EP3156595A1 - Tube de canalisation et procédé de fabrication d'un tube de canalisation - Google Patents

Tube de canalisation et procédé de fabrication d'un tube de canalisation Download PDF

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Publication number
EP3156595A1
EP3156595A1 EP15189271.8A EP15189271A EP3156595A1 EP 3156595 A1 EP3156595 A1 EP 3156595A1 EP 15189271 A EP15189271 A EP 15189271A EP 3156595 A1 EP3156595 A1 EP 3156595A1
Authority
EP
European Patent Office
Prior art keywords
rolled sheet
sheet
channelling
channelling tube
tube
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP15189271.8A
Other languages
German (de)
English (en)
Inventor
Jonathan Mugglestone
Ulf Nilsson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP15189271.8A priority Critical patent/EP3156595A1/fr
Priority to PCT/EP2016/070584 priority patent/WO2017063786A1/fr
Publication of EP3156595A1 publication Critical patent/EP3156595A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/54—Building or constructing in particular ways by sheet metal manufacturing
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer

Definitions

  • the present invention relates to a method for assembling a channelling tube of a channelling tube assembly of a turbine assembly.
  • the present invention further relates to a channelling tube assembly and to an aerofoil-shaped turbine assembly such as turbine rotor blades and stator vanes, wherein a channelling tube assembly is used in such components to aid the cooling and sealing system.
  • high temperature turbines may include hollow blades or vanes incorporating channelling tubes like so-called jumper tubes to aid the cooling and sealing flow systems by minimising the heat pickup within these flows, which can be especially critical for a disc region of the aerofoil assembly.
  • jumper tubes are hollow tubes that run radially within the blades or vanes. Air is forced into and along these tubes. The design intent is to minimise the heat pick up of the flow as it passes through the tube.
  • the jumper tube is arranged with an air gap in respect to an aerofoil cavity wall. The air gap creates an insulating layer of relatively low thermal conductivity. Heat transfer across the air gap is largely by radiation.
  • the present invention provides a method for assembling a channelling tube of a channelling tube assembly of a turbine assembly.
  • the method at least comprises the steps of: Rolling a sheet designed to be the channelling tube and freezing the rolled sheet in a configuration so that in a frozen configuration of the rolled sheet a circumferential sector of the channelling tube forms at least one double wall.
  • a channelling tube can be provided that is assembled or manufactured easily, quickly and at low cost.
  • the resulting channelling tube has a multiple layered approach that utilises a single sheet to create both the main flow passage of the channelling tube and additional layers surrounding the main flow passage.
  • An air gap is located between each layer.
  • Each layer acts as a radiation shield, significantly reducing the total heat transfer between an aerofoil equipped with such a channelling tube and a channelling tube flow.
  • the use of a single radiation shield layer can divide the radiation heat transfer by half and thus the associated heat pickup of the channelling tube flow.
  • the radiative heat transfer is reduced by a factor of 1/(N_layers+1) for each layer.
  • the invention is a simple modification to the standard design, thus saving costs and construction efforts. Further, an existing design may be retrofitted easily. Although some cooling flow is used to buffer the air gap cavity, the amount is only a fraction of that required to reduce the heat pickup of the standard design when excessive flow through the channelling tube is used to compensate.
  • a channelling tube is intended to mean a structure that primarily provides a channel for a flow medium, like cooling medium/air, and that allows the flow medium to reach the structure to be cooled (see below).
  • the channelling tube may be any tube feasible for a person skilled in the art, like an impingement tube or a jumper tube.
  • the channelling tube is a jumper tube.
  • the cooling medium can be lead to the region to be cooled efficiently.
  • a jumper tube is intended to mean a hollow structure, like a tubular tube, that primary function is to connect cavities of platforms of the turbine assembly and to bridge the span of the aerofoil, to provide a passage for the cooling medium to flow with minimal heat pickup along the aerofoil or its cavity, respectively.
  • a jumper tube is no impingement tube, which has the primary function to cool walls of the cavity of the aerofoil housing the impingement tube by jets of cooling medium exiting a plurality of holes and impinging at the cavity wall.
  • a jumper tube in comparison with an impingement tube has or is likely to have:
  • a turbine assembly is intended to mean an assembly provided for a turbine engine, like a gas turbine, wherein the assembly possesses at least an aerofoil.
  • the turbine assembly has a turbine wheel or a turbine cascade with circumferential arranged aerofoils and an outer and an inner platform arranged at opponent ends of the aerofoil(s).
  • the part of the turbine assembly to be cooled may be any part arranged in radial direction between the aerofoil and an axis of the turbine engine and is preferably a disc.
  • a disc In case of a turbine wheel several aerofoils are connected with one another by a disc. Such a disc and the surrounding disc region are intended to be cooled by the turbine assembly.
  • a turbine assembly may comprise two aerofoils with platforms, wherein the aerofoils are arranged in flow direction of the working gas one after the other, one being an aerofoil of a turbine cascade (turbine vane) and the other an aerofoil of a turbine wheel (turbine blade).
  • the term "rolling” should be understood as the process by which, starting from a flat basically two-dimensional structure/sheet, a three-dimensional structure and specifically a basically circular or spiral structure is achieved. Due to this a flow direction is predetermined depending on the entry or exit of the cooling medium.
  • the term “freezing” should be understood as the achievement of an at least temporarily stable configuration of the rolled sheet in its rolled state.
  • the freezing may be done by any method, characteristic or device feasible for a person skilled in the art.
  • the freezing may be an in situ property of the material of the sheet, so that the rolled sheet maintains its rolled state because of the properties of the material used.
  • the freezing may be triggered by an extern influence or device.
  • the freezing may be done by connecting or permanently attaching at least two regions of the rolled sheet to one another. This can be done, for example, by a bonding method, like welding, bracing, gluing or the like.
  • a bonding method like welding, bracing, gluing or the like.
  • the resulting connection can be views as an expansion stopping device.
