a steam channel 201 can be arranged in the turbine vanes 9, 19. Steam can be generated in a separate steam generator as described below. Alternatively, the steam can be generated in the fluid channel 13 of the turbine blade.

  As can be seen from FIG. 5, the turbine vanes 9, 19 include a steam channel 201. The channel 201 extends through the vanes 9,19. The channel 201 is configured to guide steam from the outside of the stationary part wall through the gas turbine part 2 to the steam turbine part 4. In this way, the steam is heated and the blades 9 and 19 are cooled. In the steam turbine portion 4, steam can exit the blade 19 through an opening (not shown) in the trailing edge of the steam turbine vane 19. Alternatively, the steam can be guided upstream by a tube (not shown) and released into the steam turbine section 4 before the vanes 9, 19. Arrow 207 illustrates the flow of steam through the vane 19 in an exemplary manner.

  The steam channel 201 may be disposed in the most upstream turbine blade of the turbine apparatus 1. The next stationary vane along the turbine axis 11 may comprise a similar steam channel 201 or a fluid channel 13 as shown in FIG. The steam flow geometry in the wing is optimized to provide high heat transfer.

  In FIG. 5, the turbine hub is indicated by reference numeral 205. The compressed air may leak from the compressor 45 to the hub 205 of the turbine apparatus 1 through, for example, a seal (not shown) of the shaft 47 and a rear bearing (not shown). This air can be exhausted using the air channel 203 in the vanes 9, 19. Alternatively, such an air channel 203 can be arranged in the blades 7, 17 although not shown.

  The purpose of the air channel 203 is to direct air from the hub 205 through the steam turbine part 4 to the gas turbine part 2. As a result, the trailing edges of the turbine blades 7, 17, 9, 19 are cooled. It is advantageous if the air channel terminates at a plurality of outlet openings 209 or slots 209 arranged at the rear or trailing edge of the turbine blade. Such slots 209 can be positioned essentially along the entire edge of the turbine blade. This provides effective cooling along the entire edge.

  FIG. 6 schematically illustrates another aspect of the present invention. This aspect has the problem of constructing a turbine apparatus having a gas turbine part 2 and a steam turbine part 4 arranged coaxially while avoiding exposing the rotor blades 7 and 17 to a high mechanical load. deal with. The coaxially arranged turbine sections 2, 4 mean that the blades 7, 17 are longer than the conventional gas turbine blade. Thereby, the centrifugal force acting on the radially inner portions of the blades 7 and 17 is increased. This increase in load is compensated to some extent by the above-described cooling of the rotor blades 7, 17. The lower the temperature, the higher the strength. In FIG. 6, an additional measure for reducing the mechanical load on the rotor blades 7, 17 is shown.

  A partition wall 301 is arranged between the gas turbine part 2 and the steam turbine part 4. A divider or outer seal ring 301 serves to separate the gas turbine part 2 from the steam turbine part 4 and is formed by a plurality of plates attached to the blades (as shown in FIGS. 4 and 5). obtain. However, by making the partition wall 301 as a complete ring and attaching the gas turbine rotor blade 7 to the partition wall 301, a part of the centrifugal force caused by each gas turbine rotor blade 7 around the rotor is reduced. The partition wall 301 can also be received.

  FIG. 6 further shows stationary wall 303, inner seal ring 305, and turbine blade root 307. The gas turbine part 4 is delimited by a partition wall 301 and an inner seal ring 305. Corresponding partition walls and inner seal rings are supported by the vanes 9,19.

  FIG. 7 relates to a further aspect of the invention. Here, the gas turbine blades 7 and 9 and the steam turbine blades 17 and 19 are respectively optimized for the gas flow and the steam flow of the turbine device 1. A turbine device 1 (FIG. 1) is assumed that comprises a coaxial gas turbine part 2 and a steam turbine part 4.

  For example, as shown in FIG. 6, the volume of the steam turbine part 4 is considerably smaller than the volume of the gas turbine part 2. This is indicated by the radial position of the partition wall 301. In fact, the steam flow through the steam part 4 is only about 10% of the gas flow through the gas part 2. Accordingly, the radial length of the steam turbine blades 17, 19 is shorter than the radial length of the gas turbine blades 7, 9.

