US3326523A - Stator vane assembly having composite sectors - Google Patents

Stator vane assembly having composite sectors Download PDF

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Publication number
US3326523A
US3326523A US511962A US51196265A US3326523A US 3326523 A US3326523 A US 3326523A US 511962 A US511962 A US 511962A US 51196265 A US51196265 A US 51196265A US 3326523 A US3326523 A US 3326523A
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United States
Prior art keywords
stator
base
composite
stator vane
vanes
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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
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US511962A
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English (en)
Inventor
Bobo Melvin
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General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US511962A priority Critical patent/US3326523A/en
Priority to GB33870/66A priority patent/GB1148590A/en
Priority to JP5252566A priority patent/JPS4617327B1/ja
Priority to DE19661551180 priority patent/DE1551180A1/de
Priority to FR75257A priority patent/FR1523147A/fr
Priority to BE686462D priority patent/BE686462A/xx
Application granted granted Critical
Publication of US3326523A publication Critical patent/US3326523A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D9/02—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
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • each stator vane has its own base and each base is individually supported in the compressor. More particularly, it is typical in this type of construction to provide each base with support lugs which are received in a suitable support means such as a T-shaped slot in the compressor casing, the bases of adjacent vanes abutting in the support slot.
  • a suitable support means such as a T-shaped slot in the compressor casing, the bases of adjacent vanes abutting in the support slot.
  • stator vanes are often subject to vibration during high speed turbomachine operation. While the causes of this vibration, as well as its nature, are not always fully understood even by those highly skilled in the art, it is clear that such vibration is caused primarily by non-uniform aerodynamic forces acting on the vanes during operation. Even a theoretically smooth flow, such as that expected in an axial flow compressor, may actually be quite irregular and may cause forced and synchronous vibration in the stator vanes. If sufiiciently severe, such vibration can create extremely high stresses in the vanes and can ultimately cause fatigue failure. To prevent such failure, it is desirable to provide suitable means for damping the destructive vibration.
  • the individual base type of stator construction has extremely effective internal damping characteristics due to movement of the individual bases in the support structure and relative to each other. As a result of this movement, substantial amounts of energy are dissipated through the frictional rubbing which occurs both between the individual bases and the support structure and between adjacent bases at their abutting surfaces. It has been found in practice, however, that this relative movement can result in uneven and sometimes excessive wear on the support lugs of the individual bases.
  • the sector type of stator vane construction generally exhibits very little wear on the common base member due both to relatively little motion between the common base member and its support structure and to relatively uniform loading on the support portions of the base member. As would be expected, however, this low wear is usually accompanied by very little damping in the system.
  • the sector type of construction is quite often expensive and difficult to manufacture, particularly of certain materials such as titanium.
  • failure of a small portion of the sector such as failure of a single vane, necessitates the removal and replacement of the entire stator vane sector.
  • Another object of this invention is to provide a stator vane assembly having a high degree of wear resistance in combination with superior vibration damping characteristics.
  • a further object is to provide for turbom-achines an improved stator vane assembly which is not only effective in resisting wear, but also relatively inexpensive and easy to manufacture and maintain.
  • a stator vane sector is comprised of a plurality of stator vanes having discrete base portions held in abutting relationship by means frictionally engaging the base portions and providing vibration damping.
  • the abutting base portions form a composite arcuate base which is supported in a turbomachine as a discrete member.
  • the means frictionally engaging the base portions is a stressed member resiliently mounted in a continuous groove formed in the composite base.
