WO2019046006A1 - Plates-formes à géométrie avancée pour aubes de turbine - Google Patents

Plates-formes à géométrie avancée pour aubes de turbine Download PDF

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Publication number
WO2019046006A1
WO2019046006A1 PCT/US2018/046612 US2018046612W WO2019046006A1 WO 2019046006 A1 WO2019046006 A1 WO 2019046006A1 US 2018046612 W US2018046612 W US 2018046612W WO 2019046006 A1 WO2019046006 A1 WO 2019046006A1
Authority
WO
WIPO (PCT)
Prior art keywords
platform
angle
blade
airfoil
mate face
Prior art date
Application number
PCT/US2018/046612
Other languages
English (en)
Inventor
Nicholas F. MARTIN Jr.
David J. Wiebe
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
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 Aktiengesellschaft, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Publication of WO2019046006A1 publication Critical patent/WO2019046006A1/fr

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
    • 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
    • F05D2230/60—Assembly 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the present invention relates to gas turbine engines, and more specifically to an advanced geometry platform for a turbine blade.
  • turbine inlet temperature is limited to the material properties and cooling capabilities of the turbine parts. This is especially important for upstream stage turbine vanes and blades since these airfoils are exposed to the hottest gas flow in the system.
  • a combustion system receives air from a compressor and raises it to a high energy level by mixing in fuel and burning the mixture, after which products of the combustor are expanded through the turbine.
  • the blades and vanes of the turbine section are typically shaped in the form of an airfoil and have further elements connected to it such as platforms that provide a boundary for the working fluid path.
  • the blade may also have a root portion that may fix the blade to a turbine disc.
  • a blade assembly arrangement for a turbine comprises: an airfoil having a first end; a root extending radially from the airfoil; a platform positioned radially between the airfoil and the root, the platform comprising a platform lower surface, a platform upper surface opposite to the lower surface, a suction side mate face and a pressure side mate face, and a pair of platform ends connecting the suction side mate face and the pressure side mate face; and an airfoil fillet having a root radius, the root radius identifying the length of the airfoil fillet, wherein the airfoil extends radially from the upper surface of the platform wherein the airfoil fillet joins the first end of the airfoil to the upper surface of the platform, and the root extends from the lower surface of the platform, wherein the suction side mate face mates with a pressure side mate face of a similar adjacent platform along a platform mate face angle that
  • a method for attaching blades to a rotor assembly using the blade assembly arrangement according to the blade assembly arrangement above comprising: assembling a plurality of blades adjacent to each other including a first blade through a second-to-last blade from downstream of a rotor; installing the next- to-last blade from downstream of the rotor adjacent to the second-to-last blade; installing the last blade from upstream of the rotor adjacent to the first blade; and axially locking the next-to-last blade and the last blade to the rotor.
  • FIG 1 is a top radial view of a prior art blade with platform.
  • FIG 2 is a top radial view of a blade and platform of an exemplary embodiment of the present invention overlaid over the prior art platform.
  • FIG 3 is a perspective view of an assembly of a plurality of blades and platforms of an exemplary embodiment of the present invention.
  • FIG 4 is a perspective view of another assembly point of a plurality of blades and platforms of an exemplary embodiment of the present invention.
  • FIG 5 is a perspective view of another assembly point of a plurality of blades and platforms of an exemplary embodiment of the present invention.
  • FIG 6 is a perspective view of another assembly point of a plurality of blades and platforms of an exemplary embodiment of the present invention.
  • FIG 7 is a side view of a blade and platform of an exemplary embodiment of the present invention.
  • FIG 8 is a detailed side view of a contact point of a second-to-last blade and a last blade being assembled in an exemplary embodiment of the present invention.
  • an embodiment of the present invention provides a blade assembly for a turbine that includes an airfoil, a root and a platform.
  • the platform is positioned radially between the airfoil and the root.
  • An airfoil fillet joins the airfoil to an upper surface of the platform.
  • a suction side mate face of the platform mates with a pressure side mate face of a similar adjacent platform along a platform mate face angle that substantially aligns with a camber line angle in relation to an axial direction.
  • a gas turbine engine may comprise a compressor section, a combustor and a turbine section.
  • the compressor section compresses ambient air.
  • the combustor combines the compressed air with a fuel and ignites the mixture creating combustion products comprising hot gases that form a working fluid.
  • the working fluid travels to the turbine section.
  • Within the turbine section are circumferential rows of vanes and blades, the blades being coupled to a rotor. Each pair of rows of vanes and blades forms a stage in the turbine section.
  • the turbine section comprises a fixed turbine casing, which houses the vanes, blades and rotor.
  • a blade of a gas turbine receives high temperature gases from a combustion system in order to produce mechanical work of a shaft rotation.
  • a conventional blade is attached to a conventional platform along an attachment centerline 12.
  • An airfoil 10 is placed on the conventional platform, the conventional platform having a conventional suction side mate face 18 and a conventional pressure side mate face 20.
  • the airfoil 10 has a smooth transition to the conventional platform.
  • the smooth transition portion can be called an airfoil fillet 16.
  • the airfoil fillet 16 extends the airfoil out by a root radius 14.
  • Embodiments of the present invention provide an advanced geometry platform that may allow for a simplified axial retention for blades and improved aerodynamics through the advanced geometry of the platform.
  • a turbine blade has an airfoil 10 with a first end 66.
  • the airfoil 10 includes a pressure side 58 and a suction side 60.
  • the airfoil 10 is joined to a platform 52 by an airfoil fillet 16.
  • the airfoil fillet having a root radius 14 that identifies the length of the airfoil fillet 16.
  • the platform 52 is positioned radially inward from the airfoil 10.
  • the platform 52 includes a platform lower surface 54, a platform upper surface 56 opposite to the lower surface 54, a suction side mate face 22 and a pressure side mate face 24, and a pair of platform ends 64 connecting the suction side mate face 22 and the pressure side mate face 24.
