GB833537A - Mechanism for controlling gaseous flow in machines such as turbines and compressors - Google Patents

Mechanism for controlling gaseous flow in machines such as turbines and compressors

Info

Publication number
GB833537A
GB833537A GB12002/57A GB1200257A GB833537A GB 833537 A GB833537 A GB 833537A GB 12002/57 A GB12002/57 A GB 12002/57A GB 1200257 A GB1200257 A GB 1200257A GB 833537 A GB833537 A GB 833537A
Authority
GB
United Kingdom
Prior art keywords
vane
metallic construction
blade
metallic
concave
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
Application number
GB12002/57A
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.)
Cummins Turbo Technologies Ltd
Original Assignee
Holset Engineering Co Ltd
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 Holset Engineering Co Ltd filed Critical Holset Engineering Co Ltd
Publication of GB833537A publication Critical patent/GB833537A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • 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
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • 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
    • 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
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

833,537. Blades for turbines, compressors and fans. HOLSET ENGINEERING CO. Ltd. April 12, 1957 [Aug. 30, 1956], No. 12002/57. Classes 110 (1) and 110 (3). In a rotary bladed machine through which a gaseous fluid flows, such as an axial- or radialflow turbine or compressor, at least a part of each stator vane or blade is formed of two or more metals having different coefficients of thermal expansion which are rigidly connected together so that changes of temperature of the gaseous fluid will cause a change in the shape of the vane or blade. The assembly shown in Fig. 1 is either the inlet nozzle guide vane assembly of an inward radial flow turbine or the diffuser guide vane assembly of a centrifugal type compressor and comprises two end walls 1, 2 with vanes 3 secured therebetween. The vane 3 in Fig. 3 has the radially inner portion 7 formed of bi-metallic construction, lugs 5 being provided to enable the vane to be secured between end walls 1 and 2 with clearance therebetween. In Fig. 4 both the radially inner end 7 and the radially outer end 8 of the vane are of bi-metallic construction, whereas in Fig. 5 the whole of the vane is of bi-metallic construction, this vane having fixing lugs 9. Various constructions of vanes of aerofoil section profile embodying bi-metallic portions are described. In one, the trailing edge portion is of bi-metallic construction, whereas in others the leading and trailing edge portions, the mid-chord portion and the whole profile respectively are of bi-metallic construction. In Fig. 12 the blade comprises a concave wall portion 3b and a convex wall portion 3a of different metals joined together at their leading and trailing edges 19, securing pins 18 being fixed to the inner surface of the concave portion 3b. In Fig. 13 concave and convex wall portions 3b, 3a respectively are secured together at the trailing edge 22 and to a solid leading edge portion 14 at 21, mounting pins 18a being formed on the portion 14.
GB12002/57A 1956-08-30 1957-04-12 Mechanism for controlling gaseous flow in machines such as turbines and compressors Expired GB833537A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US833537XA 1956-08-30 1956-08-30

Publications (1)

Publication Number Publication Date
GB833537A true GB833537A (en) 1960-04-27

Family

ID=22177775

Family Applications (1)

Application Number Title Priority Date Filing Date
GB12002/57A Expired GB833537A (en) 1956-08-30 1957-04-12 Mechanism for controlling gaseous flow in machines such as turbines and compressors

Country Status (1)

Country Link
GB (1) GB833537A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3042371A (en) * 1958-09-04 1962-07-03 United Aircraft Corp Variable camber balding
US4619580A (en) * 1983-09-08 1986-10-28 The Boeing Company Variable camber vane and method therefor
FR2592684A1 (en) * 1985-12-04 1987-07-10 Mtu Muenchen Gmbh DEVICE FOR CONTROLLING OR ADJUSTING A GAS TURBINE OR A TURBOREACTOR.
WO2006137864A1 (en) * 2004-09-22 2006-12-28 Hamilton Sundstrand Corporation Variale area diffuser vane geometry

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3042371A (en) * 1958-09-04 1962-07-03 United Aircraft Corp Variable camber balding
US4619580A (en) * 1983-09-08 1986-10-28 The Boeing Company Variable camber vane and method therefor
FR2592684A1 (en) * 1985-12-04 1987-07-10 Mtu Muenchen Gmbh DEVICE FOR CONTROLLING OR ADJUSTING A GAS TURBINE OR A TURBOREACTOR.
WO2006137864A1 (en) * 2004-09-22 2006-12-28 Hamilton Sundstrand Corporation Variale area diffuser vane geometry

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