Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/005—Repairing methods or devices
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/14—Form or construction
  • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
  • F01D5/284—Selection of ceramic materials
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
  • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
  • F01D5/288—Protective coatings for blades
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2220/00—Application
  • F05D2220/70—Application in combination with
  • F05D2220/72—Application in combination with a steam turbine
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2230/00—Manufacture
  • F05D2230/80—Repairing, retrofitting or upgrading methods
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2230/00—Manufacture
  • F05D2230/90—Coating; Surface treatment

Definitions

• the invention relates to a method for carrying out service measures on an energy conversion plant and an energy conversion plant.
• These can be machines for baseload power supply or for balancing load changes, especially due to renewable energies whose input into the power grid can vary. Requirements can include different locations, cooling options, fuels, etc.
• the problem is solved by a method according to claim 1 and an energy conversion plant according to claim 10, wherein a corresponding existing gas turbine is provided or modified accordingly or newly manufactured.
• the Figure 1 shows, as an example, a gas turbine machine 100 in a longitudinal section.
• the gas turbine machine 100 has inside a rotor 103 rotatably mounted around a rotational axis 102 with turbine blade 120, which is also referred to as a turbine runner.
• an intake housing 104 a compressor 105, a combustion chamber 110 (e.g., a torus-shaped combustion chamber, in particular a ring combustion chamber) with several coaxially arranged burners 107, a turbine 108 and the exhaust housing 109 follow one another.
• a combustion chamber 110 e.g., a torus-shaped combustion chamber, in particular a ring combustion chamber
• burners 107 e.g., a turbine 108 and the exhaust housing 109 follow one another.
• the annular combustion chamber 110 communicates with a preferably annular hot gas channel 111.
• a preferably annular hot gas channel 111 There, for example, four turbine stages connected in series 112 the turbine 108.
• Each turbine stage 112: I, II, III, IV is preferably formed from two blade rings.
• a row of guide vanes 115 is followed by a row of guide vanes 125 formed from guide vanes 120.
• the guide vanes 130 are attached to a gas turbine housing 138 of a stator 143, whereas the rotor blades 120 of a rotor blade row 125 are attached to the rotor 103, for example by means of a turbine disk 133.
• a generator 5 is coupled to the rotor 103 ( Fig. 24 ) or a working machine (not shown).
• air 135 is drawn in and compressed by the compressor 105 through the intake housing 104.
• the compressed air supplied at the turbine-side end of the compressor 105 is directed to the burners 107 in a combustion chamber 110 and mixed there with a fuel.
• the mixture is then combusted in the combustion chamber 110, forming the working fluid 113.
• the working fluid 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
• the working fluid 113 expands, transferring momentum so that the rotor blades 120 drive the rotor 103, which in turn drives the machine coupled to it.
• the components exposed to the hot working medium 113 are subject to thermal stresses during the operation of the gas turbine 100.
• the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the highest thermal stresses, along with the heat shield elements lining the combustion chamber 110.
• the substrates of the components can have a directional structure, i.e., they are single-crystal (SX structure) or have only longitudinally oriented grains (DS structure).
• SX structure single-crystal
• DS structure longitudinally oriented grains
• iron-, nickel- or cobalt-based superalloys are used as material for the components, especially for the turbine blade 120, 130 and components of the combustion chamber 110.
• Such superalloys are preferably made from the EP 1 204 776 B1 , EP 1 306 454 , EP 1 319 729 A1 , WO 99/67435 or WO 00/44949 known or in Figure 4 listed.
• the blades can have 120, 130 corrosion-resistant coatings: MCrAlX; M is at least one element from the cobalt (Co), nickel (Ni) group, X is an active element and stands for yttrium (Y) and/or tantalum (Ta) and/or at least one rare earth element or hafnium (Hf) or iron (Fe).