  • FIGS. 2 through 4 An embodiment is shown mainly in FIGS. 2 through 4.
  • the platform 52 suction side mate face 22 and pressure side mate face 24 have been modified based on a notched shifted platform section 28.
  • a section of the platform 52 is shifted so that the airfoil is fully covered by the platform 52.
  • the notched shifted platform section 28 is shifted in a circumferential direction C.
  • a platform mate face angle 26 is formed as the notched shifted platform section 28 shifts.
  • FIG. 2 shows this shift in an individual platform.
  • the notched shifted platform section 28 shifts a portion of the platform 52 in a way that substantially aligns the platform mate face angle 26 with an angle of the camber line 68 of the airfoil 10 in relation to an axial direction A.
  • the magnitude of the offset, or shift, and the platform mate face angle 26 can depend on a number of variables such as, blade stagger angle, number of blades, fillet size, and under-platform damper configuration.
  • the surface of the notched shifted platform section 28 along the circumferential direction C may be straight edges as shown or rounded edges, etc. based on the configuration of the turbine.
  • the shape of the surface of the notched shifted platform section 28 is not limited to the straight edges shown.
  • FIG. 5 shows another embodiment of the blade assembly arrangement.
  • the broach angle 38 of the platforms during installation is typically consistent with the angle of the platform.
  • the platform has a skewed platform angle 40 that is different than the broach angle 38.
  • the skewed platform angle 40 is greater than the broach angle 38.
  • the skewed platform angle 40 once again, takes into consideration the size of the airfoil circumferential length.
  • the skewed platform angle 40 allows for the coverage of the airfoil 10 and airfoil fillet 16 with root radius 14.
  • each blade is assembled from downstream, or aft side 44, of a rotor 70 except for the last blade 32.
  • the first blade 30 through until the second-to-last blade 36 is assembled from the aft side 44.
  • the next-to-last blade 34 follows the second-to-last blade 36 in the installation, as is shown in FIG. 3 and FIG. 4.
  • the next-to-last blade 34 installation direction 46 the same as the blades before.
  • the last blade 32 is installed in the forward side 48 or upstream of the rotor 70. As can be seen in FIG. 4 through FIG. 5, the next-to-last blade 34 and the last blade 32 can be slightly different than the rest of the blades.
  • the facing suction side mate face 22 and pressure side mate face 24 of the next-to-last blade 34 and the last blade 32 are modified and can be similar to the conventional suction side mate face 18 and conventional pressure side mate face 20 as these are the last blades placed into the assembly of the rotor 70.
  • this modification removes the notched shifted platform section 28, and in other embodiments, a platform angle 72 and the broach angle 38 are the same S for the next-to-last blade 34 and the last blade 32.
  • the next-to-last blade 34 and the last blade 32 will be individually axially locked to the rotor 70.
  • the first blade 30 through the second-to-last blade 36 do not have to be axially locked to the rotor 70. Due to the advanced geometry of these blades, the assembly provides stability and allows for simplified axial retention.
  • a buildup addition 42 is made for side mate faces that match up for the next-to-last blade 34 and the adjacent last blade 32 as is seen in FIG. 6.
  • the next-to-last blade 34 and the last blade 32 can be modified with these buildup additions 42 in order to have improved aerodynamics by completing the cut-off fillet sections.
  • the buildup addition 42 modifications can be only for the next-to-last blade 34 and the last blade 32 while the rest of the blades have the advanced geometry.
  • FIG. 7 illustrates how the airfoil 10, the airfoil fillet 16 along with the root radius 14 is presented along the platform 52. As can be seen in FIG. 7, all of these components of the blade are positioned and supported by the platform 52.
  • FIG. 8 shows another view other than FIG. 6 of how the next-to-last blade 34 and the last blade 32 may have an overlap.
  • the buildup addition 42 is shown from a side view in order to disclose how the platforms 52 mate. Since the last blade 32 and the next-to-last blade 34 do not have the interlocking notched shifted platform section 28 or the skewed platform angle 40, the last blade 32 and the next-to-last blade 34 provide for the overlapping of the components. Only the last blade 32 and the next-to-last blade 34 may need to have axial locking, typical of conventional blade/platform offerings, therefore not further discussed here.
  • a plurality of blades can be placed and installed on a wheel.
  • the wheel may include a rotating disc.
  • the disc may include a plurality of elongated channels provided therein and spaced along a disc periphery.
  • Having a notched shifted platform section 28 increases the overall mate face length of the platform 52. Increasing the overall mate face length of the platform 52 allows for more options under the platform for damping. Various damping configurations can be placed underneath the platform 52 with the additional space provided with either the notched shifted platform section 28 and/or with the skewed platform angle 40. Since there are no issues as to a blade airfoil fillet 16 overhanging the platform 52, there are smooth fillet transitions from the airfoil 10 to the platform 52. The smooth fillet transitions provide improved aerodynamics. The platforms 52 with the advanced geometry allow for the platforms 52 to have improved axial retention for the blades when using the interlocked mate faces that are created with the notched shifted platform section 28.
  • FIG. 7 shows a partial selection of the rotor 70.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Un ensemble aube destiné à une turbine comprend un profil aérodynamique (10), une racine (62) et une plate-forme (52). La plateforme (52) est positionnée radialement entre le profil aérodynamique (10) et la racine (62). Un carénage de raccordement de profil aérodynamique (16) relie le profil aérodynamique (10) à une surface supérieure (56) de la plate-forme (52). Une face d'accouplement côté aspiration (22) de la plate-forme (52) s'accouple avec une face d'accouplement côté pression (24) d'une plate-forme adjacente similaire (52) le long d'un angle de face d'accouplement de plate-forme (26) qui s'aligne sensiblement avec une ligne de cambrure (68) par rapport à une direction axiale (A). L'invention porte également sur un procédé de fixation d'aubes à un ensemble rotor.
PCT/US2018/046612 2017-08-28 2018-08-14 Plates-formes à géométrie avancée pour aubes de turbine WO2019046006A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201762550743P 2017-08-28 2017-08-28
US62/550,743 2017-08-28

