US3588269A - Variable vane cascades - Google Patents

Variable vane cascades Download PDF

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Publication number
US3588269A
US3588269A US836422A US3588269DA US3588269A US 3588269 A US3588269 A US 3588269A US 836422 A US836422 A US 836422A US 3588269D A US3588269D A US 3588269DA US 3588269 A US3588269 A US 3588269A
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United States
Prior art keywords
vanes
ring
throttling
flow
nozzle
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Expired - Lifetime
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US836422A
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English (en)
Inventor
Earle R Wall Jr
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Motors Liquidation Co
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Motors Liquidation Co
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Publication date
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
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    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Definitions

  • variable area turbine nozzle ring has a first set of fixed vanes and a second set of vanes which are movable toward and away from the throat of the nozzles between the other sets of vanes so as to vary the outlet area.
  • the second set of vanes may move at both ends or at only one end.
  • DESCRIPTION My invention is directed to variable area vane cascades such as turbine nozzles or stator rings of compressors and is particularly suited to arrangements wherein it is desirable to vary the area of a turbine nozzle without significantly affecting the direction of discharge of the gas from the nozzle.
  • Typical variable turbine nozzles include structures in which the vanes are rotatable about spanwise extending axes, or in which some part of the vane is so rotatable, or other structures in which shifting of one part of the vane with respect to the other creates a partial blocking, and so forth.
  • the turbine nozzle which constitutes the preferred embodiment of my invention comprises a set of fixed fluid turning vanes which may generally follow known practice defining nozzles for the fluid tov flow from the nozzle to the turbine wheel.
  • the nozzle includes a second set of vanes or throttling members which extend generally parallel to the first set of vanes and are movable generally in the direction of flow through the throats of the intervane passages of the nozzle.
  • Means are provided to shift these secondary vanes or throttling members in unison.
  • the structure is such as to be well. adapted to provision of transpiration cooling on the surfaces of the nozzles which are particularly exposed to and scoured by the hot motive fluid.
  • the principal objects of my invention are to provide an improved cooled variable area turbine nozzle; to provide a variable area turbine nozzle in which throttling of flow is accomplished without significant change in the direction of discharge of the gas; to provide a variable area turbine nozzle that is of simple, reliable, and rugged structure; and, in general, to provide a turbine nozzle particularly suited to the requirements of high temperature turbomachinery in which some variation of flow area is desired.
  • FIG. I is a sectional view through a turbine nozzle taken in a plane containing the axis of rotation of the turbine.
  • FIG. 2 is a partial sectional view taken on the plane in dicated by theline 2-2 in FIG. 1, with parts cutaway.
  • FIG. 3 is a fragmentary axonometric view of a turbine nozzle-facing.
  • FIG. 4 is a fragmentary axonometric view of a turbine nozzle mounting-ring.
  • FIG. 5 is a partial somewhat schematic view taken on a plane parallel to the axis of the turbine.
  • FIG. 6 is a view. similar to- FIG. 1 illustrating a second form of nozzle embodying myinvention.
  • the nozzle illustrated in-FIGSt l, 2, 3 and 4 forms a part of an-axial flow turbine which, as to'the structure not illustrated, may be-of any conventional'or standard construction; It may have structure such as are illustrated in my copendingapplication for Variable Turbine Nozzles Ser. No. 836,423 filed June 25, 1969.
  • the turbine includes a case 5 with' a flange 6 to which is bolted the outer'shroud 7 of a turbine nozzle or'stator vane ring which also comprises an'inner shroud 8. anda ring of flowdirecting vanes or-airfoils 10.
  • the outer shroud 7 includes a structural mounting ring ll.bolted toflange 6 and a porous facing definedby a forward or upstream ring 12and-a rear or downstream ring 14; the'latter being securedby bolts 15.to the' rear edge'of the mounting ring.
  • The'upstream facing ring12 may be retained in a slot in a ring 16 bolted to flange 6.
  • Each vane is supported from the mounting rings 11 and 17 by a tubular spine 32 to which the concave and convex walls of the vane are welded, brazed, or otherwise fixed.
  • the ends of this spine are flared into a rectangular or square cross section providing a head 34 received in a recess in the inner surface of ring 11 and a head 35 received in a recess or socket defined by notches 36 in the mating edges of the mounting rings 18 and 19.
  • a strengthening flange 38 is provided around these notches.
  • the vanes 10 define converging nozzles or flow paths 40 through which the gas is discharged from the structure ahead of the nozzle to the turbine rotor (not illustrated) downstream of the nozzle.
  • a second group of vanes or throttling members is arranged alternating with the vanes 10 and movable so as to variably restrict the flow area of the nozzle.
  • a throttling member 42 which may be regarded as a vane of a second set, is mounted in the flow passage 40 between each pair of vanes 10.
  • the vanes or throttling members 42 are of much smaller chord and thickness than the flow directing vanes. They are mounted so as to be movable toward and away from the throat or location of minimum area of the: passage or nozzle between adjacent vanes.