• MCrAlX is at least one element from the cobalt (Co), nickel (Ni) group
• X is an active element and stands for yttrium (Y) and/or tantalum (Ta) and/or at least one rare earth element or hafnium (Hf) or iron (Fe).
• Such alloys are known from the EP 0 486 489 B1 , EP 0 786 017 B1 , EP 0 412 397 B1 or EP 1 306 454 A1 .
• MCrAlX may have a thermal insulation layer, and consists, for example, of ZrO 2 , Y 2 O 3 -ZrO 2 , i.e., it is not, partially or completely stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide and/or erbium oxide and/or ytterbium oxide.
• the guide vane 130 has a guide vane root (not shown here) facing the gas turbine casing 138 of the turbine 108 and a guide vane tip opposite the guide vane root.
• the guide vane tip faces the rotor 103 and is fixed to a mounting ring 140 of the stator 143.
• Figure 2 shows a combustion chamber 110 of a gas turbine.
• the combustion chamber 110 for example, is designed as a so-called annular combustion chamber, in which a large number of circumferentially arranged
• the flames 156 are generated by burners 107 arranged around a rotational axis 102 and flow into a common combustion chamber 110.
• the combustion chamber 110 is designed as a ring-shaped structure positioned around the rotational axis 102.
• the combustion chamber 110 is designed for a relatively high working medium temperature of approximately 1273 K to 1873 K.
• the combustion chamber wall 153 of the combustion chamber 110 is provided on its working medium-facing side with an inner lining formed from heat shield elements 155.
• Each heat shield element 155 made of an alloy, is equipped on the working medium side with a particularly heat-resistant protective layer (MCrAlX layer and/or ceramic coating) or is made of high-temperature-resistant material (solid ceramic bricks).
• M is at least one element from the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and/or silicon (Si) and/or tantalum (Ta) and/or at least one rare earth element or hafnium (Hf) and/or iron (Fe).
• Such alloys are known from the EP 0 486 489 B1 , EP 0 786 017 B1 , EP 0 412 397 B1 or EP 1 306 454 A1 .
• the MCrAlX may also have a, for example, ceramic thermal insulation layer and consists of ZrO 2 , Y 2 O 3 -ZrO 2 , i.e. it is not, partially or completely stabilized by yttrium oxide and/or erbium oxide, ytterbium oxide and/or hafnium oxide.
• the thermal barrier layer can have porous granules with micro- or macro-cracks for improved thermal shock resistance.
• Refurbishment means that heat shield elements 155 may need to have their protective coatings removed after use (e.g., by sandblasting). This is followed by the removal of corrosion and/or oxidation layers or products. Any cracks in the heat shield element 155 are also repaired, if necessary. Finally, the heat shield elements 155 are recoated and reused.
• a cooling system may also be provided for the heat shield elements 155 or their retaining elements.
• the heat shield elements 155 are then, for example, hollow and may also have cooling holes (not shown) opening into the combustion chamber space 154.
• the Figure 3 The figure shows in perspective a guide vane 120 or guide vane 130 of a turbomachine, which extends along a longitudinal axis 121.
• the turbomachine can be a gas turbine of an aircraft or a power plant for generating electricity, a steam turbine, or a compressor.
• the bucket 120, 130 has a mounting area 400, an adjacent bucket platform 403, a bucket blade 406 and a bucket tip 415 successively along its longitudinal axis.
• a guide shovel 130 it can have another platform at its shovel tip 415 (not shown).
• a blade root 183 is formed, which is used to attach the rotor blades 120, 130 to a shaft or a turbine disk 133 ( Fig. 1 ) serves.
• the shovel foot 183 for example, is designed as a hammerhead. Other designs, such as a fir tree or dovetail foot, are possible.
• the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the blade 406.
• Such superalloys are preferably made from the EP 1 204 776 B1 , EP 1 306 454 , EP 1 319 729 A1 , WO 99/67435 or WO 00/44949 or from Figure 4 known.
• the shovel 120, 130 can be manufactured by a casting process, including directed solidification, by a forging process, by a milling process or combinations thereof.
