US3561884A - Stator blade construction for turbomachines - Google Patents

Stator blade construction for turbomachines Download PDF

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Publication number
US3561884A
US3561884A US766846A US3561884DA US3561884A US 3561884 A US3561884 A US 3561884A US 766846 A US766846 A US 766846A US 3561884D A US3561884D A US 3561884DA US 3561884 A US3561884 A US 3561884A
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US
United States
Prior art keywords
groove
housing
blade
stator
blades
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.)
Expired - Lifetime
Application number
US766846A
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English (en)
Inventor
Ferdinand Zerlauth
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Sulzer AG
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Sulzer AG
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Filing date
Publication date
Application filed by Sulzer AG filed Critical Sulzer AG
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Publication of US3561884A publication Critical patent/US3561884A/en
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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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the present invention pertains to turbomachines and, more particularly, to the fastening of the stator blades of such machines into the housing thereof.
  • Theterm turbomachine is intended to denote a turbine-type machine whether for development of mechanical energy at a rotating shaft from a uid owing through the machine as in a turbine, or for the delivery of energy from a rotating shaft to the fluid, as in a pump or compressor.
  • the invention provides a blade fastening in which at least some of the grooves in the housing for receipt of the roots or feet of the stator blades or stator blade segments are open. Further, these open grooves include at least one radially acting cylindrical positioning or indexing surface and at least one axially acting plane annular positioning surface.
  • these grooves include, in the vicinity of these annular positioning surfaces, a radially acting holding groove.
  • the feet of the stator blade or stator blade segments possess a complementary radially acting cylindrical positioning surface and a complementary axially acting plane positioning surface. They also include a radially acting holding member which fits into the holding groove of the stator blade housing or blade carrier, and an axially acting lock for the blades or blade segments.
  • radially acting positioning surface or radial positioning surface is used herein to denote a surface which establishes the radial position of the member on which it is formed, or of another member which is brought to bear against that surface, and the term axially acting positioning surface" or axial positioning surface is similarly defined in respect of axial positions.
  • a fastening of the stator blades in accordance with the invention has the advantage that the fabrication of the housing is much simplified. It is sufficient, to make up the step-shaped inner surface of the housing, to apply axial and radial motions to turning and boring tools. Drilling operations are reduced to a minimum. The result is a substantial reduction in manufacturing time and in the jigs and fixtures required, and also an improvement in the accuracy of the dimensions achieved.
  • the blades or blade segments can, moreover, be set in more easily and more accurately.
  • an axially acting closed groove into which a locking device is to be inserted.
  • the locking device will extend over the heads of the blades so that it may additionallyand simultaneously operate to guide the fiow of the working substance through the conduits of the rotor blades,
  • BEST AVAILABLE copy ice and eventually also serve to protect the rotor blade support against excessive temperatures.
  • the cylindrical positioning surface of the open stator blade groove can simultaneously serve as the exterior positioning surface of the axial abutment groove and as an inner positioning surface for the bearing edge of the locking groove. In this way, three positioning surfaces can be produced in a single machining operation.
  • the stator housing 25 includes an open groove 1 for the roots or feet 2 of the stator blades or stator blade segments 3. This groove is formed by machining.
  • the radial positioning surface 4 of the groove 1 is cylindrical in shape and is produced by a purely axial motion of a cutting or boring tool.
  • the surface 4 of each stage may be in two parts, the two parts being separated by a deepened portion of the groove 1.
  • the axial positioning surface 5 in contract is the result of radial motion of the cutting tool only. The same is true of the correspondingly numbered elements of structure associated with the right-hand stage 32.
  • the holding groove 6 can be produced in one machining operation together with the cylindrical positioning surfaces 4.
  • the diameter of the outer positioning surface of the groove 6 (identified at 11 in the right-hand stage 32) then has the same value as the diameter of the positioning surface 4 of the open groove 1.
  • a locking groove 12 is cut into the cylindrical positioning surface 4, at or near the axial end of that surface 4 which is adjacent the large-diameter end of the housing.
  • the groove 12 serves to receive stator blade locking segments l0, which are seen to be located axially of the machine opposite the ring of rotor blades on the large-end side of the stator blades held in position by those locking segments.
  • the Shape of the groove 12 is chosen so that it can be cut primarily by radial motion of the cutting tool. In this process, accurate dimensioning need be held only for the positioning surface 14, which must be at a specified distance from the axial positioning surface 5 to the left thereof in the figure.
  • the abutment edge or lip 17 whose outside diameter, defining the positioning surface 15, must be carefully worked to a specified dimension.
  • the positioning surface 16 on the inside diameter of the abutment edge 17 has the same diameter as the positioning surface 4, in each stagev the tool need only be moved axially toward the small diameter and of the housing once it has reached the radially outer limit desired for groove 12.
  • the method described for machining the interior surface of the stator has the advantage that the positioning surfaces necessary to locate the stator blades in the stator blade carrier or housing can be produced with a minimum of profile cutting tools. Instead, it sufces to employ normal cutting or grinding tools, moved axially or radially, in order to form the cylindrical and plane positioning surfaces.