  • Throttling member 42 preferably is a hollow tubular body of streamlined or, in other words, noncambered airfoil cross section. Each member 42 extends from outside the outer mounting ring 11 to the interior of the inner mounting ring 17. However, only the portion between the porous facings is of the airfoil shape.
  • arms50 are coupled by suitable hearings to a unison ring 51 which extends around the axis of the nozzle and is coupled to suitable means by which it may be rotated to vary the position of members 42.
  • Means for actuating the unison ring 51! may be of the nature of that described in my above-mentioned copending application.
  • the extensions 46 may be fixed to the arms 47 and 50 so as to rotate with the shaft 48 or they may be mounted so they may rotate relative to these. Also, extensions 46 may be made rotatable with respect to members 42.
  • the throttling member 42 may be arranged to weathervane or automatically align itself for direction of flow; or, if desired, it may be positively oriented by engagement in the outer and inner mounting ring or facing ring so that the throttling member is aligned by positive engagement with the fixed structure.
  • the extensions 46 pass through an elongated hole 53 in the ring 19 and a similar hole in the ring 11. Any suitable guide structure may be provided to control the rotation of the extensions 46 or members 42.
  • the members 42 move upstream or downstream in the flow passages 40 as the unison ring is rotated, moving the arms 50 and 47 so as to move the throttling members. As each member moves toward or away from the nozzle throat, the area for flow is decreased or increased.
  • the throttling members 42 move so that they remain generally parallel to their original position, although it is possible to vary this relation to some extent by having different effective lengths of the arms 47 and the portion of the arms 50 which couple the extensions 46 to shaft 48.
  • FIG. 6 illustrates a simplified structure in which the movement of the throttling members 42 is a swinging movement about a fixed point in the inner shroud so that the radially inner end of the throttling member .moves relatively little as compared to the movement ofthe radially outer end. With this structure, there is less uniformity in the throttling from end to end of the vanes but this effect is not of particular importance in many cases.
  • FIG. 6 eliminates the need for the shaft 48 and crank 47, but otherwise the structure may be substantially the same as that previously described. Correspond' ing parts shown in FIG. 6 have the same numbers as FIG. 1.
  • the throttling member 42 may have an inner extension 55 rotatably coupled by a pin 57 to a clevis on the portion 19 of the inner mounting ring.
  • the radially outer end of the throttling member 42 bears a rod-like extension 58 which may be rectangular section and which is coupled to the arm 50 by a pin 59 engaging in a clevis 60.
  • the extension 58 may be sufficiently limber to twist when the arm 50 is rotated through the small angle involved or the clevis 60 may be rotatably mounted on the arm 50. It will be seen, therefore, that the structure of HO. 6 is the same as that previously described except that the motion of the radially outer end of the throttling member 42 is substantially greater than that ofthe inner end.
  • means for introducing cooling air behind the porous facings and into the interior of the vane are preferably provided. These may be of the same nature as those described in my copending application Ser. No. 836,423 and the nature thereof is immaterial to my present invention in a variable nozzle. Therefore, it will not be described herein in detail. lt may be pointed out, however, that cooling air may be admitted through holes 61 in the outer shroud and holes 62 in the inner facing. The ends of the vanes may be open to receive air from within the facing and discharge it through the surface of the vane, which may be porous.
  • a variable-area stator vane ring for a turbomachine comprising, in combination, first and second annular shrouds defining a fluid flow path between the shrouds, an annular cascade of fixed flow-deflecting vanes extending from shroud to shroud defining flow passages between adjacent vanes and adapted to determine the direction of fluid flow from the said passages, a set of streamlined throttling members extending generally parallel to the vanes, each throttling member being disposed between two adjacent vanes in a said passage, and means connected to the throttling members for concurrently moving the throttling members upstream and downstream in the passages while maintaining the setting of the throttling members substantially constant, so as to vary the effective area of the vane ring and maintain a substantially constant direction of flow from the passages.
  • a variable-area stator vane ring for a turbomachine comprising, in combination, first and second annular shrouds defining a fluid flow path between the shrouds, an annular cascade of fixed flow-deflecting vanes extending from shroud to shroud defining flow passages between adjacent vanes and adapted to determine the direction of fluid flow from the said passages, a set of streamlined throttling members extending from shroud to shroud generally parallel to the vanes, each throttling member being disposed between two adjacent vanes in a said passage, one end of each throttling member being pivotally connected to one said shroud, and means connected to the other ends of the throttling members for concurrently translating the other ends of the throttling members upstream and downstream in the passages while maintaining the setting of the throttling members substantially constant so as to vary the effective area of the vane ring and maintain a substantially constant direction of flow from the passages.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US836422A 1969-06-25 1969-06-25 Variable vane cascades Expired - Lifetime US3588269A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US83642269A 1969-06-25 1969-06-25