  • a circumferential sector is intended to mean a section of the rolled sheet where, after the rolling process, at least two layers of the sheet took a curved contour and are arranged basically in parallel or coaxial towards each other. Thus, each layer forms a wall of the double wall.
  • circumferential not only strictly circumferential shapes but also oval or slightly bended shapes should apply.
  • circumferential is used in the following text.
  • the circumferential section or the double wall section established after the freezing may have any circumferential length feasible for a person skilled in the art, like more than 90°, preferably more than 180° and most preferably more than 360°.
  • a single wall tube would be formed.
  • a tubular structure would be reached where a circumferential section with a double wall of about 90° would be formed.
  • the result would be a double wall of about 360°.
  • the first 360° would build an inner layer that surrounds a central passage of the channelling tube and the second 360° would build and outer layer radially restricting a circumferential 360° gap around the inner layer of the channelling tube and this the central passage.
  • a rolling of more than 720° like 1080° or 1440° a circumferential section with tree walls or even four walls would be build, resulting in a multiwall structure.
  • the rolled sheet or the resulting channelling tube would have a spiral shaped cross section, wherein the spiral would preferably be 720° or longer. In general, the greater the overlap the better the positive effects would be.
  • the used configuration would, for example, depend on the material used for the sheet, the radial distance adjusted between the layers of the rolled sheet (radial thickness of the resulting gap(s)), the dimensions of the channelling tube, the aerofoil or the cavity housing the channelling tube or the running properties of the turbine engine, like pressure or temperature. This would be selected from a person skilled in the art due to his knowledge in the field. Critical factors to be considered might be the integrity of the rolled sheet during the operation of the gas turbine engine, especially when subjected to temperature or pressure differences.
  • the extent of the resulting circumferential sector with the at least the double wall would of course be effected if there is a difference between the amount of overlap of the rolled sheet in the rolled state and the amount of overlap of the rolled sheet in the frozen state, like for example when the rolled sheet expands to a larger diameter after the rolling process and before the freezing. In this case the overlap would always be larger after in the rolled stated than in the frozen state.
  • the given degrees of overlap above shout refer to the extent of overlap in the frozen state.
  • the method comprises the step of: rolling the sheet in such a way so that it is rolled in a tight configuration in which an outer diameter of at least a radially outermost layer of the rolled sheet is smaller than an outer diameter of at least a radially outermost layer of the rolled sheet in its frozen configuration.
  • the sheet is rolled into a configuration where it can be assembled easily due to its smaller diameter.
  • the method comprises the step of: rolling the sheet over or around a centre tool, like a pin or a bar, in such a way so that it is rolled in a tight configuration in which an outer diameter of at least a radially outermost layer of the rolled sheet is smaller than an outer diameter of at least a radially outermost layer of the rolled sheet in its frozen configuration. Due to the centre tool the rolled sheet can be given a larger inner diameter than otherwise achievable. This centre tool is then removed, whilst the outer diameter of the rolled configuration remains unchanged. Moreover, the tightly rolled configuration can hold an expansion force to achieve the end configuration automatically. In case of this expansion the expansion occurred helically or spirally.
  • all diameters of the spirally arranged layer would increase from a smaller diameter to a wider diameter.
  • the diameter of all layers may change when the gas turbine engine is started and load is increasing, so does the pressure, leading to a movement in the spirally arranged layers outwards.
  • the adjusted inner diameter may be locked into position to ensure the integrity of the central passage.
  • a circumferential most inner end of the rolled sheet may be permanently attached to an adjacent next outer layer, e.g. by bracing or welding.
  • the centre tool it may be possible to adjust the inner diameter by using a belt-like connection. Therefore, the end designed to be the circumferentially most inner end would have an elongated aperture through which the opposed end would be inserted.
  • the sheet would comprise two radial locking slots at the circumferential position marking the desired inner diameter. The slots would engage with radial ends of the aperture at the circumferentially inner end to lock the inner diameter.
  • the method comprises the steps of: expanding the rolled sheet from its tight configuration and freezing the rolled sheet in its frozen configuration by at least a first expansion stopping device.
  • the expansion stopping device is preferably a radial expansion stopping device or radial restriction device.
  • the expansion stopping device can be achieved by any method or be any means or device feasible skilled in the art. Suitable would be, for example, the attachment of the most radially arranged outer end of the sheet to the next innermost layer of the sheet by any attachment method (bracing, welding etc.). Further, the expansion stopping device may be at least one assembly ring in which the tightly rolled sheet is inserted beforehand of the expansion, wherein a radial abutment of the outer most layer with the ring would stop the expansion. After the expansion the frozen configuration might be further stabilised by additional attachment of sections of the rolled sheet to one another or by transferring the rolled sheet into (an) end fixture(s) for mounting the channelling tube in the aerofoil.
  • the expansion stopping device is the at least one end fixture for mounting the channelling tube in the aerofoil.
  • the end fixture may be any device feasible for a person skilled in the art, like a ring, a clamp or a cap.
  • the method comprises the step of: inserting the tightly rolled sheet beforehand of the expansion in at least a first expansion stopping device.
  • the positioning in the first expansion stopping device can be done easily and the end configuration can be determined by the selected dimensions of the first expansion stopping device.
  • the method comprises the step of: equipping the sheet with at least one spacer. Due to this it can be ensured that a distance between the layers can be created to reduce heat transfer to radiation. In the best way of carrying out the invention substantially all of the cooling air flow would flow inside the most inner layer of the roll. This may be possible, for example if the layers (walls) are thin and the spaces (gap) between the layers are small. Moreover, the double wall structure or the gap between the layers of the rolled sheet can be held open. Hence, a collapsing of the gap along the spiral passage and thus a blockage of the flow passage for the cooling medium along the gap can be advantageously prevented.
  • the spacer may be any structure feasible for a person skilled in the art, like a dimple or a rib (horizontal or vertical).
  • the spacer would be a dimple thus minimising a large metal to metal contact area between adjacent layers of the rolled sheet and further minimising are blocking effects.
  • the spacer embodied as a rib it should preferably be arranged in parallel to a centre line of the finished channelling tube.
  • the ribs could be of a "dashed line type".
