[go: up one dir, main page]

GB707353A - Improvements in or relating to axial-flow compressor apparatus - Google Patents

Improvements in or relating to axial-flow compressor apparatus

Info

Publication number
GB707353A
GB707353A GB17728/52A GB1772852A GB707353A GB 707353 A GB707353 A GB 707353A GB 17728/52 A GB17728/52 A GB 17728/52A GB 1772852 A GB1772852 A GB 1772852A GB 707353 A GB707353 A GB 707353A
Authority
GB
United Kingdom
Prior art keywords
annular
shell
flanges
shrouds
axial
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
GB17728/52A
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.)
Westinghouse Electric International Co
Original Assignee
Westinghouse Electric International Co
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 Westinghouse Electric International Co filed Critical Westinghouse Electric International Co
Publication of GB707353A publication Critical patent/GB707353A/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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F01D25/265—Vertically split casings; Clamping arrangements therefor

Landscapes

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

Abstract

707,353. Axial-flow compressors. WESTING- HOUSE ELECTRIC INTERNATIONAL CO. July 14, 1952 [Aug. 3, 1951], No. 17728/52. Class 110(1) In an axial-flow compressor, a number of diaphragm members each carrying a stage of radial stationary vanes have annular flanges extending outwardly normal to the axis of the structure, and are retained within an outer shell with their flanges abutting by means of retaining members disposed at the opposite ends of the shell. The stator blades 41 are carried by annular shrouds 38, 42. The rotor blades 30 are carried by rotor discs 25 which are each formed with teeth for inter-engagement with the adjacent discs 25 and are held together and connected to the shaft by axially extending tie rods. During assembly, rotor discs and stator diaphragms are alternately inserted into the casing shell 32. The shrouds 38 abut against each other at their annular flanges 40 and are held against rotation by the engagement of slots 47 with longitudinally extending members 45 carried by the casing shell 32. The first and last shrouds 38 abut against rings 49 and 52 respectively, one or more annular shims 50 being inserted if desired. Clearances between the flanges 40 and the casing shell 32 and between the members 45 and the bottom walls of the slots 47 allow free radial expansion of the diaphragms. The casing shell 32 may be of steel or titanium alloy.
GB17728/52A 1951-08-03 1952-07-14 Improvements in or relating to axial-flow compressor apparatus Expired GB707353A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US240212A US2724546A (en) 1951-08-03 1951-08-03 Gas turbine apparatus

Publications (1)

Publication Number Publication Date
GB707353A true GB707353A (en) 1954-04-14

Family

ID=22905599

Family Applications (1)

Application Number Title Priority Date Filing Date
GB17728/52A Expired GB707353A (en) 1951-08-03 1952-07-14 Improvements in or relating to axial-flow compressor apparatus

Country Status (2)

Country Link
US (1) US2724546A (en)
GB (1) GB707353A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2741454A (en) * 1954-09-28 1956-04-10 Clifford R Eppley Elastic fluid machine

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3025037A (en) * 1957-10-24 1962-03-13 Bert F Beckstrom Gas turbine
FR2073239A1 (en) * 1969-12-01 1971-10-01 Snecma
US5197856A (en) * 1991-06-24 1993-03-30 General Electric Company Compressor stator
US7513102B2 (en) * 2005-06-06 2009-04-07 General Electric Company Integrated counterrotating turbofan
US7510371B2 (en) * 2005-06-06 2009-03-31 General Electric Company Forward tilted turbine nozzle
US7594388B2 (en) * 2005-06-06 2009-09-29 General Electric Company Counterrotating turbofan engine
US7445426B1 (en) * 2005-06-15 2008-11-04 Florida Turbine Technologies, Inc. Guide vane outer shroud bias arrangement
GB2441543B (en) * 2006-09-07 2008-07-23 Rolls Royce Plc An array of components
IT1399904B1 (en) * 2010-04-21 2013-05-09 Nuovo Pignone Spa STACKED ROTOR WITH TIE AND BOLTED FLANGE AND METHOD

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US917206A (en) * 1908-12-04 1909-04-06 Charles James Watts Circulator.
US2080425A (en) * 1933-02-10 1937-05-18 Milo Ab Turbine
US2247387A (en) * 1940-01-25 1941-07-01 Gen Electric Elastic fluid turbine diaphragm supporting and centering arrangement
CH225221A (en) * 1941-02-06 1943-01-15 Bmw Flugmotorenbau Gmbh Idler for axial compressors or axial turbines.
CH234848A (en) * 1943-02-09 1944-10-31 Tech Studien Ag Rotor for centrifugal machines with rotating bodies arranged axially next to one another and connected to one another by screws.
US2446552A (en) * 1943-09-27 1948-08-10 Westinghouse Electric Corp Compressor
US2591488A (en) * 1946-11-08 1952-04-01 Smith Corp A O Balanced turbodrill
US2592119A (en) * 1947-07-11 1952-04-08 Curtiss Wright Corp Aircraft engine
GB724074A (en) * 1948-08-05 1955-02-16 Edward Archibald Stalker Improvements in blade structures as may be employed in axial flow compressors
US2649243A (en) * 1948-08-05 1953-08-18 Edward A Stalker Axial flow compressor construction

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2741454A (en) * 1954-09-28 1956-04-10 Clifford R Eppley Elastic fluid machine

Also Published As

Publication number Publication date
US2724546A (en) 1955-11-22

Similar Documents

Publication Publication Date Title
GB1525934A (en) Bladed rotor assemblies for turbomachines
GB1461958A (en) Vaned stator assemblies particularly in or for compressors
GB571205A (en) Improvements in and relating to rotors for multistage turbo-machines
GB1041587A (en) Improvements in gas turbine engines
GB938189A (en) Improvements in the construction of turbine and compressor blade elements
GB707353A (en) Improvements in or relating to axial-flow compressor apparatus
GB1296310A (en)
GB1395957A (en) Fluid flow machines and rotors therefor
GB689270A (en) Improvements in axial flow turbines or compressors
GB1217275A (en) Gas turbine engine axial flow multi-stage compressor
GB1266080A (en)
GB831412A (en) Improvements relating to axial-flow turbines
GB867759A (en) Stator vane assemblies for axial-flow compressors or turbines
GB777955A (en) Improvements in or relating to fluid flow machines such as hydraulic, steam or gas turbines or axial-flow compressors
GB727608A (en) Improvements in blade assemblies for gas turbines and the like
GB789733A (en) Improvements in or relating to structural elements for axial-flow compressors or turbines or the like machines
GB586560A (en) Improvements in axial flow compressors and like machines
GB586562A (en) Improvements in high speed axial flow elastic fluid turbines, compressors, superchargers and like apparatus
GB815032A (en) Improvements in or relating to multi-stage axial-flow turbines and compressors
GB789204A (en) Improvements in or relating to axial flow compressors or turbines
GB1527074A (en) Bladed rotors
GB786689A (en) Improvements relating to elastic-fluid turbines
GB724074A (en) Improvements in blade structures as may be employed in axial flow compressors
GB1013835A (en) Improvements in or relating to axial-flow turbines, compressors and exhausters
GB1408618A (en) Gas compressor