EP1165939A1 - Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine - Google Patents

Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine

Info

Publication number
EP1165939A1
EP1165939A1 EP00920564A EP00920564A EP1165939A1 EP 1165939 A1 EP1165939 A1 EP 1165939A1 EP 00920564 A EP00920564 A EP 00920564A EP 00920564 A EP00920564 A EP 00920564A EP 1165939 A1 EP1165939 A1 EP 1165939A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine blade
core
supply channels
coolant
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.)
Granted
Application number
EP00920564A
Other languages
German (de)
English (en)
Other versions
EP1165939B1 (fr
Inventor
Peter Tiemann
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 EP00920564A priority Critical patent/EP1165939B1/fr
Publication of EP1165939A1 publication Critical patent/EP1165939A1/fr
Application granted granted Critical
Publication of EP1165939B1 publication Critical patent/EP1165939B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc

Definitions

  • the invention relates to a cast gas turbine blade through which coolant flows, in particular gas turbine rotor blade with a blade root, which is inserted into a rotatable disk of the gas turbine and which has a plurality of supply channels for an internal cooling system and which has a distributor space, coolant being able to be fed to the supply channels by means of a supply channel to the disk that communicates with the supply channels through the distribution room.
  • the invention further relates to a device for casting a
  • Gas turbine blade with a casting core which has core ribs forming supply channels, and a method for producing a cast gas turbine blade.
  • a gas turbine blade is known from US Pat. No. 4,344,738, which is inserted with a blade root into a disk transverse groove of a rotatable disk of the gas turbine, the disk having a supply duct for supplying the gas turbine with coolant.
  • the feed channel opens below the blade root in the transverse disk groove intended for receiving the blade root.
  • Supply channels lead from the blade root, through which the coolant is led into the internal cooling system.
  • the supply channels have predominantly edge-entry openings.
  • US Pat. No. 4,992,026 discloses a gas turbine blade through which a coolant flows and with an internal cooling system, the coolant being introduced into the blade root through supply channels and introduced into the internal cooling system through supply channels.
  • the supply channels have edges set at right angles at their transitions from the blade root.
  • the internal cooling of the gas turbine blade is intended to prevent excessive heating of the blade material caused by high operating temperatures, which can lead to serious damage.
  • a further possibility of forming the supply duct area in the lower blade root is to provide a so-called distributor space, from which the supply ducts for the internal cooling system originate and which is supplied with coolant from the supply duct of the disk.
  • the distribution space should essentially serve a reliable and uniform distribution of the coolant to the supply channels, with only slight losses of the coolant being allowed to occur.
  • this distribution space is generally rectangular and in particular has right-angled transitions of the supply channels to the distribution space.
  • the edged structure of the entrances to the supply channels creates strong flow vortices, which in principle ensure good cooling of the flow areas.
  • the distributor space since the distributor space is located in the blade root, it is not subjected to excessive heat and therefore has only a low cooling requirement.
  • This condition can be improved by mechanically reworking the inputs of the supply channels in the distributor space after the casting process.
  • this has to be done predominantly by hand and is therefore very labor-intensive.
  • this procedure does not ensure that all supply channels of a gas turbine blade have the desired shape or all gas turbine blades of one type have the same flow resistance, which would, however, be necessary for a calculation of the flow properties and optimal utilization of the cooling medium that meets the high quality requirements.
  • the object of the invention is therefore to provide a coolant-flowed, cast gas turbine blade, in particular a gas turbine blade, which has flow-optimized transitions from the distribution space to the supply channels, that is to say low flow resistances at the outlet openings of the distribution space.
  • Distribution room and internal cooling system should be able to be produced in a single manufacturing process, the casting process.
  • Another object of the invention is to provide a device and a method for producing such a coolant-flowed, cast gas turbine blade with a corresponding distributor space.
  • the object directed to a cast gas turbine blade through which coolant flows is achieved in that a cast distributor space is present which has rounded or flattened inlet openings of the supply ducts.
  • the rounded or flattened inlet openings of the supply channels, which adjoin the distribution space, ensure that the flow resistance of the cooling medium is minimized, in particular in the transition area from the distribution space to the supply channels.
  • the flow of the coolant it remains mostly laminar.
  • the coolant can thus - with a corresponding edge-free transition solution from the supply duct to the distribution space - flow almost freely into and out of the distribution space through the supply ducts and in this way reaches the internal cooling system quickly and with low losses, which is particularly important for the hot and coolant-intensive areas of the Gas turbine blade, for example the contact edge area, leads to a greatly extended service life.
  • the coolant supplied is better used.