  • the spacer may be arranged in any feasible configuration or pattern at or on the sheet, e.g. in selected regions like a or the circumferential end(s) of the sheet or (homogeneously) all over the inner and/or outer surface of the sheet.
  • the equipping of the sheet with the spacer(s) may be easily done using a pressing or punching technique to form the spacers.
  • the spacer may be an embossment.
  • the equipping step can be done beforehand of the rolling or after the rolling/freezing of the sheet. To avoid inaccuracies or to achieve repeatable results it is preferred to do the equipping beforehand of the rolling.
  • the cooling medium entering the aerofoil needs to have a surplus pressure to reach its destination and there to cool or seal the component from hot gases.
  • the pressure inside the channelling tube is higher than the pressure on the outside. Due to this pressure difference across the channelling tube wall the most inner circumferential end of the rolled sheet would tend to seal against the next outward layer.
  • the method comprises the step of: equipping the sheet with at least one aperture.
  • This aperture may be located at any region feasible for a person skilled in the art, but preferably it is positioned in such a way to allow cooling medium to enter and/or the exit the spiral passage or the gap of the rolled sheet; and hence at the circumferential inner and/or outer end of the rolled sheet.
  • the aperture may be embodied in any way suitable for a person skilled in the art, like a hole (circular, oval, rectangular triangular etc.) or a corrugation that forms an aperture with an adjacent layer of the rolled sheet. In case of predrilled holes there is the need to drill them further away from the edge (circumferential end) to be clear of the layer below, to allow the cooling medium to flow.
  • the channelling tube is sealed such that the cooling medium it is transporting does not escape the gap.
  • This can be done by attaching the outer most circumferential end of the rolled sheet to the adjacent radially next inner layer.
  • the method comprises the step of: attaching at least one circumferential end (radially outer end) of the rolled sheet to a surface of the rolled sheet that is positioned radial inward to the at least one circumferential end (radially outer end).
  • This step can be an additional step to the freezing (see above) or it can be the same action in which the frozen configuration is achieved by the attachment process.
  • the method comprises the step of: attaching the at least first expansion stopping device to at least one axial end of the rolled sheet after the insertion of the rolled sheet in the at least first expansion stopping device and after the expansion of the rolled sheet.
  • the rolled sheet is held securely in its expanded and rolled end configuration.
  • the attachment is preferably done by welding or bracing.
  • a first and at least a second expansion stopping device are attached to at least one axial end of the rolled sheet.
  • due to thusly arranged expansion stopping deceives the main airflow through the channelling tube is ensured at all times.
  • the channelling tube assembly may be subjected to forces from trying to bend the channelling tube or vibrations. If only relied on a spring force between the rolled sheet and the expansion stopping device, the integrity of the assembly may be jeopardised.
  • the expansion stopping device is a cap. Since, only the location of the circumferential outer end of the rolled sheet is known, the rest of the spiral may vary in position. A cap would provide a sideways stability.
  • the method comprises the steps of: rolling the sheet, especially around a centre tool, in such a way so that it is rolled in a tight configuration in which an outer diameter of a radially outermost layer of the rolled sheet is smaller than an outer diameter of a radially outermost layer of the rolled sheet in its frozen configuration, inserting the rolled sheet in its tight configuration in at least a first expansion stopping device, expanding the rolled sheet from its tight configuration, freezing the rolled sheet in its frozen configuration by at least a first expansion stopping device, attaching at least one circumferential end of the rolled sheet in its frozen configuration to a surface of the rolled sheet that is positioned radial inward to the at least one circumferential end and attaching the at least first expansion stopping device to at least one axial end of the rolled sheet in its frozen configuration.
  • the method provides a channelling tube assembly that is manufactured easily and with low costs. Moreover, a state of the art turbine assembly can be easily retrofitted with such a channelling tube assembly. Furthermore, the heat transfer between the channelling tube and the aerofoil can be advantageously minimised.
  • the invention further refers to a use of a rolled sheet as a channelling tube and specifically, as a jumper tube.
  • the invention further relates to a channelling tube assembly for a turbine assembly comprising at least a channelling tube and at least a first freezing device.
  • the channelling tube is formed by a rolled sheet. Due to the inventive matter a channelling tube can be provided that has a multiple layered approach that utilises a single sheet to create both the main flow passage of the channelling tube and additional layers surrounding the main flow passage. An air gap is located between each layer. Each layer acts as a radiation shield, significantly reducing the total heat transfer between an aerofoil equipped with such a channelling tube and a channelling tube flow. For example, the use of a single radiation shield layer can divide the radiation heat transfer by half and thus the associated heat pickup of the channelling tube flow. As a general rule, for constant wall emissivity, the radiative heat transfer is reduced by a factor of 1/(N_layers+1) for each layer.
  • the invention is a simple modification to the standard design, thus saving costs and construction efforts. Further, an existing design may be retrofitted easily. Although some cooling flow is used to buffer the air gap cavity, the amount is only a fraction of that required to reduce the heat pickup of the standard design when excessive flow through the channelling tube is used to compensate.
  • the channelling tube comprises a central passage and a gap extending at least partly in circumferential direction around the central passage.
  • sufficient ventilation can be provided and the heat transfer between the channelling tube and the aerofoil can be advantageously minimised.
  • the first 360° of the sheet are the outer wall of the central passage as well as the inner wall of the gap.
  • the second 360° of the sheet represent the outer wall of the circumferential gap.
  • the gap is radially restricted by the inner and the outer walls.
  • the sheet is a thin metal sheet.
  • the rolling can be executed easily.
  • a robust channelling tube can be provided.
  • "thin” should be understood as with a thickness thicker than 0.2 millimetres (mm), preferably between 0.2 mm and 2 mm and most preferably about 0.3 mm and 0.75 mm. Due to the way the channelling tube is manufactured, the wall thickness would have to be smaller than the wall thickness used for a conventional channelling/jumper tube of the same diameter and length. This is due to the fact that a spring effect is wanted. In fact the inventive channelling tube will be stronger than a conventional tube due to its design.