  • the feet 2 of the stator blades or blade segments 3 can be set into place by simple axial motion into the ready-prepared grooves 1.
  • the locking segments 10, on the other hand, are inserted radially circumferentially into their locking grooves 12.
  • the radially operative holding edge or fillet 9 on the blade feet is fitted at its positioning surface 7 on the positioning surface 4 of the housing. As is evident from the drawing, part of the positioning surfaces may be relieved by radial motion of the cutting tool. In this way, there is achieved the advantage of ready installation of the blades without requiring adherence to close tolerances.
  • the holding ridge 9 is further located by engagement of its surface 22 on the support surface 23 of the groove 6.
  • the blade root As to its axial location, the blade root is supported at one axial end thereof by engagement of its surface 8 on the annular housing surface 5. At the other axial end, the surface 19 of the locking member 10 bears against the positioning surface 18 of the blade foot 2. In this way, the stator blades are tightly fastened into the housing. The result is that their weight, the stresses exerted thereon by the working substance passing through the machine ⁇ vibrational stresses. and also those due to distortion of the blades and of the locking members on temperature changes, are borne by positive interengagement of elements requiring rupture before failure, and not merely by forces of friction.
  • the blade ring and more particularly the feet 2 of the blade segments, can be provided with a cylindrical locating surface 20 on the axial side thereof away from the ridge 9, to bear against a complementary cylindrical locating surface 21 of the locking segments 10.
  • the blade feet are held against radial motion only at one axial end thereof, as indicated at 9 for the stage 32 at the right in the drawing, the other axial end of the blade feet being positioned only with axially holding surfaces 18 and 19 on the blade feet and locking members. That is, in stage 32, the members 2 and 10 do not include the radially acting surfaces 20 and 21 which appear on those members in stage 31.
  • the locking segments 10 are positioned against radial motions at the surfaces and 16 of the abutment edge 17. In respect of axial stresses, the segments 10 bear in each of stages 31 and 32 at the surface 13 thereof on the surface 14 of the groove 12. The result is that the locking segments are in condition to support at their surfaces 19 axial stresses delivered to them at the surface 18 of the blade feet. They can also support at their surfaces 21, when provided, a portion of the radial stresses which are exerted from the blade root via the surface 20.
  • the blades may be provided with individual feet.
  • the feet 2 illustrated may, however, extend over a substantial sector uniting a plurality of blades into a single segment.
  • the invention s of particular advantage when the blades are so collected into segments because the feet thereof are readily inserted and held actually into the grooves therefor.
  • the invention thus provides a stator blade assembly for turbomachines comprising an annular housing having CII BEST AVAILABLE COPY formed on the inner wall thereof at least one groove 1 for the stator blades of each stage of the machine.
  • This groove includes as bounding surfaces thereof a radially extending annular surface of revolution 5. an inwardly facing axially extending surface of revolution 4, and an outwardly facing axially extending surface of revolution 23.
  • This outwardly facing axially extending surface 23 defines a radially operative, axially facing groove 6.
  • the assembly further includes a plurality of stator blade feet 2 having formed thereon surfaces 8 and 7 respectively complementary to and engageable against said radially extending and inwardly facing axially extending surfaces 5 and 4.
  • the feet include an axially extending annular ridge 9 adapted to t in the axially facing groove 6.
  • the assembly further includes locking means comprising a plurality of locking members 10 adapted to hold those feet against the radially extending surface 5 of the housing
  • the housing of the assembly has formed therein for each stage a second groove l2 bounded in part by a radially extending surface 14 facing the radially extending surface 5, and the locking means and blade feet are engaged together between the facing radially extending surfaces 5 and 14.
  • the axially facing groove 6 is bounded at the radially outer limit thereof by the inwardly facing axially extending surface 4.
  • the second groove 12 includes an axially extending undercut portion defining an axially extending housing ridge 17 bounded on the radially inner side by the inwardly facing axially extending surface 4 of its stage.
  • the locking means comprise a plurality of sectors 10 insertable into the second groove l2. The sectors are positioned radially by at least one side of the axially extending housing ridge 17.
  • the locking means and blade feet engage each other at radially extending surfaces 18 and 19, and may further engage each other at axially extending surfaces 20 and 21.
  • each of one or more stages of the stator blade assembly of the invention (or in the single stage thereof, in single-stage turbomachines embodying the invention), provision may be made for the introduction of a heating or cooling medium.
  • a heating or cooling medium such as a cooling gas.
  • introduced through the bores 35 will then ow into the annular space 33 and thence through the throat 36 connecting it to the interior of the housing and over the feet of the adjacent stator blades 32.
  • Introduction of a cooling gas in this way makes possible a substantial reduction in temperature at the blade feet, so that they need not be made of the same high-temperature resistant material as the blades themselves.
  • a stator blade assembly for multi-stage axial ow turbomachines comprising an annular housing having a high-pressure end and a low-pressure end, said housing having:
  • said groove being bounded at least in part by an BEST AVAILABLE COPY inside cylindrical surface, by a first plane annular surface facing the low-pressure end of the housing, said first plane annular surface being of smaller diameter than said cylindrical surface, and by a rc taining groove cut below said annular surface; said housing further having formed on the inner wall thereof for each stage:
  • said assembly further comprising for each stage:

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US766846A 1968-03-22 1968-10-11 Stator blade construction for turbomachines Expired - Lifetime US3561884A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH433068A CH488928A (de) 1968-03-22 1968-03-22 Leitschaufelbefestigung in Turbomaschinen

Publications (1)

Publication Number Publication Date
US3561884A true US3561884A (en) 1971-02-09

Family

ID=4274061

Family Applications (1)

Application Number Title Priority Date Filing Date
US766846A Expired - Lifetime US3561884A (en) 1968-03-22 1968-10-11 Stator blade construction for turbomachines

Country Status (6)

Country Link
US (1) US3561884A (de)
BE (1) BE730121A (de)
CH (1) CH488928A (de)
DE (1) DE1751056B2 (de)
FR (1) FR2004480A1 (de)
NL (1) NL6805402A (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4379677A (en) * 1979-10-09 1983-04-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for adjusting the clearance between moving turbine blades and the turbine ring
US4907944A (en) * 1984-10-01 1990-03-13 General Electric Company Turbomachinery blade mounting arrangement
US5004402A (en) * 1989-09-05 1991-04-02 United Technologies Corporation Axial compressor stator construction
US6217282B1 (en) * 1997-08-23 2001-04-17 Daimlerchrysler Ag Vane elements adapted for assembly to form a vane ring of a gas turbine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4379677A (en) * 1979-10-09 1983-04-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for adjusting the clearance between moving turbine blades and the turbine ring
US4907944A (en) * 1984-10-01 1990-03-13 General Electric Company Turbomachinery blade mounting arrangement
US5004402A (en) * 1989-09-05 1991-04-02 United Technologies Corporation Axial compressor stator construction
US6217282B1 (en) * 1997-08-23 2001-04-17 Daimlerchrysler Ag Vane elements adapted for assembly to form a vane ring of a gas turbine

Also Published As

Publication number Publication date
DE1751056A1 (de) 1970-08-13
NL6805402A (de) 1969-09-24
BE730121A (de) 1969-09-19
DE1751056B2 (de) 1971-07-22
CH488928A (de) 1970-04-15
FR2004480A1 (de) 1969-11-28

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