CA619018A - Turbine blades - Google Patents

Turbine blades

Info

Publication number
CA619018A
CA619018A CA619018A CA619018DA CA619018A CA 619018 A CA619018 A CA 619018A CA 619018 A CA619018 A CA 619018A CA 619018D A CA619018D A CA 619018DA CA 619018 A CA619018 A CA 619018A
Authority
CA
Canada
Prior art keywords
turbine blades
turbine
blades
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
CA619018A
Inventor
J. Dennis Leonard
J. French Michael
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
Publication date
Application granted granted Critical
Publication of CA619018A publication Critical patent/CA619018A/en
Expired legal-status Critical Current

Links

CA619018A Turbine blades Expired CA619018A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CA619018T

Publications (1)

Publication Number Publication Date
CA619018A true CA619018A (en) 1961-04-25

Family

ID=35861306

Family Applications (1)

Application Number Title Priority Date Filing Date
CA619018A Expired CA619018A (en) Turbine blades

Country Status (1)

Country Link
CA (1) CA619018A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3575522A (en) * 1968-08-30 1971-04-20 Gen Motors Corp Turbine cooling
US4582467A (en) * 1983-12-22 1986-04-15 United Technologies Corporation Two stage rotor assembly with improved coolant flow

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3575522A (en) * 1968-08-30 1971-04-20 Gen Motors Corp Turbine cooling
US4582467A (en) * 1983-12-22 1986-04-15 United Technologies Corporation Two stage rotor assembly with improved coolant flow

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