  • the individual base portions have lugs thereon which cooperate to form composite flanges which are engaged by suitable support means forming an integral portion of the turbomachine casing.
  • the continuous groove in the composite base is dovetail shaped and arcuate in configuration, and the stressed member received therein has a compound arcuate configuration both along its length and in cross section.
  • FIG. 1 is a sectional view of a gas turbine engine having compressor stator vane assemblies constructed in accordance with this invention
  • FIG. 2 is a view -of a compressor stator vane assembly taken along viewing lines 22 of FIG. 1;
  • FIG. 3 is a pictorial view of one of the composite sectors comprising the stator vane assembly of FIG. 2;
  • FIG. 4 is a view taken along viewing lines 4-4 of FIG. 2 showing a stator vane and its discrete base portion;
  • FIG. 5 is a view of a stressed member in its unassembled, or unstressed, condition
  • FIG. 6 is an enlarged view of the base portion of the stator vane of FIG. 4 illustrating the frictional engagement between the base portion and the stressed memher;
  • FIG. 7 is a view similar to FIG. 6 showing a slightly modified arrangement.
  • a gas turbine engine 10 of the turbojet type is illustrated, the engine 10 having a generally cylindrical casing 11 enclosing, in axial flow relationship, an annular inlet duct 12, a compressor 13, a combustor 14, a gas generator turbine 15, and an annular exhaust nozzle or duct 16.
  • the gas turbine engine 10 has a stator portion comprising the casing 11 and the other stationary structure including radial support struts 17 spanning the inlet duct 12 to provide rotor support means 18 at the front of the engine, a plurality of rows of radial compressor stator vanes 21, 22, 23, etc., the structure of the combustor 14, nozzle guide vanes 24 and 25 for the gas generator turbine 15, and radial support struts 26 spanning the exhaust nozzle 16 to provide rotor support means 27 at the aft end of the engine 10.
  • the stator and rotor portions of the engine cooperate to form an annular motive fluid passageway 40 extending the entire length of the engine, the passageway 46 including at opposite ends of the engine 10 the inlet and exhaust ducts 12 and 16, respectively.
  • the motive fluid which is initially air and then combustion products, is subject to several processes is it flows through the passageway 40. It is first compressed to high pressure in the compressor 13 and then burned at substantially constant pressure to produce high temperature exhaust gases which drive the gas generator turbine 15 where both the temperature and the pressure of the gases are reduced. Finally the low pressure, low temperature exhaust products are discharged at atmosphere through the exhaust duct 16.
  • a turbomachine such as the gas turbine engine 10 is often thought of as a continuous flow machine through which the motive fluid flows in a completely uniform manner.
  • the flow is generally far from uniform and smooth, particularly because of discontinuities introduced into the flow by the vanes, blades, buckets, and support struts extending across the annular passageway 40.
  • the various elements are subject to fluctuating aerodynamic forces which cause forced vibration.
  • the compressor stator vanes 21, 22, 23, etc. are particularly susceptible to vibration caused in this manner. These aerodynamic forces are, of course, not the only cause of destructive vibration in a turbomachine.
  • FIGS. 2 and 3 the annular row of non-variable or fixed angle vanes 21 is viewed in FIG. 2 from its upstream side, one of the composite sectors 45 comprising the stator vane assembly of FIG. 2 being illustrated pictorially by FIG. 3. As shown by FIG. 2,
  • each sector 45 there are twelve sectors 45 of 30 each, but it will occur to those skilled in the art that other numbers of sectors can be used, such as six 60 sectors. In general, any number of sectors may be used, down to a minimum number of two. In addition, each sector should contain a suflicient number of vanes to provide a suitable degree of wear resistance in accordance with the present invention; this requirement will become clear as this description proceeds.
  • stator vanes 21 includes a plurality of composite sectors 45. These sectors 45, are, however, substantially different than the sectors of certain prior art assemblies in that each stator vane 21 has a discrete base portion 46 formed integrally therewith, the circumferentially spaced vanes 21 projecting radially inward from the base portions 46 across the annular passageway.
  • the abutting base portions 46 of each sector 45 form a composite base 47 which is, as best shown by FIG. 2, arcuate in configuration with respect to the longitudinal axis of the engine 10. Stated differently, the longitudinal axis of the engine 10, as viewed in FIG. 2, can be said to be the center of curvature of the composite base 47.