  When the steam turbine blade 17 can support the centrifugal load of the gas turbine blade 7 (that is, when the partition wall 301 supporting the load is not used), the cross section of the steam turbine blade 17 is the same as that of the gas turbine blade 7. Must be essentially the same in cross section.

  If the same cross section is used for the steam turbine blade 17 and the gas turbine blade 7, the ratio of the chord 401 to the blade length of the steam turbine blade 17 is relatively large. The blade length means the length of the moving blade 17 in the radial direction. A large ratio of the chord 401 to the blade length is not preferable because it means that the flow resistance is high.

  It is therefore desirable to use different configurations for the steam turbine blade 17 and the gas turbine blade 7. As a result, the respective blades 17, 7 are optimized for the flow of the steam turbine part 4 and the gas turbine part 2. In particular, the large ratio of the chord 401 to the wing length should be avoided.

  In the left part of FIG. 7, the first design proposal for the cross section of the steam turbine blade is shown. A cross section of the gas turbine blade 7 is also shown. Each steam turbine rotor blade is divided into a first blade portion 17a and a second blade portion 17b. Thereby, the flow-through channel 403 is formed in the rotor blade. The once-through channel 403 reduces the flow resistance of the steam turbine rotor blades 17a and 17b. Furthermore, the ratio of the chord to the wing length is reduced.

  The right hand side of FIG. 7 further shows a second possible design for the cross section of the steam turbine blade. For comparison, the cross section of the gas turbine blade 7 is again shown. Here, a plurality of smaller steam turbine blades 17c, 17d, 17e are used instead of one larger turbine blade. Therefore, the radial length of the steam turbine blade is unchanged, but the chord is reduced. This means that the ratio of chord to wing length is reduced.

  According to the present invention, by using 2 to 5 smaller steam turbine blades for the corresponding gas turbine blade, the ratio of chord to blade length is adequate. In particular, the three smaller steam turbine blades 17c, 17d, 17e provide an appropriate chord to blade length ratio.

  Optimization of the steam turbine blade may be realized in conjunction with the use of the partition wall 301 described with reference to FIG. In this way, the steam turbine blades 17 a, 17 b, 17 c, 17 d, 17 e do not have to support all the centrifugal load caused by the gas turbine blade 7. However, the optimization can be performed without the partition wall 301. In that case, the steam turbine blades 17a, 17b, 17c, 17d, 17e must be designed to be able to support the centrifugal forces caused by the gas turbine blades 7.

  The block diagram of FIG. 8 shows a method for controlling a turbine engine of a power plant including a turbine device 1 with a gas part 2 and a steam part 4. Although this block diagram is consistent with the schematic diagram of FIG. 2, FIG. 8 further discloses a steam generator 51, a condenser 53, a generator 55, and valves V1-V5. The compression turbine 31 and the output turbine 41 are turbine apparatuses of the type shown in FIG.

  The steam generator 51 is connected to the outlet of the gas turbine part 2 of the output turbine 41. Furthermore, the steam generator 51 is connected to the inlet of the steam portion of the compression turbine 31 via the valve V1. The steam generator 51 is connected to the inlet of the steam portion of the output turbine 41 via the valve V2. Thus, the steam generator 51 uses heat from the combustion gas to generate steam. This steam is supplied to the compression turbine 31 and the output turbine 41. The arrow at the top of the steam generator 51 in FIG. 8 indicates the outlet of the combustion gas. The steam generator 51 can also be powered by a separate burner or electrical means.

  The valves V <b> 1 and V <b> 2 are control valves that ensure that a maximum amount of steam is supplied to the compression turbine 31 and the steam turbine portion 4 of the output turbine 41. There is essentially no leakage of steam from the steam portion 4 of each turbine 31, 41 to the gas portion 2. The valves V1 and V1 are adjusted by the combustion gas pressure before the compression turbine 31 and the output turbine 41, respectively. A blow valve V <b> 4 is disposed at the steam outlet of the steam generator 51.

  A condenser 53 is connected to the steam generator 51 and can supply a condensed fluid such as water to the steam generator 51. The steam is guided to the condenser 53 through a connection portion of the output turbine 41 with the steam turbine portion 4. As can be seen from FIG. 8, the connection between the output turbine 41 and the condenser 53 includes a blow valve V5. The heat generated during condensation can be used for heating purposes.