  • the medium fed through the supply channel of the disk no longer has to be introduced into the internal cooling system through two 90 ° angles, but is instead conducted in a flowing, continuous flow movement directly to the internal cooling system.
  • the cooling medium flows around, there are no cavities in which the cooling medium is located as in dead zones.
  • the supplied cooling medium is swirled very little due to the rounding or flattening of the inlet openings.
  • the inlet openings of the supply channels connect directly to the distribution space and are produced with it in a manufacturing process.
  • the rounding or flattening is designed to be reproducible through the casting process.
  • a series of gas turbine blades can have the same, predetermined sizes or dimensions for the inlet openings and the distributor space. This provides the basis for a reliable predetermination of the coolant requirement or the coolant function. This is particularly important in order to ensure that even remote parts of the gas turbine blades are reliably cooled and thus wear due to overheating is minimized.
  • the present invention cools the coolant even at a low pressure due to the low flow rate. introduced through the distribution space into the supply channels and thus only escapes to a small extent through the space between the blade root and the rotating disk of the gas turbine. This minimizes the loss of the coolant and makes optimal use of the coolant.
  • the distribution space is preferably designed in the form of a semi-ellipsoid. Its base area also corresponds to the largest cross section of the ellipsoid and is delimited by the disk when the gas turbine blade is inserted into a disk groove.
  • the side surfaces of the semi-ellipsoid and also the transitions between the side surfaces are rounded. This simple geometry is easy to manufacture and reliably prevents the formation of dead zones in which the introduced coolant is located. Due to the missing edges, only slight turbulence occurs on the walls of the distribution room, which leads to negligible flow losses. Due to the ellipsoidal shape, it is possible to control the flow of coolant to the supply channels adjacent to different areas of the ellipsoid.
  • a further optimization of the coolant flow is achieved in that the rounded or flattened inlet openings adjoin one another in an optimized flow or are adjacent to one another.
  • Optimized in terms of flow means that the necessary flow deflections caused by the relative position of two inlet openings or the distributor space and one inlet opening relative to one another take place with the least possible turbulence in the flow. This is done in particular by rounding off the edges which result from the meeting of the respective roundings of the inlet openings.
  • the optimization of the flow vortex preventing shape is possible through the use of the rounded one-piece cast core individually tailored to the requirements placed on a particular type of gas turbine and without post-processing in the casting process.
  • a predetermined coolant supply can be easily adjusted in that the cross section of the supply duct and the local changes in the cross sections of the distributor space are matched to the cross sections of the inlet openings downstream in terms of flow.
  • the changes in cross-section of the distribution space correspond, for example, in the height and width to the shape of a semi-ellipsoid.
  • the transitions between the inlet openings or around the inlet openings are referred to as transition cross sections. Due to the rounding or flattening of the inlet openings, a larger inlet opening cross-section is created directly at the distributor space, which cross-section is then reduced at the transition to the supply duct.
  • the supply duct has an essentially constant cross section, but there may also be a rounding or flattening of a supply duct to improve the flow properties, as a result of which the cross section to the distributor space increases.
  • the cross-sections described are coordinated, i.e. predetermined cross-sectional relationships for matching the coolant supply are taken into account. This is necessary if, for example, there is an increased coolant requirement due to a high operating temperature or special designs of the internal cooling system in a gas turbine blade which require high coolant pressures or have a high leakage rate.
  • the lowermost longitudinal rib of the blade root which is closest to the axis of rotation of the gas turbine, is extended along a main axis of the gas turbine blade. With its longitudinal ribs, the blade root is held on the undercuts of the disk groove in which it is inserted. The distribution space for the cooling medium is housed in the lowest longitudinal rib.
  • the blade root is extended according to the invention in the area of the lowest longitudinal rib. This extension takes place along the main axis of the gas turbine blade, that is to say, when the gas turbine blade is inserted, perpendicular to the circumference of the disk. Due to the extended design of the lower longitudinal rib, the stability of the holding device in the blade root is still ensured and the extension can be easily accomplished in the manufacturing process of the gas turbine blade by making the core base of the casting core thicker.
  • the inlet openings of the supply channels are at the level of the transition flank between the lowermost longitudinal rib and the longitudinal rib above it. In this way it is ensured that the area of the distribution space is only encompassed by the lowest longitudinal rib. There is a transition flank between each of the two longitudinal ribs. supply ensures that the blade root of the gas turbine blade is held securely in the undercut of the disk.
