GB878988A - Improvements in or relating to a turbine or compressor inlet nozzle assembly - Google Patents

Improvements in or relating to a turbine or compressor inlet nozzle assembly

Info

Publication number
GB878988A
GB878988A GB13432/58A GB1343258A GB878988A GB 878988 A GB878988 A GB 878988A GB 13432/58 A GB13432/58 A GB 13432/58A GB 1343258 A GB1343258 A GB 1343258A GB 878988 A GB878988 A GB 878988A
Authority
GB
United Kingdom
Prior art keywords
sectors
vanes
turbine
housing
assembly
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
GB13432/58A
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.)
MAN AG
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg AG
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 MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Publication of GB878988A publication Critical patent/GB878988A/en
Expired legal-status Critical Current

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
    • 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
    • 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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Abstract

878,988. Axial flow and centrifugal compressors; turbines. MASCHINENFABRIK AUGSBURG - NURNBERG A.G. April 28, 1958 [Oct. 31, 1957], No. 13432/58. Classes 110 (1) and 110 (3). In a turbine or compressor inlet nozzle assembly, the entire ring of guide vanes is subdivided into a number of sectors each comprising a plurality of vanes, each sector being pivotally mounted about an associated axis perpendicular to the direction of flow. As shown for an axial flow turbine (Fig. 3), the assembly is divided into four sectors 23a, 23b, &c., each pivotally mounted by a pin 25 in a housing part 21<SP>1</SP> movable radially in the turbine housing 21 to allow for thermal expansion. Each sector comprises a carrier part 30 rotatably received in a chamber 31 in the corresponding housing part 211 and biased radially inwards by a spring 28 to bear on the spherical peripheral face of an annular projection 33 on the housing. The clearances between the parts 21<SP>1</SP> are sealed by labyrinth packings. Each sector comprises six vanes (Fig. 6) spaced a constant distant t apart, the narrowest cross-sectional width of the passage between two adjacent vanes being # and the narrowest cross-sectional width of the passage between the end vanes of two adjacent sectors being 2# before the sectors have been pivoted. The normal vane passage area of 28 #h (where h is the height of each vane) may be decreased to 20 8h by pivoting the sectors in one direction so as to close the passages between the sectors, or increased to 36 8h by pivoting the sectors in the opposite direction to open these passages to 4#, thus providing a variation of up to 56% of the normal vane passage area. In an alternative embodiment (Figs. 1 and 2, not shown), the assembly comprises two semicircular sectors having sliding abutting diametral surfaces at least one of which may be provided with labyrinth packings. The peripheral faces of the two sectors and the counter face of the housing are spherical, a packing effect being produced in the radial clearance by the formation of peripheral slots in the outer ring of the assembly. Fig. 7 (not shown), illustrates the application of the invention to radial flow turbines.
GB13432/58A 1957-10-31 1958-04-28 Improvements in or relating to a turbine or compressor inlet nozzle assembly Expired GB878988A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE360074X 1957-10-31

Publications (1)

Publication Number Publication Date
GB878988A true GB878988A (en) 1961-10-04

Family

ID=6291742

Family Applications (1)

Application Number Title Priority Date Filing Date
GB13432/58A Expired GB878988A (en) 1957-10-31 1958-04-28 Improvements in or relating to a turbine or compressor inlet nozzle assembly

Country Status (3)

Country Link
CH (1) CH360074A (en)
FR (1) FR1195960A (en)
GB (1) GB878988A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3685921A (en) * 1969-08-14 1972-08-22 Bennes Marrcl Gas turbine with variable blade distributor
EP1143111A3 (en) * 2000-04-04 2003-05-07 Man B&W Diesel Aktiengesellschaft Axial turbomachine with variable guide vanes
US10711798B2 (en) 2016-07-13 2020-07-14 MTU Aero Engines AG Variable turbomachine vane cascade

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1239889B (en) * 1963-06-28 1967-05-03 Licentia Gmbh Inlet guide vane ring for axial turbines, in particular axial gas turbines, with radially resiliently pressed ring segments
DE161559T1 (en) * 1984-05-15 1986-04-10 Aktieselskabet Kongsberg Vaepenfabrikk, Kongsberg INSERTION AND ANGLE LEVEL CONTROL DEVICE FOR COMPRESSOR INLET VANE.
DE4309637A1 (en) * 1993-03-25 1994-09-29 Abb Management Ag Radially flow-through turbocharger turbine
DE4309636C2 (en) * 1993-03-25 2001-11-08 Abb Turbo Systems Ag Baden Radially flow-through turbocharger turbine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3685921A (en) * 1969-08-14 1972-08-22 Bennes Marrcl Gas turbine with variable blade distributor
EP1143111A3 (en) * 2000-04-04 2003-05-07 Man B&W Diesel Aktiengesellschaft Axial turbomachine with variable guide vanes
KR100824894B1 (en) * 2000-04-04 2008-04-23 만 디젤 에스이 Axial flow machine with a guide apparatus comprising a row of adjustable guide vanes
EP2243932A2 (en) * 2000-04-04 2010-10-27 MAN Diesel SE Axial turbomachine with a guiding nozzle comprising a stage of variable guide vanes
EP2243932A3 (en) * 2000-04-04 2011-01-26 MAN Diesel SE Axial turbomachine with a guiding nozzle comprising a stage of variable guide vanes
US10711798B2 (en) 2016-07-13 2020-07-14 MTU Aero Engines AG Variable turbomachine vane cascade

Also Published As

Publication number Publication date
CH360074A (en) 1962-02-15
FR1195960A (en) 1959-11-20

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