  • each base portion 46 has a first lug 50 projecting axially upstream relative to the engine axis C and a second lug 51 projecting axially downstream, the first lugs 50 of each sector 45 being aligned to form a first composite, arcuate flange 50' and the second lugs 51 of each sector 45 being aligned to form a second composite, arcuate flange 51'.
  • These composite flanges 50 and 51' are engaged by support means 52 which is an integral portion of the engine casing 11. More particularly, the support means 52 includes a first flange 53 projecting inwardly from the casing 11, the flange 53 defining an annular channel 54 opening in the downstream direction.
  • the support means 52 further includes a second flange 55 spaced axially downstream of the first flange 53, the second flange 55 also projecting inwardly from the casing 11 and defining an annular channel 56 opening in the upstream direction.
  • each base ortion 46 has a recess 65 formed in its radially outer surface 58, the recess 65 being dovetail shaped in cross section and being circumferentially disposed with respect to the engine axis C.
  • the recesses 65 in the abutting base portions 46 are aligned to form a continuous groove 66 extending the entire circumferential length of the composite base 47.
  • the groove 66 is, as the composite base 47, arcuate with respect to the engine axis, or center of curvature C of the composite base 47.
  • the means frictionally engaging the base portions 46 is, as shown by FIG. 5, a spring member 70.
  • the spring member 70 is mounted in the arcuate groove 66 to provide the required frictional engagement. Since the member 70 extends the. entire length of the groove 66, its arcuate length L is substantially equal to the arcuate length of the groove 66. In addition, the curvature of the spring member 70 in its unstressed state is slightly greater than that of the groove 66; the reason for this will soon be apparent. In addition, the spring member 70 has in its unstressed condition an arcuate shape in cross section throughout its length. This arcuate configuration is superimposed on the arcuate configuration of the member 70 along its length. Stated differently, it can be said that the spring member 70 has a compound arcuate configuration.
  • the spring member 70 which has a width W greater than the width W of the widest part of the groove 66, assumes in cross section an arcuate shape, as shown by FIG. 4, having a curvature greater than that of its unstressed state.
  • the spring member 7 0 straightens out along its length until the curvature along its length is the same as that of the groove 66.
  • the spring member 70 also has .a compound arcuate configuration in its assembled state
  • the member 70 is a stressed member which, because of its resilience, wants to return to its unstressed configuration.
  • the member 70 exerts, as best shown by the embodiments of FIGS. 6 and 7, substantial forces F on the wall surfaces S of the groove 66 to maintain the bases 46 in abutting relationship.
  • substantial forces F can be dissipated through frictional rubbing between the stressed, spring member 70 and the base portions 46.
  • the member 70 permits a limited amount of relative movement and rubbing between the lugs 50 and 51 and the channels 54 and 56 and between the abutting surfaces of abutting base portions 46. In this manner, significant levels of vibration damping can be attained.
  • the stressed member 70 imparts enough rigidity to the composite base 47 to provide substantially uniform wear along the support flanges 50 and 51.
  • the stressed member 713 permits relative motion within a limited range, but, by transmitting moment and shear forces between adjacent base portions 46, does not permit the large relative motions normally associated with excessive wear.
  • the arrangement of this invention permits the turbomachine desinger to vary the amounts of vibration damping and wear resistance within substantial ranges.
  • a thin spring member 76 as illustrated by FIG. 6, a rather flexible vibration damping arrangement can be provided.
  • a stiffer spring member 70 can be used as illustrated by FIG. 7, the spring member 70 of FIG. 7 having much greater thickness than the spring member of FIG. 6.
  • This type of construction gives a more rigid vane sector 45 generally less subject to wear along its support flanges 50 and 51. Going even further in increasing rigidity, the member 70 may engage the inner surface 59 of the casing 11 as shown to bias the composite flanges 50' and 51' inwardly against the inner surfaces of the channels 54 and 56 respectively.
  • the means for frictionally engaging the base portion 46 is a spring member 70 received in a dovetail shaped groove 66. It will readily occur to those skilled in the art that other stressed elements can be used to perform this function. Similarly, it will be obvious that the invention may be used relative to nonvariable turbine nozzle vanes and rotor blades and buckets in addition to the illustrated compressor stator vanes.