Publications (1)

Publication Number Publication Date
WO2019046006A1 true WO2019046006A1 (fr) 2019-03-07

Family

ID=63449693

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2018/046612 WO2019046006A1 (fr) 2017-08-28 2018-08-14 Plates-formes à géométrie avancée pour aubes de turbine

Country Status (1)

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WO (1) WO2019046006A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030044282A1 (en) * 2001-08-29 2003-03-06 Gaoqiu Zhu Method and apparatus for turbine blade contoured platform
DE10346384A1 (de) * 2003-09-29 2005-04-28 Rolls Royce Deutschland Turbinenschaufelkranz
US20100166561A1 (en) * 2008-12-30 2010-07-01 General Electric Company Turbine blade root configurations
EP2423438A2 (fr) * 2010-08-31 2012-02-29 General Electric Company Aube de turbine carénée avec plateforme profilée et segment axial en queue d'aronde
US20130004315A1 (en) * 2011-06-29 2013-01-03 Beeck Alexander R Mateface gap configuration for gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030044282A1 (en) * 2001-08-29 2003-03-06 Gaoqiu Zhu Method and apparatus for turbine blade contoured platform
DE10346384A1 (de) * 2003-09-29 2005-04-28 Rolls Royce Deutschland Turbinenschaufelkranz
US20100166561A1 (en) * 2008-12-30 2010-07-01 General Electric Company Turbine blade root configurations
EP2423438A2 (fr) * 2010-08-31 2012-02-29 General Electric Company Aube de turbine carénée avec plateforme profilée et segment axial en queue d'aronde
US20130004315A1 (en) * 2011-06-29 2013-01-03 Beeck Alexander R Mateface gap configuration for gas turbine engine

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