JPS6483827A - Gas turbine rotor - Google Patents

Gas turbine rotor

Info

Publication number
JPS6483827A
JPS6483827A JP23880987A JP23880987A JPS6483827A JP S6483827 A JPS6483827 A JP S6483827A JP 23880987 A JP23880987 A JP 23880987A JP 23880987 A JP23880987 A JP 23880987A JP S6483827 A JPS6483827 A JP S6483827A
Authority
JP
Japan
Prior art keywords
air passage
disk
rotary shaft
intermediate rotary
cooling
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.)
Pending
Application number
JP23880987A
Other languages
Japanese (ja)
Inventor
Junji Ishii
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.)
Toshiba Corp
Original Assignee
Toshiba 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 Toshiba Corp filed Critical Toshiba Corp
Priority to JP23880987A priority Critical patent/JPS6483827A/en
Publication of JPS6483827A publication Critical patent/JPS6483827A/en
Pending legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE:To enhance durability eliminating the necessity for providing an air passage in the center part of a turbine disk by providing the air passage in the peripheral side of an intermediate rotary shaft between a compressor rotor and the turbine disk and the second air passage, formed radially communicating with the former described air passage, in the turbine disk. CONSTITUTION:In the case of a gas turbine in which a compressor rotor 2b is connected through an intermediate rotary shaft 11 to the first stage turbine disk 32, many circular holes, which extend in the axial direction forming a cooling seal air flow path 15, are provided along the peripheral direction in a side wall part of the intermediate rotary shaft 11. While a cooling air passage 16a, for cooling an end surface of the disk 12, is provided in the intermediate rotary shaft 11 in its connection part to the above described disk 12. Further providing a rotor disk cover 17, integrally formed with the intermediate rotary shaft 11, in the outside of the connection part, a space part 19 is partitioned between the intermediate rotary shaft 11 and the disk 3 2, and the above described cooling air passage 16a and a cooling air passage 16b, cooling a turbine moving blade 9a, are opened to this space part 19.
JP23880987A 1987-09-25 1987-09-25 Gas turbine rotor Pending JPS6483827A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP23880987A JPS6483827A (en) 1987-09-25 1987-09-25 Gas turbine rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP23880987A JPS6483827A (en) 1987-09-25 1987-09-25 Gas turbine rotor

Publications (1)

Publication Number Publication Date
JPS6483827A true JPS6483827A (en) 1989-03-29

Family

ID=17035608

Family Applications (1)

Application Number Title Priority Date Filing Date
JP23880987A Pending JPS6483827A (en) 1987-09-25 1987-09-25 Gas turbine rotor

Country Status (1)

Country Link
JP (1) JPS6483827A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100530759B1 (en) * 1999-02-18 2005-11-23 삼성테크윈 주식회사 Gas turbine engine for the aircraft

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100530759B1 (en) * 1999-02-18 2005-11-23 삼성테크윈 주식회사 Gas turbine engine for the aircraft

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