  • the metal can be any metal or combination of metal or a metal alloy feasible for a person skilled in the art.
  • the metal is for example stainless steel or nimonic.
  • the rolled sheet comprises two axial ends.
  • the at least first expansion stopping device is positioned at at least one axial end.
  • a span wise length of the channelling tube can be designed for further functions, like for the entry or exit of the cooling medium into the gap.
  • the expansion can be stopped especially effective, when the channelling tube assembly comprises at least a second expansion stopping device. Moreover, a homogeneous distribution of the expansion stopping forces can be provided when the first expansion stopping and the at least second expansion stopping device are arranged at opposed axial ends of the rolled sheet.
  • the at least first expansion stopping device comprises a bottom with a solid part and at least one aperture.
  • different parts of the expansion stopping device can have different functions.
  • the solid part surrounds the at least one aperture.
  • the solid part covers the circumferential gap of the rolled sheet.
  • the at least one aperture is arranged at least partially flush with the central passage of the rolled sheet providing easy access for cooling air to travel the length of the channelling tube arrangement top cool adjacent regions, like the disc region.
  • the expansion stopping device(s) e.g. embodied as caps, seal(s) the end of the spiral. They will be the interface with e.g. the platforms.
  • At least one expansion stopping device that is used only for the expansion stop and during the freezing (e.g. welding/bracing the circumferential outer end to the adjacent layer). In other words, it is only an assembly fixture. Thereafter it would be removed and the rolled sheet would be positioned/installed in the turbine assembly or aerofoil, respectively, alone. After this instalment the axial ends would be added/sealed. To seal the ends in-situ in the aerofoil extra material may be added for machining on the aerofoil to a fixed dimension (corresponding to the length of the channelling tube).
  • the rolled sheet comprises at least one embossment.
  • selected means like spacers or corrugations, can be easily added. These means can perform specific function, like ensuring unblocked ventilation or the entry/exit of cooling medium into the gap.
  • the rolled sheet comprises a plurality of embossments. Preferably, they are distributed evenly over at least one surface of the sheet.
  • the embodiments function is that of a spacer and to minimise metal to metal contact it is advantageously a dimple.
  • the embossment may be embodied as a corrugation.
  • a corrugation e.g. positioned at the very edge of the sheet together with an adjacently arranged layer of the sheet can function as an entry or exit aperture.
  • the corrugation provides the opening but can also function as a spacer to prevent collapsing of the gap e.g. at circumferential ends of the rolled sheet.
  • the corrugation may be provided by punching appropriately sized dimples into a sheet and cutting the sheet so that the dimples are divided approximately in half, wherein the cutting edge will be a circumferential end of the sheet after the rolling. As a result, an inlet or outlet on the edge of the rolled up sheet is provided.
  • the "dimple” must at least cover the overlap between the edge of the sheet and the next layer. In other words, the “dimple” must exceed a contact area of the circumferential outer end and the adjacent most outer layer.
  • the rolled sheet comprises an inner end located at the radially most inner position of the rolled sheet and an outer end located at the radially most outer position of the rolled sheet.
  • the rolled sheet comprises at least one aperture positioned at the inner end of the sheet and/or wherein the rolled sheet comprises at least one aperture positioned at the outer end of the sheet.
  • these apertures may be formed by the corrugation or it may be (a) drilled or punched hole(s).
  • the inlet and outlet apertures/holes are at opposite ends of the length of the channelling tube.
  • the apertures are drilled or punched in the correct positions (for the finished product) in the sheet before it is rolled. It might be also possible to drill apertures in the end surfaces (solid part of the bottom) of the expansion stopping device (cap).
  • the invention further relates to a turbine assembly comprising at least one channelling tube assembly with a channelling tube and at least one freezing device.
  • the channelling tube is formed by a rolled sheet. Due to the inventive matter a channelling tube can be provided that has a multiple layered approach that utilises a single sheet to create both the main flow passage of the channelling tube and additional layers surrounding the main flow passage. An air gap is located between each layer. Each layer acts as a radiation shield, significantly reducing the total heat transfer between an aerofoil equipped with such a channelling tube and a channelling tube flow. For example, the use of a single radiation shield layer can divide the radiation heat transfer by half and thus the associated heat pickup of the channelling tube flow. As a general rule, for constant wall emissivity, the radiative heat transfer is reduced by a factor of 1/(N_layers+1) for each layer.
  • the invention is a simple modification to the standard design, thus saving costs and construction efforts. Further, an existing design may be retrofitted easily. Although some cooling flow is used to buffer the air gap cavity, the amount is only a fraction of that required to reduce the heat pickup of the standard design when excessive flow through the channelling tube is used to compensate.
  • a freezing device is intended to mean any device or effect that triggered or assures the frozen state of the rolled sheet.
  • the freezing device is the expansion stopping device. It is also possible that the freezing device is a further means in addition to the expansion stopping device, like a material property or an external impulse acting on the rolled sheet.
  • the turbine assembly comprises a basically hollow aerofoil with at least one cavity spanning the aerofoil in span wise direction of the aerofoil and housing at least one channelling tube assembly with a channelling tube comprising a central passage and a gap extending at least partly in circumferential direction around the central passage, wherein the rolled sheet comprises an inner end located at the radially most inner position of the rolled sheet and an outer end located at the radially most outer position of the rolled sheet and/or wherein the rolled sheet comprises at least one entry aperture positioned at the radially inner end of the sheet to allowing cooling medium to enter from the central passage into the gap and/or wherein the rolled sheet comprises at least one exit aperture positioned at the radially outer end of the sheet to allow the cooling medium to exit the gap.
  • a “basically hollow aerofoil” means an aerofoil with a casing, wherein the casing encases at least one cavity.
  • a structure like a rip, which divides different cavities in the aerofoil from one another and for example extends in a span wise direction of the aerofoil, does not hinder the definition of "a basically hollow aerofoil".
  • the aerofoil is hollow.
