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GB758696A - Improvements in or relating to the guide blade structure of axial flow compressors - Google Patents

Improvements in or relating to the guide blade structure of axial flow compressors

Info

Publication number
GB758696A
GB758696A GB2423054A GB2423054A GB758696A GB 758696 A GB758696 A GB 758696A GB 2423054 A GB2423054 A GB 2423054A GB 2423054 A GB2423054 A GB 2423054A GB 758696 A GB758696 A GB 758696A
Authority
GB
United Kingdom
Prior art keywords
ring
casing
guide blade
tip
ridges
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
GB2423054A
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.)
Siemens Schuckertwerke AG
Siemens Corp
Original Assignee
Siemens Schuckertwerke AG
Siemens Corp
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 Siemens Schuckertwerke AG, Siemens Corp filed Critical Siemens Schuckertwerke AG
Publication of GB758696A publication Critical patent/GB758696A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Landscapes

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

Abstract

758,696. Axial-flow compressors; blade fixing. SIEMENS-SCHUCKERTWERKE AKT.- GES. Aug. 19, 1954 [Aug. 19, 1953], No. 24230/54. Classes 110(1) and 110(3) In an axial-flow compressor, the guide blade tips are secured to a non-resilient substantially annular support 6, Fig. 1, and the guide blade roots are secured to a substantially annular support 7 which is resilient and is adapted to locate the blade roots by co-operation with the compressor casing. The root of each guide blade 4 is chamfered at 9 and sweated into the ring 7, while the tip is slid into an axial groove in the ring 6 and retained by inserted wires 8. The ring 7 has a thin web 10 which overlaps the following rotor blades, and a thickened portion 11 which is a snug fit in the cylindrical bore of the casing. The thin web 10 allows the part of the ring 7 which carries the blades 4 to expand radially. Adjacent root support rings 12, 7 and 13 abut one another and are located and held against rotation by pins such as 14, 15 which engage the thickened parts such as 11, 16 and are inserted in the joint of the casing and held by screws. Ridges such as 25 co-operate with annular webs 19, 20, 21 to form labyrinth glands. In a modification, Fig. 2, two labyrinth seals in series are formed by thin cylinders 30, 31 screwed to an extension 28 of a guide blade support ring 27 and cooperating with ridges 33 on a ring 35 and similar ridges on a cylinder 34. In a further modification, two rows of whirlremoving stator blades are provided after the last row of rotor blading, their two tip-supporting rings being secured together, with a spacer ring interposed, by screws. The two root-supporting rings are spaced from the inner wall of the casing, and radial location is provided by the engagement of the second tip-supporting ring with an annular surface in the casing.
GB2423054A 1953-08-19 1954-08-19 Improvements in or relating to the guide blade structure of axial flow compressors Expired GB758696A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DES34865A DE1109310B (en) 1953-08-19 1953-08-19 Axial compressor with guide vane rims arranged between the rotating blade rims

Publications (1)

Publication Number Publication Date
GB758696A true GB758696A (en) 1956-10-10

Family

ID=7481677

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2423054A Expired GB758696A (en) 1953-08-19 1954-08-19 Improvements in or relating to the guide blade structure of axial flow compressors

Country Status (3)

Country Link
CH (1) CH327434A (en)
DE (1) DE1109310B (en)
GB (1) GB758696A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3062497A (en) * 1958-11-24 1962-11-06 Ford Motor Co Gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19507673C2 (en) * 1995-03-06 1997-07-03 Mtu Muenchen Gmbh Guide wheel for turbomachinery

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE476399C (en) * 1929-05-15 Siemens Schuckertwerke Akt Ges Device to seal the gap for constant pressure steam turbines
AT106893B (en) * 1923-07-13 1927-07-25 Jan Ing Kieswetter Device for compensating for different thermal expansions between an outer housing wall and an intermediate wall of the same housing, especially in steam or gas turbines.
DE518107C (en) * 1925-04-03 1931-02-24 Jan Kieswetter Device to compensate for different thermal expansions between an outer housing wall and at least one intermediate wall of the same housing, especially in the case of steam or gas turbines
DE538088C (en) * 1927-06-22 1931-11-10 Skoda Kp Steam or gas turbine
BE462182A (en) * 1944-12-22 1900-01-01

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3062497A (en) * 1958-11-24 1962-11-06 Ford Motor Co Gas turbine engine

Also Published As

Publication number Publication date
DE1109310B (en) 1961-06-22
CH327434A (en) 1958-01-31

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