  • the proposed arrangement of the inlet openings of the supply channels ensures that subsequent processing of the blade root after the casting process can take place in a defined area without the blade being damaged, the area of the distributor space being located within the lowermost longitudinal rib. The extent of the longitudinal rib can thus be adjusted almost as desired.
  • the object directed to a casting device for producing a gas turbine blade with a distribution space is achieved by a device for casting a gas turbine blade with a casting core which has core ribs which form supply channels, the casting core having a core base which forms the distribution space and with which the core ribs are formed in one piece and there is a smooth transition from the core base to the core ribs.
  • the casting device has an inner casting core in addition to an outer jacket.
  • the casting core is used in the casting of the gas turbine blade in order to keep a predetermined, inner area of the gas turbine blade free of casting material. This reserved area includes the internal cooling system, the supply ducts and the distribution room.
  • the supply channels are kept free by elongated approaches of the casting core, the so-called core ribs.
  • the distribution space is formed by an area that is widened compared to the core ribs and has a certain thickness and height, the so-called core foot.
  • the core base is formed in one piece with the core ribs. The one-piece design of the two parts of the casting core enables a rounded design of the transition between the supply channels and the distribution space.
  • the rounded design of the transition between the supply channels and the distribution room always takes place in the same way as specified by the shape of the casting core. This enables exact compliance with predetermined dimensions. It is possible to ensure desired dimensions of the internal cooling system of the gas turbine blade in such a way that they can be set reproducibly for a whole series of gas turbine blades. This provides a basis for an inexpensive and reliable manufacture of internally cooled gas turbine blades.
  • the casting core is formed in one piece, it is very stable against the deformation forces which occur due to the solidification of the melt.
  • the transition from the core base to the core ribs is designed in such a way that it takes place smoothly, in that the cross section from the core ribs to the core base preferably increases continuously. After the casting process, due to the smooth transition of the core ribs into the core base, no reworking of the inlet openings of the supply channels is necessary to ensure a low flow resistance.
  • the core ribs merge with the increasing cross section into the core foot, which has a thickness that is greater than the thickness of the core ribs. In this way, a further reduction in the flow resistance of the coolant flow is possible.
  • the transition from the distribution space to the supply channels is provided in that the rounded core ribs end in a curved surface that ends in the core base.
  • This area forms a constriction, which is introduced to the actual entrances of the supply channels and which supports a continuous and low-swirl diversion of the coolant flow into the supply channels.
  • tiger casting core easier to manufacture and also better calculated in terms of its flow properties.
  • the object directed to a method for producing a gas turbine show using a described device for casting is achieved in that the distributor space and the supply channels are cast by using the one-piece casting core.
  • the casting process is more accurate and at the same time less time-consuming, since the individual parts of the casting core can be set up together. With this method, the distribution room no longer has to be mechanically incorporated. This complex, essentially to be carried out by hand
  • the distribution space can be mechanically reworked. This is simplified compared to the usual mechanical processing in that most of the material to be worked out is already missing due to the casting process. It is therefore only necessary to carry out minor corrections which require less production effort.
  • Fig.l shows a detail of the disc and the blade root in a perspective side view
  • Fig.2 shows a perspective view of the blade root and the distributor space from below
  • Fig.3 shows a view of the distributor space, the inlet openings and the supply channels from below
  • FIG. 4b a cross section through the distribution space of FIG. 3
  • FIG. 5 a perspective side view of the lower part of the casting core
  • FIG. 6 a cross section through a core rib and the core foot of Fig. 5.
  • FIG. 1 shows schematically and not to scale a basic structure of the base area of a gas turbine blade 1 inserted into a disk 3 of a gas turbine.
  • the disk 3 can be rotated about the axis of rotation 14 of the gas turbine.
  • the gas turbine blade 1 is held with its blade root 2, which has two longitudinal ribs 13, 13 ', in a disk transverse groove 60 of the disk 3.
  • the blade root 2 is supported on undercuts 12 of the disk 3 with its longitudinal ribs 13, 13 'against the centrifugal forces acting parallel to the longitudinal direction 15 of the gas turbine blade 15 when the disk 3 rotates about the axis of rotation 14.
  • the disk 3 has a supply duct 6 and the blade root 2 has a plurality of supply ducts 4, which are in flow connection with one another through a distributor space 5.
  • coolant 80 can be guided from the disk 3 into the internal cooling system of the gas turbine blade 1.
  • the coolant 80 is preferably cooling air.
  • the distribution space 5 has rounded or flattened inlet openings 7 of the supply channels 4.
  • the coolant 80 passed through is divider room 5 and directed into the supply channels 4 to the internal cooling system with minimal flow losses.