  • the basically hollow aerofoil referred as aerofoil in the following description, has two cooling regions, a channelling cooling region at a leading edge of the aerofoil and a state of the art pin-fin/pedestal cooling region at the trailing edge. These regions could be separated from one another through a rip.
  • the aerofoil assembly further comprises outer platform and an inner platform, each comprising at least one cavity, which are in flow communication with each other over the central passage of the channelling tube.
  • Each platform preferably comprises at least one wall segment being arranged basically perpendicular to the span wise direction of the aerofoil, wherein the wall segments of the platforms are arranged at opposite ends of the aerofoil and basically in parallel towards each other.
  • a wall segment is intended to mean a region of the turbine assembly which confines at least a part of a cavity and in particular, a cavity of the aerofoil.
  • the wall segment comprises an aperture that provides access to the cavity of the aerofoil and may partially cover this cavity.
  • the inserted channelling tube may at least span a part of the aperture in span wise direction.
  • an arrangement of the wall segment as "basically perpendicular" to a span wise direction should also lie a divergence of the wall segment in respect to the span wise direction of about 30°.
  • the wall segment is arranged perpendicular to the span wise direction.
  • a “basically parallel arrangement” is intended to mean a divergence of the arrangement of the wall segments in respect to each other of about 30° from their strictly parallel arrangement.
  • a span wise direction of the aerofoil is defined as a direction extending basically perpendicular, preferably perpendicular, to a direction from the leading edge to the trailing edge of the aerofoil.
  • a cavity of the platform is intended to mean an at least at two , preferably four sides enclosed space that is radially encased at at least one radial side from the platform or its wall segment.
  • An opposed radial side may for example be restricted by a casing, like a casing of the turbine engine in which the turbine assembly is mounted.
  • a flow communication through slots or apertures in the side wall, the casing or between them should not hinder the meaning of enclosed or encased.
  • the channelling tube may be arranged in the cavity of the aerofoil with a clearance between the most outer layer of the tube and an inner surface of the cavity.
  • the channelling tube may be arranged coaxially with a cavity axis or it may be arranged off centre in respect to the axis. In other words, as long as the minimum distance is exceeded the distance between the aerofoil wall and the channelling tube does not have to be equal around its circumference.
  • the clearance may extend all around an outer contour, preferably the circumference, of the channelling tube preventing contact of the tube with the cavity wall and minimising heat transfer to the aerofoil.
  • the cooling medium entering the gap or spiral of the channelling tube is only a minor fraction and/or less than 10% of the cooling medium entering the channelling tube from the cavity of the platform.
  • the purpose of the cooling medium traveling the gap is to vent away the radiative heat transfer or rather heat flux.
  • the needed amount of cooling medium entering and traveling the gap will for example depend on the used methods of the aerofoil and/or the channelling tube.
  • the heat flux may e.g. occur between two metal surfaces or a metal and a ceramic surface (coating of the channelling tube). In case of a ceramic surface and the low thermal conductivity of a ceramic would significantly lower the need for the purge flow and would for example be less than 2%.
  • the gap provides a by-pass for cooling medium in respect to the main cooling flow along the channelling tube.
  • the main flow of cooling medium is intended for cooling of the disc region and surrounding regions.
  • the entry or exit apertures into the spiral gap may be positioned directly adjacent to the outer and/or inner platform.
  • the phrasing "directly adjacent” should be understood as in near proximity Moreover, the exits occur directly adjacent to the wall segments of the outer and the inner platform, respectively. Furthermore, the flow of cooling medium exits the gap or the clearance around the channelling tube into the gas path and especially away from the disc to be cooled.
  • the aerofoil comprises a single cavity.
  • the invention could also be realized for an aerofoil comprising two or more cavities e.g. each of them accommodating at least one channelling tube and/or being a cavity as a part of the fin-pin/pedestal cooling region.
  • a cooling flow of the cooling medium flowing in span wise direction and spirally along the gap provides an insulation for the channelling tube to prevent a heat transfer between the channelling tube and the cavity wall of the aerofoil.
  • heat pickup of the channelling tube flow can be minimised by using a buffer layer of cooling air to shield the channelling tube effectively.
  • the temperature rise of the channelling tube flow can be adjusted by varying the amount of flow through the buffer cavity.
  • At least 80% preferably at least 90% and most preferably at least 95% of a span wise length of the gap are travelled by the cooling medium.
  • the metal temperature of the aerofoil may vary along the span wise length and the higher the temperature the more important the insulation effect. Hence, a proper insulation effect preferably along the whole span wise length will be most beneficial.
  • the cavity wall of the aerofoil or at least one of the platforms comprises at least one aperture. Consequently, the discharged cooling medium can be directed away from the disc region to be cooled by the main cooling flow through the channelling tube.
  • This aperture may be positioned at any suitable location of the aerofoil or platform, preferably it is near the exit aperture of the spiral to minimize travelling distances or to avoid turbulences.
  • the aerofoil comprises a suction side and a pressure side, wherein the aperture for the exit of the cooling medium from the aerofoil assembly directs the cooling flow of the cooling medium in direction of the pressure side. Consequently, the cooling medium exits the aerofoil at the pressure side. Due to this, the cooling flow will exit at a location of the aerofoil where the highest heat transfer will be present. This is caused by the so-called secondary flow effect where the main gas flow passing between the adjacent aerofoils also rotates, moving along the wall of one aerofoil to the opposite aerofoil. Moreover, since an aerofoil surface at the pressure side has a larger region it is able to discard the flow with less aerodynamic loss. In turn, a suction side flow must be discarded towards the leading edge before the throat region.
  • the aerofoil comprises a leading edge and a trailing edge.
  • a sufficient flow of cooling medium for the cooling of the disc region can be provided, when the channelling tube is arranged near the leading edge. Since, the leading edge has a relatively large cross section in comparison with other regions of the aerofoil, a low pressure drop can be provided in the channelling tube. This results in a low velocity of the cooling medium traveling the channelling tube. Furthermore, the low velocity creates low convective heat transfer inside the channelling tube, helping to minimise the heat pick up.
  • the aerofoil is a turbine blade or vane, and especially a nozzle guide vane.
