GB797488A - Gas turbine rotor - Google Patents

Gas turbine rotor

Info

Publication number
GB797488A
GB797488A GB36572/56A GB3657256A GB797488A GB 797488 A GB797488 A GB 797488A GB 36572/56 A GB36572/56 A GB 36572/56A GB 3657256 A GB3657256 A GB 3657256A GB 797488 A GB797488 A GB 797488A
Authority
GB
United Kingdom
Prior art keywords
shrouds
blades
row
blade
reaction
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
GB36572/56A
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.)
Rheinmetall Air Defence AG
Maschinenfabrik Oerlikon AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Maschinenfabrik Oerlikon 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 Werkzeugmaschinenfabrik Oerlikon Buhrle AG, Maschinenfabrik Oerlikon AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Publication of GB797488A publication Critical patent/GB797488A/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Abstract

797,488. Elastic-fluid turbines. MASCHINENFABRIK OERLIKON. Nov. 29, 1956 [Dec. 30, 1955], No. 36572/56. Class 110 (3). The high-pressure end of multi-stage gas turbine rotor comprises at least one row of unshrouded blades 2 providing only a small degree of reaction, whereas the remaining rows of blades 3 are provided at their tips with shrouds 4 and have a high degree of reaction. The shrouds 4 may extend wholly circumferentially around each row of blades, or they may be in segments surrounding groups of blades of each blade row. The object of the invention is to dispense with blade shrouds at the high pressure end of the turbine since these shrouds tend to intercept any impurities such as vanadium pentoxides or sodium oxides contained in the gas stream whereby the balance of the rotor is disturbed. With only a small degree of reaction in the high pressure stage, the pressure drop across the blade row is reduced and the necessity of a blade shroud is avoided.
GB36572/56A 1955-12-30 1956-11-29 Gas turbine rotor Expired GB797488A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH797488X 1955-12-30

Publications (1)

Publication Number Publication Date
GB797488A true GB797488A (en) 1958-07-02

Family

ID=4537402

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36572/56A Expired GB797488A (en) 1955-12-30 1956-11-29 Gas turbine rotor

Country Status (1)

Country Link
GB (1) GB797488A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3034762A (en) * 1960-05-31 1962-05-15 United Aircraft Corp Blade damping means

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3034762A (en) * 1960-05-31 1962-05-15 United Aircraft Corp Blade damping means

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