  • the distribution space 5 is open on its base side 70 to the supply duct 6. There is almost no flow loss on this base side 70.
  • the distribution space 5 is rounded in the manner of an ellipsoid. In its cross-sectional shape parallel to its base side 70, it has a shape of a shrinking ellipse. In the perpendicular cross-sectional area 9, shown in FIG. 4b, it has the cross-sectional shape of a half ellipse with a continuously changing cross-section. This semi-elliptical shape is interrupted by the rounded inlet openings 7 of the supply channels 4.
  • the transitions between the inlet openings 7 of the supply channels 4 and the half ellipse of the distributor space 5 are rounded, so that they do not form any appreciable flow resistance.
  • the inlet openings 7 can both lie directly next to one another, that is to say abut one another or be adjacent to one another.
  • the areas between the inlet openings 7 of the supply channels 4 are rounded in terms of flow, ie there are no edges.
  • This also applies to the cross sections 8 of the supply duct 6 in the disk 3 of the gas turbine.
  • the cross section 8 of the supply duct 6 is preferably matched to the local changes in the cross sections 9 of the distributor space 5 perpendicular to its base plane 70, as well as to the cross sections 10 of the inlet openings 7 arranged downstream in terms of flow. In this way, one for cooling the most distant regions of the gas turbine blade 1 necessary coolant flow 80 can be set safely.
  • the supply channels 4 adjoin the distribution space 5 with different cross-sections 10 and transition cross-sections 11 which are adapted to them and which merge into the distribution space 5. In this way, a differently strong coolant flow 80, which depends in each case on the cross section 10 of the supply duct 4, can be changed into a predetermined one Area of the internal cooling system. This enables an individual adaptation of the cooling.
  • the gas turbine blade 1, which is shown in FIG. 1, is produced in a single casting process, the distributor space 5 being formed by a casting core 18 with the core ribs 19, which keep the supply channels 4 free of casting material.
  • the distributor space 5 has a height 90 which approximately corresponds to the height 16 of the distance of the lower part of the lower longitudinal rib 13 to the transition into the subsequent longitudinal rib 13 'of the blade root 2. Accordingly, in order to obtain a large distributor space 5 with as little flow resistance as possible, it is advantageous if the lower longitudinal rib 13 is extended along a main axis 15 of the gas turbine blade 1. With such an enlarged distributor space 5, only a small proportion of turbulence in the coolant flow 80 can be determined within the distributor space 5 and at the transition into the inlet openings 7.
  • FIG. 2 shows a top view of the base side 70 of the blade root 2 in a perspective view.
  • Rounded or flattened inlet openings 7 of the supply ducts 4 depart from the distributor space 5.
  • the longitudinal ribs 13, 13 ' are formed with undercuts 12.
  • the supply channels 4 have an oval or elliptical shape, which is particularly aerodynamic.
  • the inlet openings 7 are also correspondingly elliptical, the cross section of the elliptical inlet openings 7 continuously decreasing from the distributor space 5 to the supply channels 4.
  • the coolant flow 80 runs from the supply duct 6 with a diameter 8 into the distributor space 5 and through the inlet openings 7 into the supply ducts 4 rounded inlet openings 7 and the rounded distributor space 5 as well as the rounded opening 110 of the supply duct 6, the coolant flow 80 is passed unhindered into the internal cooling system of the gas turbine blade 1.
  • the distribution space 5 has a maximum height 90.
  • FIG. 4b shows a cross section through the view of FIG.
  • the blade root 2 of the gas turbine blade is shown, which is cut through the distributor space 5.
  • the distributor space has an elliptical cross-section with the cross-sectional area 9.
  • the casting core 18 represents the essential component of the device for casting a gas turbine blade 1.
  • the casting core 18 has core ribs 19 and one
  • the core ribs 19 with the thickness 21 form the supply channels 4 of the gas turbine blade 1 during casting.
  • the core foot 20 and the core ribs 19 are formed in one piece and the core rib 19 merges into the core foot 20 with an enlarging cross section 21. This transition takes place in a continuously increasing cross section 21, so that no sudden changes in the thickness occur.
  • the core ribs 19 are rounded and preferably end in a curved surface 24 which ends in the core base 20. In this way, the distributor space 5 is shaped particularly aerodynamically after the casting. 6 shows in a longitudinal section through the core base 20 and a core rib 19 the continuous transition of the thickness 23 of the core rib 19 into the thickness 22 of the core base 20.
  • a casting core 18 described above is used in the manufacture of the gas turbine blade 1 described above. It enables simple manufacture of both a large distributor space 5 and a continuous transition from the distributor space 5 to the supply ducts 4 of the gas turbine blade, without the gas turbine blade 1 having to be reworked in this area. However it is readily possible to mechanically reprocess a gas turbine blade 1 cast in this way in its distributor space 5, for example in order to subsequently adapt the gas turbine blade 1 to changed requirements or to use the same casting core 18 for different models. A substantial part of the material to be worked out is already kept free by the core base 20. The subsequent mechanical processing is therefore only a correction that can be carried out quickly and inexpensively.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)