  The arrow to the left of the condenser in FIG. 8 indicates, for example, a connection to the district heating system.

  A generator 55 is connected to the output turbine 41 via the second turbine shaft 49.

  The outlet of the compressor 45 is connected to the steam inlet of the compression turbine 31. As can be seen from FIG. 8, the valve V <b> 3 is arranged to regulate the flow of air from the compressor 45 toward the compression turbine 31. The compressor 45 can also be connected to the steam inlet of the output turbine 41.

  The adjustment of the turbine engine of the present invention is in principle consistent with the adjustment of a conventional engine that combines a gas turbine and a steam turbine. However, because the gas turbine section 2 and the steam turbine section 4 (in each of the compression turbine 31 and the power turbine 41) are located in the same housing and share the same rotor, the gas turbine Even when no steam is generated by the part 2, the steam turbine part 4 will operate. This is a case of a transient state such as a start-up or an emergency stop. The shortage of steam during such a state means that the cooling of the compression turbine 31 and the output turbine 41 is insufficient.

  In order to obtain sufficient cooling at startup, the valves V1, V2 between the steam generator 51, the compression turbine 31 and the output turbine 41 are closed. The remaining valves V3, V4, V5 are open so that air from the compressor 45 is directed through the compression turbine 31 and the output turbine 41 and cools them. Air is directed through a fluid channel 13 (see FIG. 1) located in the turbine blades of the turbines 31,41. A starter motor is used to help bring the turbines 31, 41 into no-load operation, which generally takes about 2-3 minutes. Subsequently, steam is generated by the steam generator 51 and is generated using the fluid channel 13 in the compression turbine 31 and the output turbine 41. Here, the valves V1, V2 between the steam generator 51, the compression turbine 31, and the output turbine 41 can be opened, and the remaining valves V3, V4, V5 can be closed.

  For example, during an emergency stop caused by sudden loss of load on the shaft 49, overspeed operation of the turbines 31, 41 must be prevented. In this regard, the fuel supply is immediately shut off. The supply of steam to the steam turbine portion 4 of the compression turbine 31 and the output turbine 41 is interrupted by closing the valves V1, V2 between the steam generator 51 and the turbines 31, 41. A blow valve V 4 at the steam outlet of the steam generator 51 is opened to exhaust from the steam generator 51. The remaining valves V3 and V5 are gradually opened to direct air from the compressor through the steam turbine portion 4 of the turbines 31, 41 for cooling. Air is directed through the fluid channel 13 (see FIG. 1) located in the turbine blades of the turbines 31, 41. By gradually opening in this way, the air flow is sufficient for cooling. However, the air flow is not strong enough to give the turbines 31 and 41 an undesired driving force.

Claims (14)