• Workpieces with single-crystal structure or structures are used as components for machines that are exposed to high mechanical, thermal and/or chemical stresses during operation.
• single-crystal workpieces are achieved, for example, by directed solidification from the melt. These are casting processes in which the liquid metallic alloy solidifies into a single-crystal structure, i.e., a single-crystal workpiece, or in a directed manner.
• dendritic crystals align along the heat flow, forming either a columnar grain structure (i.e., grains that extend the entire length of the workpiece and are commonly referred to as directionally solidified) or a single-crystal structure (i.e., the entire workpiece consists of a single crystal).
• a columnar grain structure i.e., grains that extend the entire length of the workpiece and are commonly referred to as directionally solidified
• a single-crystal structure i.e., the entire workpiece consists of a single crystal.
• directionally solidified structures When referring generally to directionally solidified structures, this includes both single crystals, which have no grain boundaries or at most low-angle grain boundaries, and columnar crystal structures, which have grain boundaries running longitudinally but no transverse grain boundaries. These latter crystalline structures are also called directionally solidified structures.
• the blades can also have coatings against corrosion or oxidation, specifically MCrAlX; M is at least one element from the cobalt (Co) or nickel (Ni) group, X is an active element and represents yttrium (Y) and/or tantalum (Ta) and/or at least one rare earth element and/or hafnium (Hf) and/or iron (Fe).
• MCrAlX coatings against corrosion or oxidation
• M is at least one element from the cobalt (Co) or nickel (Ni) group
• X is an active element and represents yttrium (Y) and/or tantalum (Ta) and/or at least one rare earth element and/or hafnium (Hf) and/or iron (Fe).
• Such alloys are known from the EP 0 486 489 B1 , EP 0 786 017 B1 , EP 0 412 397 B1 or EP 1 306 454 A1 .
• the density is preferably at 95% of the theoretical density.
• the MCrAlX may also have a thermal insulation layer, which is preferably the outermost layer, and consists, for example, of ZrO 2 , Y 2 O 3 -ZrO 2 , i.e., it is not, partially or completely stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide and/or erbium oxide and/or ytterbium oxide.
• the thermal barrier layer covers the entire MCrAlX layer.
• Other coating methods are conceivable, e.g., atmospheric plasma spraying (APS), LPPS, VPS, or CVD.
• APS atmospheric plasma spraying
• LPPS LPPS
• VPS VPS
• CVD chemical vapor deposition
• the thermal barrier layer can contain porous grains with micro- or macro-cracks for improved thermal shock resistance. Therefore, the thermal barrier layer is preferably more porous than the MCrAlX layer.
• Refurbishment means that components 120 and 130 may need to have their protective coatings removed after use (e.g., by sandblasting). This is followed by the removal of corrosion and/or oxidation layers or products. Any cracks in component 120 or 130 are also repaired, if necessary. Finally, component 120 or 130 is recoated and put back into service.
• the bucket 120, 130 can be hollow or solid. If the bucket 120, 130 is to be cooled, it is hollow and may also have cooling holes 418 (indicated by dashed lines).
• Figure 24 Figure 1 shows an example of an energy conversion plant 1 with one unit. This arrangement according to Figure 24 It can be present multiple times in an energy conversion plant, or in a modified form.
• the gas turbine 100 is coupled to a generator 5 for power generation via a gearbox 4 or a coupling 4.
• the generator 5 is also connected to a steam turbine 6 via a coupling 2.
• a power conversion plant 1 can also consist of only a gas turbine 100 without a steam turbine 6.
• a condenser 7 is connected to the steam turbine 6, if present.
• the exhaust gas from the gas turbine 100 flows via a diffuser 8 into a heat recovery system 9, where the hot exhaust air is used to generate steam.
• the defective components can preferably only include turbine blades.
• the defective components can preferably only be turbine blades or their coatings. as well as burners or burner components.
• measures to extend the service life of components and measures to optimize components can preferably be implemented as additional measures.
• the Figure 5 shows how Figure 1 a gas turbine machine 100 with compressor 105 and rotor 103 in cross-section.