Abstract

L'invention concerne une aube de turbine à gaz moulée (1) parcourue par un réfrigérant, comprenant un pied (2) présentant plusieurs canaux d'alimentation (4) et une chambre distributrice (5). Un réfrigérant peut être amené aux canaux d'alimentation (4) au moyen d'un canal d'amenée (6) du disque (3) qui communique avec lesdits canaux d'alimentation (4), via la chambre distributrice (5). En vue d'obtenir des résultats optimums quant à l'écoulement et quant à la fabrication, l'invention est caractérisée en ce qu'il est prévu une chambre distributrice moulée (5) présentant des orifices d'admission arrondis ou aplatis (7) pour les canaux d'alimentation (4), et en ce que ladite chambre distributrice (5) est produite au moyen d'un noyau de coulée en une seule pièce.
EP00920564A 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine Expired - Lifetime EP1165939B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP00920564A EP1165939B1 (fr) 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP99106454 1999-03-29
EP99106454A EP1041246A1 (fr) 1999-03-29 1999-03-29 Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz
PCT/EP2000/002606 WO2000058606A1 (fr) 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine
EP00920564A EP1165939B1 (fr) 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine

Publications (2)

Publication Number Publication Date
EP1165939A1 true EP1165939A1 (fr) 2002-01-02
EP1165939B1 EP1165939B1 (fr) 2003-08-13

Family

ID=8237884

Family Applications (2)

Application Number Title Priority Date Filing Date
EP99106454A Withdrawn EP1041246A1 (fr) 1999-03-29 1999-03-29 Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz
EP00920564A Expired - Lifetime EP1165939B1 (fr) 1999-03-29 2000-03-23 Aube de turbine a gaz moulee parcourue par un refrigerant, et dispositif et procede de production d'une chambre distributrice pour l'aube de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP99106454A Withdrawn EP1041246A1 (fr) 1999-03-29 1999-03-29 Aube de turbine à gaz coulée avec refroidissement interne, procédé et dispositif de fabrication d'un collecteur dans l'aube de turbine à gaz

Country Status (5)

Country Link
US (1) US6565318B1 (fr)
EP (2) EP1041246A1 (fr)
JP (1) JP4567206B2 (fr)
DE (1) DE50003266D1 (fr)
WO (1) WO2000058606A1 (fr)

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Also Published As

Publication number Publication date
WO2000058606A1 (fr) 2000-10-05
EP1041246A1 (fr) 2000-10-04
EP1165939B1 (fr) 2003-08-13
JP4567206B2 (ja) 2010-10-20
DE50003266D1 (de) 2003-09-18
JP2002540347A (ja) 2002-11-26
US6565318B1 (en) 2003-05-20

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