  • the present invention is described with reference to the above exemplary turbine engine having a single shaft or spool connecting a single, multi-stage compressor and a single, one or more stage turbine.
  • the present invention is equally applicable to two or three shaft engines and which can be used for industrial, aero or marine applications.
  • reference will only be made to a vane, for the sake of simplicity, but it is to be understood that the invention is applicable to both blades and vanes of a turbine engine.
  • upstream and downstream refer to the flow direction of the airflow and/or working gas flow through the engine 70 unless otherwise stated.
  • the terms forward and rearward refer to the general flow of gas through the engine 70. If used in context to the engine 70, the terms axial, radial and circumferential are made with reference to a rotational axis 80 of the engine 70.
  • FIG 1 shows an example of a gas turbine engine 70 in a sectional view.
  • the gas turbine engine 70 comprises, in flow series, an inlet 72, a compressor section 74, a combustion section 76 and a turbine section 78, which are generally arranged in flow series and generally in the direction of a longitudinal or rotational axis 80.
  • the gas turbine engine 70 further comprises a shaft 82 which is rotatable about the rotational axis 80 and which extends longitudinally through the gas turbine engine 70.
  • the shaft 82 drivingly connects the turbine section 78 to the compressor section 74.
  • air 84 which is taken in through the air inlet 72 is compressed by the compressor section 74 and delivered to the combustion section or burner section 76.
  • the burner section 76 comprises a burner plenum 86, one or more combustion chambers 88 defined by a double wall can 90 and at least one burner 92 fixed to each combustion chamber 88.
  • the combustion chambers 88 and the burners 92 are located inside the burner plenum 86.
  • the compressed air passing through the compressor section 74 enters a diffuser 94 and is discharged from the diffuser 94 into the burner plenum 86 from where a portion of the air enters the burner 92 and is mixed with a gaseous or liquid fuel.
  • the air/fuel mixture is then burned and the combustion gas 96 or working gas from the combustion is channelled to the turbine section 78 via a transition duct 98.
  • This exemplary gas turbine engine 70 has a cannular combustor section arrangement 76, which is constituted by an annular array of combustor cans 90 each having the burner 92 and the combustion chamber 88, the transition duct 98 has a generally circular inlet that interfaces with the combustor chamber 88 and an outlet in the form of an annular segment.
  • An annular array of transition duct outlets form an annulus for channelling the combustion gases 96 to the turbine section 78.
  • the turbine section 78 comprises a number of blade carrying discs 100 or turbine wheels 102 attached to the shaft 82.
  • the turbine section 78 comprises two discs 100 each carry an annular array of turbine assemblies 14, which each comprises an aerofoil 62 embodied as a turbine blade.
  • the number of blade carrying discs 100 could be different, i.e. only one disc 100 or more than two discs 100.
  • turbine cascades 104 are disposed between the turbine blades.
  • Each turbine cascade 104 carries an annular array of turbine assemblies 14, which each comprises an aerofoil 62 in the form of guiding vanes, which are fixed to a stator 106 of the gas turbine engine 70.
  • Between the exit of the combustion chamber 88 and the leading turbine blades inlet guiding vanes or nozzle guide vanes 108 are provided and turn the flow of working gas 96 onto the turbine blades.
  • the combustion gas 96 from the combustion chamber 88 enters the turbine section 68 and drives the turbine blades which in turn rotate the shaft 82.
  • the guiding vanes 108 serve to optimise the angle of the combustion or working gas 96 on to the turbine blades.
  • the turbine section 78 drives the compressor section 74.
  • the compressor section 74 comprises an axial series of guide vane stages 110 and rotor blade stages 112 with turbine assemblies 14 comprising aerofoils 62 or turbine blades or vanes, respectively.
  • the rotor blade stages 112 comprise a rotor disc supporting an annular array of blades.
  • the compressor section 74 also comprises a stationary casing 114 that surrounds the rotor stages 112 and supports the vane stages 110.
  • the guide vane stages 110 include an annular array of radially extending vanes that are mounted to the casing 114. The vanes are provided to present gas flow at an optimal angle for the blades at a given engine operational point.
  • Some of the guide vane stages 110 have variable vanes, where the angle of the vanes, about their own longitudinal axis, can be adjusted for angle according to air flow characteristics that can occur at different engine operations conditions
  • the casing 114 defines a radially outer surface 116 of the passage 118 of the compressor section 74.
  • a radially inner surface 120 of the passage 118 is at least partly defined by a rotor drum 122 of the rotor which is partly defined by the annular array of blades.
  • FIG 2 shows in a perspective view a turbine assembly 14 of the gas turbine engine 70.
  • the turbine assembly 14 comprises a basically hollow aerofoil 62, embodied as a nozzle guide vane 108, with two cooling regions, specifically, an channelling cooling region 124 and a fin-pin/pedestal cooling region 126.
  • the former is located at a leading edge 128 and the latter at a trailing edge 130 of the aerofoil 62.
  • an outer platform 134 and an inner platform 134' are arranged at opposed ends 132, 132' of the aerofoil 62.
  • the outer and the inner platform 134, 134' both comprise a wall segment 136, 136' which are oriented basically perpendicular to a span wise direction 66 of the aerofoil 62.
  • Each wall segment 136, 136' has an insertion aperture 138 which provides access to the aerofoil 62 (only the insertion aperture of wall segment 136 could be seen in FIG 3 ).
  • a circumferential direction 140 of a not shown turbine wheel several aerofoils 62 could be arranged, wherein all aerofoils 62 where connected through the inner and the outer platforms 134, 134' with one another.
  • a casing 142 of the aerofoil 62 comprises or forms a cavity 64 spanning the aerofoil 62 in span wise direction 66, wherein the cavity 64 is located in the region of the leading edge 128.
  • Via the insertion aperture 138 is a channelling tube arrangement 12 inserted inside the cavity 64 for cooling purpose.
  • the outer platform 134 and the inner platform 134' each comprises at least one cavity 144, 144'.