A method of changing a gas turbine engine (37) to a turbine engine (33) equipped with a combined gas / steam turbine device, the gas turbine engine (37) comprising:
A compressor (45);
A combustion chamber (43) fed with air from the compressor (45);
A compression turbine (31);
An output turbine (41),
The compression turbine (31) drives the compressor (45), the output turbine (41) supplies output, and the compression turbine (31) is a gas turbine including a plurality of gas stages (G). In the method,
Replacing the compression turbine (31) with a turbine arrangement (33) comprising a gas turbine section (2) and a steam turbine section (4), wherein the gas The turbine part (2) and the steam turbine part (4) are arranged coaxially, comprising the steps of:
Selecting the number of stages (G) of the gas turbine part (2) in the turbine device (33) to be less than the number of stages (G) of the compressed turbine (31) to be replaced;
A method characterized in that the number of stages (S) in the steam turbine part (4) is greater than the number of stages (G) of the gas turbine part (2) configured in the turbine device (33). .   Initially, the compression turbine (31) includes two gas stages (G), and after modification, the compression turbine (33) includes one gas stage (G) and three steam stages (S). Item 2. The method according to Item 1.   At least one of the steam stages is arranged axially forward of the inlet of the gas turbine part (2), the inlet pressure of the steam turbine part (4) being the inlet of the gas turbine part (2). The method according to claim 1 or 2, wherein the pressure is higher than the pressure. Turbine blades (7, 17) for a turbine device (1), the device (1) comprising:
A gas turbine section (2);
A turbine blade comprising a coaxially arranged steam turbine portion (4),
The turbine blade (7, 17) includes a channel (101, 103) in the blade (7, 17), the channel (101, 103) delivering steam to the steam turbine portion (4). Turbine blades characterized in that they are adapted to be led from the gas to the gas turbine part (2) and back to the steam turbine part (4).   The channel (101, 103) includes at least one outer channel (101) and a plurality of inner channels (103), the outer channel (101) extending from the steam turbine portion (4) to the gas turbine portion. Turbine motion according to claim 4, wherein the turbine channel (103) extends from the gas turbine part (2) to the steam turbine part (4). Wings. Turbine vanes (9, 19) for a turbine device (1), wherein the device (1)
An outer gas turbine section (2);
An inner steam turbine section (4) arranged coaxially;
In a turbine vane, including a steam generator,
The turbine vane (9, 19) includes a steam channel (201), which steam channel (201) steams from the steam generator through the gas turbine part (2) to the steam turbine part (4). A turbine stationary blade configured to guide Turbine blades (7, 17, 9, 19) for a turbine device (1),
The device (1) is
An outer gas turbine part (2) and an inner steam turbine part (4) arranged coaxially,
In a turbine blade, wherein the steam turbine portion (4) surrounds a hub (205) of the turbine device (1),
The turbine blades (7, 17, 9, 19) further include an air channel (203), the air channel (203) passing from the hub (205) through the steam turbine portion (4) to the gas turbine portion. A turbine blade configured to guide air to (2).   The blade of claim 7, wherein the air channel (203) terminates in a plurality of slots (209) disposed at a trailing edge of the turbine blade. A turbine device (1) comprising:
A gas turbine section (2);
A coaxially arranged steam turbine section (4);
Steam turbine blades (17) and gas turbine blades extending from the turbine hub of the device (1) through the steam turbine portion (4) and through the gas turbine portion (2) 7) including:
A partition wall (301) separating said gas turbine part (2) from said steam turbine part (4);
The gas turbine rotor blade (7) is attached to the partition wall (301) so that the rotation of the hub, and hence the centrifugal force due to the rotation of the gas turbine rotor blade (7), is Turbine device characterized in that it is partially supported and counteracted by a partition wall (301). A turbine device (1) comprising:
A gas turbine section (2);
A coaxially arranged steam turbine section (4);
Steam turbine blades (17) and gas turbine blades extending from the turbine hub of the device (1) through the steam turbine portion (4) and through the gas turbine portion (2) 7) including:
The steam turbine blade (17) and the gas turbine blade (7) have different cross sections so that the cross section of the steam turbine blade (17) is the same as that of the steam turbine portion (4). Optimized for the flow of steam inside, the cross section of the gas turbine blade (7) being optimized for the flow of gas in the gas turbine part (2) Turbine equipment.   Each steam turbine blade (17) is divided into first and second blade portions (17a, 17b), whereby a flow-through channel (403) is formed in the blade (17). The turbine apparatus according to claim 10.   The steam turbine blade (17a, 17b, 17c) has a smaller cross-section than the gas turbine blade (7), so that more steam turbine blades than the gas turbine blade (7). The turbine device according to claim 10, wherein (17a, 17b, 17c) can be arranged. A method of adjusting a turbine engine, the turbine engine comprising:
A compressor (45), a combustion chamber (43), a compression turbine (31) and a power turbine (41), and a steam generator (51);
The compression turbine (31) and / or the output turbine (41) comprises a gas turbine part (2), a coaxially arranged steam turbine part (4), and a rotor blade having a fluid channel (13) ( 7, 17) and stationary vanes (9, 19),
The steam generator (51) generates steam toward the fluid channel (13) to cool the blades (7, 17, 9, 19) and drive the steam turbine portion (4). In a method for adjusting a turbine engine,
To prevent overheating, from the compressor (45) at start-up, i.e. before the steam generator (51) supplies enough steam to cool the blades (7, 17, 9, 19). A method, characterized in that compressed air is led to the blades (7, 17, 9, 19) of the turbine device (1).   In order to prevent overspeed operation of the turbine, when the engine is stopped, the supply of steam to the steam turbine part (4) of the turbine device (1) is shut off, and a relatively small amount of air is supplied to the compressor to prevent overheating. 14. The method according to the preamble of claim 13, characterized in that it leads from (45) to the steam turbine part (4) of the turbine arrangement (1).

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