  • the improved non-Van'able vane assembly of this invention provides a composite sector arrangement having superior vibration damping in combination with a high degree of wear resistance.
  • the arrangement or this invention since each vane and its base portion are manufactured separately, the arrangement or this invention has the manufacturing and maintenance advantages of the individual base type of stator construction while still having the ease of handling characteristics of the sector type of stator construction.
  • a stator assembly for use in a turbomachine having an axial flow passageway extending between axially spaced upstream and downstream ends thereof, said stator assembly comprising:
  • said row comprising at least two stator vane sectors
  • each of said stator vane sectors comprising: a plurality of vanes each having a discrete base portion formed integrally therewith at radially outer end thereof, said base portions disposed in abutting relationship to form a composite base having an arcuate configuration relative to the axis of said turbornachine;
  • each of said base portions has a recess therein, said recesses being aligned and forming a continuous arcuate groove in said composite base, and in which said means frictionally engaging said base portions comprises a stressed member resiliently mounted in said arcuate groove.
  • a stator assembly as defined by claim 3 in which said stressed member in its unstressed state has a length substantially equal to the arcuate length of said groove and a width greater than the width of said groove, assembly of said stressed member in said groove causing said stressed member to assume a compound arcuate configuration both along its length with respect to the axis of said turbomachine and in cross section, the arcuate configuration along its length being the same as the arcuate configuration of said groove.
  • each of said base portions has a first lug projecting axially upstream and a second lug projecting axially downstream, the first lugs of each stator vane sector being aligned to form a first composite flange and the second lugs to each stator vane sector being aligned to form a second composite flange, said support means engaging said first and second composite flanges to support said row of stator vanes in said axial flow turbomachine.
  • a stator vane assembly as defined by claim 5 in which said support means includes first and second annular, axially spaced channels, said first annular channel opening in the downstream direction and receiving said first composite flanges and said second annular channel opening in the upstream direction and receiving said second composite flanges.
  • a stator vane assembly as defined by claim 6 including a substantially cylindrical casing surrounding said row of vanes, said support means being an integral portion of said casing.
  • a stator vane assembly as defined by claim 7 in which said stressed member engages said casing to bias said first and second composite flanges against the radially inward surfaces of said first and second annular channels respectively.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US511962A 1965-12-06 1965-12-06 Stator vane assembly having composite sectors Expired - Lifetime US3326523A (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
US511962A US3326523A (en) 1965-12-06 1965-12-06 Stator vane assembly having composite sectors
GB33870/66A GB1148590A (en) 1965-12-06 1966-07-28 Improvements in stator vane assembly having composite sectors
JP5252566A JPS4617327B1 (zh) 1965-12-06 1966-08-10
DE19661551180 DE1551180A1 (de) 1965-12-06 1966-09-05 Leitschaufelkranz fuer Turbomaschinen,insbesondere Gasturbinen-Triebwerke
FR75257A FR1523147A (fr) 1965-12-06 1966-09-05 Assemblage d'ailettes de stator à secteurs composites
BE686462D BE686462A (zh) 1965-12-06 1966-09-05

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US511962A US3326523A (en) 1965-12-06 1965-12-06 Stator vane assembly having composite sectors

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US3326523A true US3326523A (en) 1967-06-20

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US511962A Expired - Lifetime US3326523A (en) 1965-12-06 1965-12-06 Stator vane assembly having composite sectors

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US (1) US3326523A (zh)
JP (1) JPS4617327B1 (zh)
BE (1) BE686462A (zh)
DE (1) DE1551180A1 (zh)
GB (1) GB1148590A (zh)

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Also Published As

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JPS4617327B1 (zh) 1971-05-14
GB1148590A (en) 1969-04-16
DE1551180A1 (de) 1969-06-19
BE686462A (zh) 1967-03-06

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