• air 135 is pumped into the compressor 105, which has a compressor housing 19.
• a rotor bearing 31 of the rotor 103 in the flow direction 11 of the gas turbine machine 100 at the beginning of the compressor 105 and near the intake housing 104 has a length of at least 370mm and in particular a maximum length of 500mm or is designed to be at least 5% longer in the case of upgrade or overhaul in order to achieve a lower surface pressure.
• the built-in bearing does not need to be replaced, or it can be used until the end of the gas turbine machine's lifespan.
• Figure 6 is the burner 107' of a gas turbine engine 100 starting from Figure 1 , 5 or 7 , 8 , 12 or 14
• the corrosive properties of fuels, especially gas or oil that is burned, can vary locally.
• the burner system with the burner 107 ( Fig. 1 ) is exposed to the highest temperatures.
• the fuel supply means such as pipes, especially those of the burner 107', particularly those for gas, are at least partially, especially completely, internally coated with a diffusion coating, especially alitized, i.e., internal alitization (or chromizing, ...) is used.
• the internal coating can also be applied using the same methods while the part is installed.
• combustion chambers 111 refers to well-known systems such as ring combustion chambers or CANs.
• Figure 7 shows a similar arrangement of a cross-section of a gas turbine machine 100 according to Figure 1 , 5 , 6 , 8 , 12 , 14 or 24 , but with a now two-part compressor housing 19, which in the end area of the compressor 105 has an inner compressor housing 19'' and an outer compressor housing 19'.
• the materials of the compressor housings 19', 19'', especially if they are one-piece, are generally the same primary material, particularly gray cast iron.
• the inner compressor housing 19'', serving as the guide vane support is manufactured from a significantly different secondary material, particularly cast steel.
• Different between the first and second material means that at least one alloying element differs by 10% in its weight fraction and/or at least one other alloying element is present or less present and/or a a different manufacturing process was used or it has a different, distinguishable microstructure.
• Figure 8 shows in particular the hot gas channel 111 with its stages I, II, III and especially also stage IV.
• Stages I and II are subjected to higher thermal loads compared to stages III and IV.
• Appropriate modifications to the substrate material are employed here, particularly in the form of directionally solidified alloys (SX, DS) or additional or improved cooling, especially of the blade tip 415.
• Such a shovel 120, 130 preferably has a directed solidification structure SX, DS in the form of a columnar solidification microstructure, such as alloys with the addition of DS in particular.
• Figure 4 a directed solidification structure SX, DS in the form of a columnar solidification microstructure, such as alloys with the addition of DS in particular.
• shovel 120, 130 has a single-crystal microstructure in the substrate, similar to an alloy in Figure 4 with the suffix SX or CMSX ....
• first stage I has a DS structure, and most specifically only the guide vane of stage I.
• the blades have 120,130 cooling holes on the side surfaces of the blade platform 403, whereby the blade tips 415 are also cooled.
• a ceramic coating (TBC) based on partially stabilized YSZ (yttrium-stabilized zirconia) has a porosity of 12 ⁇ 4%.
• shovel 120, 130 features a segmented TBC based on yttrium-stabilized zirconia.
• Another type of blade 120, 130 consists of a directed solidification structure DS in the substrate, i.e. in the form of a columnar microstructure and with a TBC based on YSZ without segmentation.
• FIG 9 shows a turbine blade 120, 130, especially starting from Figure 3 , in which, however, cooling holes 399 are provided on the side surfaces 404 of the blade platform 403.
• the cooling holes 399 on the side surfaces 404 can be present on one, two, three, or all four side surfaces 404, as required, either singly or in multiples.
• cooling holes 405 can also be provided on the blade tip 415 (shown schematically only). Cooling air holes 418 are also provided on the blade 406 in a known manner.
• cooling air holes 399, 405, 418 are only schematic.
• the cooling holes 399, 405, 418, 501 run at an angle other than 90° to the side surface 404 of the bucket platform 403 and/or have a diffuser.
