FR1373359A - Intermediate stage diaphragms for turbines and axial compressors - Google Patents

Intermediate stage diaphragms for turbines and axial compressors

Info

Publication number
FR1373359A
FR1373359A FR951141A FR951141A FR1373359A FR 1373359 A FR1373359 A FR 1373359A FR 951141 A FR951141 A FR 951141A FR 951141 A FR951141 A FR 951141A FR 1373359 A FR1373359 A FR 1373359A
Authority
FR
France
Prior art keywords
turbines
intermediate stage
axial compressors
stage diaphragms
diaphragms
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
FR951141A
Other languages
French (fr)
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.)
Associated Electrical Industries Ltd
Original Assignee
Associated Electrical Industries 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
Priority claimed from GB3970562A external-priority patent/GB996773A/en
Application filed by Associated Electrical Industries Ltd filed Critical Associated Electrical Industries Ltd
Priority to FR951141A priority Critical patent/FR1373359A/en
Application granted granted Critical
Publication of FR1373359A publication Critical patent/FR1373359A/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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
FR951141A 1962-10-19 1963-10-18 Intermediate stage diaphragms for turbines and axial compressors Expired FR1373359A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR951141A FR1373359A (en) 1962-10-19 1963-10-18 Intermediate stage diaphragms for turbines and axial compressors

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB3970562A GB996773A (en) 1962-10-19 1962-10-19 Improvements in interstage diaphragms for turbines and axial-flow compressors
FR951141A FR1373359A (en) 1962-10-19 1963-10-18 Intermediate stage diaphragms for turbines and axial compressors

Publications (1)

Publication Number Publication Date
FR1373359A true FR1373359A (en) 1964-09-25

Family

ID=26203963

Family Applications (1)

Application Number Title Priority Date Filing Date
FR951141A Expired FR1373359A (en) 1962-10-19 1963-10-18 Intermediate stage diaphragms for turbines and axial compressors

Country Status (1)

Country Link
FR (1) FR1373359A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009004934A1 (en) * 2009-01-16 2010-08-19 Mtu Aero Engines Gmbh Method for mounting an integral inner ring of a turbocompressor stator

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009004934A1 (en) * 2009-01-16 2010-08-19 Mtu Aero Engines Gmbh Method for mounting an integral inner ring of a turbocompressor stator
US8943689B2 (en) 2009-01-16 2015-02-03 Mtu Aero Engines Gmbh Method for mounting an integral inner ring of a turbocompressor stator
DE102009004934B4 (en) 2009-01-16 2021-08-26 MTU Aero Engines AG Method for assembling an integral inner ring of a turbo compressor stator

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