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GB (1) GB1266254A (US06605200-20030812-C00035.png)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4314791A (en) * 1978-03-09 1982-02-09 Motoren- Und Turbinen-Union Munchen Gmbh Variable stator cascades for axial-flow turbines of gas turbine engines
US4355953A (en) * 1980-04-07 1982-10-26 Guy F. Atkinson Company Flow-adjusted hydraulic rotary machine
US4374469A (en) * 1980-12-24 1983-02-22 United Technologies Corporation Variable capacity air cycle refrigeration system
US4652208A (en) * 1985-06-03 1987-03-24 General Electric Company Actuating lever for variable stator vanes
US4679400A (en) * 1983-12-15 1987-07-14 General Electric Company Variable turbine vane support
US6763653B2 (en) 2002-09-24 2004-07-20 General Electric Company Counter rotating fan aircraft gas turbine engine with aft booster
US6763654B2 (en) 2002-09-30 2004-07-20 General Electric Co. Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans
US6763652B2 (en) 2002-09-24 2004-07-20 General Electric Company Variable torque split aircraft gas turbine engine counter rotating low pressure turbines
US20100172760A1 (en) * 2009-01-06 2010-07-08 General Electric Company Non-Integral Turbine Blade Platforms and Systems
US20100202873A1 (en) * 2009-02-06 2010-08-12 General Electric Company Ceramic Matrix Composite Turbine Engine
US20120156045A1 (en) * 2010-12-17 2012-06-21 General Electric Company Methods, systems and apparatus relating to root and platform configurations for turbine rotor blades
US8668445B2 (en) 2010-10-15 2014-03-11 General Electric Company Variable turbine nozzle system
US20140348655A1 (en) * 2013-05-27 2014-11-27 MTU Aero Engines AG Balancing body for a continuous blade arrangement
US20180171819A1 (en) * 2016-12-20 2018-06-21 Rolls-Royce Plc Variable guide vane device
US10280757B2 (en) 2013-10-31 2019-05-07 United Technologies Corporation Gas turbine engine airfoil with auxiliary flow channel
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades
CN114144573A (zh) * 2019-07-24 2022-03-04 赛峰航空发动机公司 涡轮机械整流器级，带有具有根据叶片的取向的可变截面的冷却空气泄漏通道
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4314791A (en) * 1978-03-09 1982-02-09 Motoren- Und Turbinen-Union Munchen Gmbh Variable stator cascades for axial-flow turbines of gas turbine engines
US4355953A (en) * 1980-04-07 1982-10-26 Guy F. Atkinson Company Flow-adjusted hydraulic rotary machine
US4374469A (en) * 1980-12-24 1983-02-22 United Technologies Corporation Variable capacity air cycle refrigeration system
US4679400A (en) * 1983-12-15 1987-07-14 General Electric Company Variable turbine vane support
US4652208A (en) * 1985-06-03 1987-03-24 General Electric Company Actuating lever for variable stator vanes
US6763652B2 (en) 2002-09-24 2004-07-20 General Electric Company Variable torque split aircraft gas turbine engine counter rotating low pressure turbines
US6763653B2 (en) 2002-09-24 2004-07-20 General Electric Company Counter rotating fan aircraft gas turbine engine with aft booster
US6763654B2 (en) 2002-09-30 2004-07-20 General Electric Co. Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans
US20100172760A1 (en) * 2009-01-06 2010-07-08 General Electric Company Non-Integral Turbine Blade Platforms and Systems
US8382436B2 (en) 2009-01-06 2013-02-26 General Electric Company Non-integral turbine blade platforms and systems
US20100202873A1 (en) * 2009-02-06 2010-08-12 General Electric Company Ceramic Matrix Composite Turbine Engine
US8262345B2 (en) 2009-02-06 2012-09-11 General Electric Company Ceramic matrix composite turbine engine
US8668445B2 (en) 2010-10-15 2014-03-11 General Electric Company Variable turbine nozzle system
US20120156045A1 (en) * 2010-12-17 2012-06-21 General Electric Company Methods, systems and apparatus relating to root and platform configurations for turbine rotor blades
US20140348655A1 (en) * 2013-05-27 2014-11-27 MTU Aero Engines AG Balancing body for a continuous blade arrangement
US9816379B2 (en) * 2013-05-27 2017-11-14 MTU Aero Engines AG Balancing body for a continuous blade arrangement
US10280757B2 (en) 2013-10-31 2019-05-07 United Technologies Corporation Gas turbine engine airfoil with auxiliary flow channel
US20180171819A1 (en) * 2016-12-20 2018-06-21 Rolls-Royce Plc Variable guide vane device
US10876407B2 (en) * 2017-02-16 2020-12-29 General Electric Company Thermal structure for outer diameter mounted turbine blades
CN114144573A (zh) * 2019-07-24 2022-03-04 赛峰航空发动机公司 涡轮机械整流器级，带有具有根据叶片的取向的可变截面的冷却空气泄漏通道
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly

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