• Figure 10 shows a blade tip 415, 500 of a turbine running blade 120, in particular stages I, II.
• the shovel tip 500 has two externally extending ribs 503, 505 which, in cross-section, enclose a recess 504.
• the original recess 504 is indicated by a dashed line and is rectangular in cross-section.
• the blade tip 500 has a stepped shoulder 507 in the recess 504, which connects directly to the rib 505 of the suction side and thus initially represents additional material in the recess 504.
• a cooling air hole 501 now extends through the shoulder 507 from the interior of the rotor blade 120 to improve cooling of the blade tip 500.
• the cooling air hole 501 is preferably aligned with the longitudinal axis 121 of the turbine blade 120.
• the Figure 11 shows a blade carrier 50 with modified cooling air supply.
• Stage IV is attached in the area of this bucket carrier 50.
• the front plenum 54 is preferably located behind the rotor blade of stage III and in the area above the guide vane IV.
• the inlet of the new channel 60 is located downstream of the rotor blade 402 in the axial flow direction through the gas turbine, and not between the guide vane and the rotor blade of stage IV. Less cooling air is consumed, resulting in higher efficiency.
• Figure 12 The figure shows the transition from a final heat shield 155 or combustion chamber brick 155 of the combustion chamber 110 to a guide vane 130 of stage I. It can be seen that there is a gap 64 between the heat shield 155 and the guide vane 130.
• the rounded section 72 at the flow-side end of the heat shield/combustion chamber brick 155 and the opposite rounded section 75 of the guide vane 130 of stage I are identical.
• Figure 13 shows a sealing arrangement 79 of a guide vane carrier 50 ( Fig. 11 ), which leads to lower cooling air consumption.
• the individual elements 81, 83 of the guide vane carrier 79 have a gap 80, which here is labyrinthine or S-shaped.
• the reduced cooling air consumption is achieved by the fact that the element 81, which is forward in the direction of flow 11, has a first protrusion 82, and the second element 83, which is rearward in the direction of flow 11, has a second protrusion 85 formed above it, so that an S-shaped gap 80 is formed. and the nose 82 of the front element 81 forms part of the hot gas channel 111.
• the opening of the gap in the hot gas channel 111 is located at the rear in the direction of flow.
• Figure 14 shows a combustion chamber 110 with combustion chamber bricks 601, 604, 610, which lead to a spoiler effect.
• the combustion chamber bricks 601, 602 and 603, 605 are arranged in a row and circumferentially when viewed in the direction of flow 11.
• modified combustion chamber bricks 603, 605; 604 are present at the end, with further such combustion chamber bricks arranged in the circumferential direction around the axis of rotation 102.
• This spoiler effect leads to reduced erosion and also to a narrowing of the hot gas flow, which also increases efficiency.
• Figure 15 shows a combustion chamber brick 155 with a side surface 35, whereas Figures 16, 17 Sectional views of the Figure 15 are.
• Figure 15 shows the side surface 35 of a combustion chamber brick 155, as used in a combustion chamber 110, wherein a side surface 35 has two elongated recesses 40, 40' in which a holder engages from the rear and a corresponding through opening 42 to the rear 43 of the combustion chamber brick 155, which is opposite the top 44.
• an undercut 41 is present along the side surface with the recesses 40.
• Figure 16 is a cross-section through two combustion chamber bricks placed next to each other according to Figure 15 along the continuous opening 42', 42'' shown, whereas in Figure 17 a gap between two combustion chamber bricks 155 according to Figure 15 shown outside the opening 42 or elongated recess 40.
• Figure 18 shows a lower turbine housing part 550 with the guide vane recesses 553 and channel 557 in the contact surface 600 for the other, upper housing half.
• one or more additional recesses 630 and a seal are incorporated to reduce leakage in this area ( Fig. 19 ).
• Figure 20 shows a burner 70 which has a swirler in which air and fuel are mixed together.
• Two different guide vanes, 73' and 73'', of the swirler are in the Figure 21 shown and in a different, modified shallower angle (73') from the first position to a second position and/or a torsion of the guide vane 73'' along a trailing edge to achieve better turbulence.