  • This cavity 144, 144' either extends between the wall segment 136 of the outer platform 134 and the outer casing 114 of the gas turbine engine 70 or the wall segment 136' of the inner platform 134'2 and an inner casing 114' of the gas turbine engine 70.
  • the cavities 134, 134" are in flow communication with each other over a channelling tube 10 of a channelling tube arrangement 12.
  • the channelling tube arrangement 12 is inserted via the insertion aperture 138 into the cavity 64 of the aerofoil 62.
  • the channelling tube 10 extends in span wise direction 66 along a whole length 1 of the cavity 64 of the aerofoil 62. Further, during an operation of the turbine assembly 14 the channelling tube 10 provides a flow path for a flow of a cooling medium 68, like air, from the cavity 144 of the outer platform 134 to the cavity 144' of the inner platform 134' where the cooling medium 68 exits into the gas path to cool a part of a aerofoil assembly, like a disc 100 in a disc region of adjacently arranged turbine blades (not shown in detail).
  • a cooling medium 68 like air
  • the channelling tube 10 is arranged in the cavity 64 of the aerofoil 62 in such a way that a circumferential clearance 146 is formed between an outer surface 148 of the channelling tube 10 and an inner surface 150 of a cavity wall 152 of the cavity 64 of the aerofoil 62 (see also FIG 12 and 13 ).
  • the channelling tube assembly 12 comprises the channelling tube 10 and several expansion stopping devices 26, 26', 28 or freezing devices 26, 26', 28.
  • the channelling tube 10 is formed by a rolled sheet 16 (see also FIG 12 and 13 ).
  • a method for assembling or manufacture the a channelling tube 10 and the channelling tube arrangement 12 will be described in the following passages in reference to FIG 4 to 11 .
  • the assembling process starts with a thin, flat metal sheet 16, for example, made out of stainless steel.
  • the sheet 16 is designed to be the channelling tube 10.
  • This sheet 16 has e.g. a thickness of 0.4 mm.
  • it has for example a rectangular shape and its horizontal length L is longer than its vertical length 1, wherein the vertical length 1 is basically the span of the aerofoil 62.
  • the horizontal ends of the sheet 16 are equipped each with at least one aperture 32 (one aperture 32 for each side is shown in bold lines and additional optional apertures are shown in dashed lines in FIG 4 ).
  • the apertures 32 may for example be drilled into the sheet 16.
  • the sheet 16 is rolled into a tight configuration, coil or spiral.
  • FIG 5 and 6 show a side and top view of the sheet 16 in its tightly rolled state.
  • the sheet is rolled around a centre tool in the form of a pin to limit an inner diameter of the spiral or to ensure a desired inner diameter of a central passage 42 (see below).
  • the rolling is done in such a way so that it is rolled in a tight configuration in which an outer diameter d of a radially outermost layer 22 of the rolled sheet 16 is smaller than an outer diameter D of a radially outermost layer 24 of the rolled sheet 16 in its frozen configuration (compare FIG 6 and 11 ).
  • the tightly rolled sheet 16 is inserted in two expansion stopping devices 26, 26'.
  • the expansion stopping devices 26, 26' are positioned at opposed axial ends 38, 40 of the rolled sheet 16.
  • the expansion stopping device 26 is embodied as a cap with a ring segment 154 and a bottom 48 arranged basically perpendicular to the ring segment 154.
  • the bottom 48 comprises a solid part 50 and an aperture 52 that is surrounded by the aperture.
  • the tightly rolled sheet 16 will be expanded and it expands spirally. Due to the expansion stopping devices 26, 26' the rolled sheet 16 will be frozen in its expanded state which is the frozen configuration.
  • This configuration is basically shown in FIG 10 that shows the channelling tube assembly 12 in a side view in an assembled state.
  • the circumferential most outer end 34 of the rolled sheet 16 in its frozen configuration is attached, e.g. by welding or bracing a connection seam 156, to a surface 36 of the rolled sheet 16 that is positioned radial inward to the circumferential end 34. Due to the attachment or the connecting seam 156 a further expansion stopping device 28 is formed. Moreover, to secure the expansion stopping devices 26, 26' they are attached, e.g. by welding or bracing a connection seam 156, to the axial ends 38, 40 of the rolled sheet 16 in its frozen configuration.
  • the expanded rolled sheet 16 or the channelling tube 10 in its frozen configuration comprises a central passage 42 and a spiral gap 44 extending in circumferential direction 46 around the central passage 42 (Expansion stopping device 26' is not shown in FIG 11 ).
  • the central passage 42 is surrounded by the first 360° stretch of the rolled sheet 16 or inner layer 158.
  • the most outer layer 22 has the wide expansion diameter D and surrounds the last 360° stretch of the gap 44.
  • the channelling tube 10 or the rolled sheet 16 is frozen in a configuration in that a circumferential sector 18 of the channelling tube 10 forms at least one double wall 20.
  • a quadruple wall is formed.
  • the dimensions are for example selected in such that the rolled sheet 16 or the spiral would only take up about 50% to 20% of the diameter D. Consequently, the central passage 42 would take about 50% to 80% of the diameter D.
  • the arrangement of the expansion stopping devices 26, 26' in respect to the rolled sheet 16 is in such a way so that the solid part 50 of the bottom 48 covers the circumferential gap 44 of the rolled sheet 16 and the aperture 52 is arranged flush with the central passage 42 of the rolled sheet 16 (not shown in detail).
  • the apertures 32 to allow the cooling medium 68 to enter the gap 44 from the central passage 42 are not specifically shown in FIG 10 and 11.
  • the aperture 32 at the inner end 56 will be an entry aperture 58 to allowing cooling medium 68 to enter from the central passage 42 into the gap 44 and the outer end 34 will be an exit aperture 60 to allow the cooling medium 68 to exit the gap 44.
  • these apertures 58, 60 can be arranged at any span wise position at the circumferential ends 34, 56. Most beneficially, would for example be the positioning of the entry aperture 58 near the upper expansion stopping device 26 and the exit aperture near the lower expansion stopping device 26'. In an assembled state the entry would occur near the outer platform 134 and the exit near the inner platform 134'. As stated above also more than one aperture for entry or exit can be provided. For better presentability of the channelling tube 10 and its positioning in cavity 64 the rolled sheet 16 shown in FIG 3 is only shown with a double wall design.