• the dashed line on guide vane 73' indicates the original position of the swirler's guide vane, whereas the dashed line on guide vane 73'' shows how it is twisted along its longitudinal axis, which runs parallel to the leading edge.
• Gas turbines can be operated alone to drive a generator, but are often also used in combination with steam turbines in a combined cycle power plant.
• a steam turbine 6 Due to the higher power output generated by the gas turbine, the performance of a steam turbine 6 must also be adjusted. This is achieved in particular by, as described in Figure 22 It is shown that a blade root of a turbine running blade 883 receives a larger radius in the three recesses 886', 886'', 886′′′ of the fir tree base 880 than before.
• Combustion stability and dynamics also have a very high influence on the system's lifespan, so a control system 90 is installed here which registers the combustion dynamics and acceleration ( Fig 23 ).
• Some of the service measures can be carried out together because they are easier to perform together and can be carried out in parallel if necessary.
• Some measures can be offered and implemented free of charge to the operator of the plant to extend or even skip the next service interval, or to reduce operating costs through increased efficiency, in which the service provider participates.
• service contracts are often concluded, which offer the operator of the energy conversion plant a service maintenance contract that includes a guarantee of a certain operating time (lifespan) with certain performance characteristics and specified service intervals.
• the service provider not only repairs (refurbishes) what needs to be repaired because it can no longer be used or only for a short time, but also considers implementing measures during a service that allow the service period to be extended. to extend it until the next service interval or until the service interval after that.
• new burners with an aluminized coating can also be installed, eliminating the need for servicing the burner components at the next or subsequent service interval. This avoids downtime.
• a service measure can be used to extend the service life or to bring forward a service measure, thus significantly shortening the next service measure, because measures such as bearing removal, turbine blade removal, replacement of combustion chamber bricks, changes to the housing, etc. involve different maintenance times.
• the flexible refurbishment includes enhanced remote monitoring and diagnostic capabilities as part of the Omnivise Digital Services portfolio, as well as spare parts deliveries, scheduled maintenance, and performance guarantees throughout the plant's operating life. With its high efficiency at part load and its high operational flexibility, the combined cycle gas turbine power plant, along with its associated services, will complement the fluctuating renewable energy sources in the region as part of this flexible refurbishment.
• the long-term, flexible service goes a step further and offers a maintenance program that is individually tailored to specific needs and requirements.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Materials Engineering (AREA)
• Ceramic Engineering (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Supply And Distribution Of Alternating Current (AREA)
• Diaphragms For Electromechanical Transducers (AREA)

Applications Claiming Priority (3)

Related Parent Applications (1)

Publications (2)

Family

ID=70681764

Family Applications (4)

Family Applications Before (2)

Family Applications After (1)

Country Status (4)

Families Citing this family (1)

Citations (10)

Family Cites Families (20)

• 2019
  • 2019-05-22 DE DE102019207479.0A patent/DE102019207479A1/de not_active Withdrawn
• 2020
  • 2020-04-22 EP EP20725415.2A patent/EP3947915A1/fr active Pending
  • 2020-04-22 EP EP24198900.3A patent/EP4455452A3/fr active Pending
  • 2020-04-22 EP EP25207485.1A patent/EP4653667A3/fr active Pending
  • 2020-04-22 WO PCT/EP2020/061141 patent/WO2020233925A1/fr not_active Ceased
  • 2020-04-22 US US17/609,378 patent/US12055063B2/en active Active
  • 2020-04-22 EP EP24194316.6A patent/EP4438858A3/fr active Pending
• 2024
  • 2024-08-03 US US18/793,761 patent/US20240392684A1/en active Pending

Patent Citations (10)

Also Published As

Similar Documents

Legal Events