  • the entry aperture 58 may be arranged in flow direction of the cooling medium 68 at a radial beginning of the clearance 146 or directly adjacent to the wall segment 136 of the outer platform 134. This allows a fraction 160 of the cooling medium 68 access into the gap 44. Further, to allow the cooling medium 68 to exit the gap 44 the exit aperture 60 is arranged near the inner platform 134' (The actual location of the aperture 60 is not shown in FIG 3 , but a slightly circumferentially off-set position to depict its basic location. Aperture 60 would be located with a circumferential distance from end 34 and the connecting seam 156.).
  • the cavity wall 152 of the aerofoil 62 comprises an aperture 162 arranged in flow direction of the cooling medium 68 e.g. at a radial end of the clearance or directly adjacent to the inner platform 134' or its wall segment 136'.
  • the wall segment 136' of the inner platform 134' may comprise an aperture 162', what is shown in dashed lines in FIG 3 .
  • the positioning of the channelling tube 10 in the aerofoil 62 can be seen in FIG 12 that shows a cross section along line XII-XII in FIG 3 . Further, the positioning of aperture 162 in the cavity wall 152 can be seen in FIG 13 that shows a cross section along line XIII-XIII in FIG 3 .
  • the aperture 162 in the cavity wall 152 directs the cooling flow of the cooling medium in direction of a pressure side 164 of the aerofoil 62 opposed arranged to the suction side 166.
  • Cooling medium 68 flows from the cavity 144 of the outer platform 134 into the central passage 42 of the channelling tube 10. A fraction 160 of the cooling medium 68 exits the channelling tube 10 through the entry aperture 58 and enters the gap 44. Inside the gap 44 the cooling medium 68 travels along the spiral as well as in span wise direction 66. However, the general direction is still the flow in span wise direction 66 from the outer platform 134 in direction to the inner platform 134'. Adjacent of the inner platform 134' the cooling medium 68 exits the gap 44 through exit aperture 60 into clearance 146 and from there through the aperture 162 in the cavity wall 152 of the aerofoil 62 to be exhausted into a flow path of a flow medium of the gas turbine engine 70.
  • the cooling flow 38 of the cooling medium 68 established long the gap 44 provides insulation for the channelling tube 10 to prevent a heat transfer between the channelling tube 10 and the cavity wall 152 of the aerofoil 62.
  • a main fraction 168 of cooling medium 68 travels the central passage 42 of the channelling tube 10 along a whole span of the aerofoil 62 and exits into the cavity 144' of the inner platform 134'. From there it is exhausted in such a way that it cools the disc 100 of up- and downstream arranged discs 100 of adjacent turbine wheels.
  • FIG 14 to 16 alternative embodiments of the sheet 16 and the channelling tube assembly 12 are shown. Components, features and functions that remain identical are in principle substantially denoted by the same reference characters. To distinguish between the embodiments, however, the letter “a” and “b” has been added to the different reference characters of the embodiment in FIG 14 to 16 . The following description is confined substantially to the differences from the embodiment in FIG 1 to 13 , wherein with regard to components, features and functions that remain identical reference may be made to the description of the embodiment in FIG 1 to 13 .
  • FIG 14 shows an alternatively embodied sheet 16a.
  • the sheet 16a is equipped with spacers 30.
  • the spacers 30 are imprinted embossments 54.
  • the spacers 30 span the gap of the channelling tube from one layer to an adjacent layer 22, 24, 158 to ensure an unhindered flow of cooling medium and an integrity of a gap.
  • FIG 15 and 16 show a further alternatively embodied sheet 16b and an alternative channelling tube assembly 12b.
  • the sheet 16b is equipped with embossments 54 in the form of a corrugation 170.
  • the corrugation 170 is inserted at a circumferentially most outer end 34 of the rolled sheet 16b.
  • the corrugation 170 together with an adjacent surface 36 of a most outer layer 24 of the rolled sheet 16b form an exit aperture 60 for cooling medium to exit the channelling tube 10. Sections of end 34 positioned vertically between the apertures 60 are attached (braced/welded) to surface 36.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15189271.8A 2015-10-12 2015-10-12 Tube de canalisation et procédé de fabrication d'un tube de canalisation Withdrawn EP3156595A1 (fr)

Priority Applications (2)

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EP15189271.8A EP3156595A1 (fr) 2015-10-12 2015-10-12 Tube de canalisation et procédé de fabrication d'un tube de canalisation
PCT/EP2016/070584 WO2017063786A1 (fr) 2015-10-12 2016-09-01 Tube de canalisation et son procédé de fabrication

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Application Number Priority Date Filing Date Title
EP15189271.8A EP3156595A1 (fr) 2015-10-12 2015-10-12 Tube de canalisation et procédé de fabrication d'un tube de canalisation

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US11512601B2 (en) 2020-05-18 2022-11-29 Raytheon Technologies Corporation Airfoil vane with coated jumper tube
CN111794807B (zh) * 2020-06-24 2022-01-11 中船重工龙江广瀚燃气轮机有限公司 一种燃驱压缩机组用动力涡轮进口导向器

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3707750A (en) * 1968-11-14 1973-01-02 Mtu Muenchen Gmbh Method for manufacturing a turbine blade
US5516260A (en) * 1994-10-07 1996-05-14 General Electric Company Bonded turbine airfuel with floating wall cooling insert

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5488825A (en) * 1994-10-31 1996-02-06 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
US7007488B2 (en) * 2004-07-06 2006-03-07 General Electric Company Modulated flow turbine nozzle

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3707750A (en) * 1968-11-14 1973-01-02 Mtu Muenchen Gmbh Method for manufacturing a turbine blade
US5516260A (en) * 1994-10-07 1996-05-14 General Electric Company Bonded turbine airfuel with floating wall cooling insert

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