JPS54114620A - Thermal stress reducing method of turbine rotor - Google Patents

Thermal stress reducing method of turbine rotor

Info

Publication number
JPS54114620A
JPS54114620A JP2162278A JP2162278A JPS54114620A JP S54114620 A JPS54114620 A JP S54114620A JP 2162278 A JP2162278 A JP 2162278A JP 2162278 A JP2162278 A JP 2162278A JP S54114620 A JPS54114620 A JP S54114620A
Authority
JP
Japan
Prior art keywords
rotor
turbine
center hole
temperature
holes
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
JP2162278A
Other languages
Japanese (ja)
Inventor
Nobumasa Hara
Kazunari Kimura
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
Tokyo Shibaura Electric Co 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
Application filed by Toshiba Corp, Tokyo Shibaura Electric Co Ltd filed Critical Toshiba Corp
Priority to JP2162278A priority Critical patent/JPS54114620A/en
Publication of JPS54114620A publication Critical patent/JPS54114620A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE: To reduce the thermal stress of a rotor, by equalizing the temperature distribution of the rotor by passing a heating or cooling fluid through a center hole of the rotor.
CONSTITUTION: A number of holes 3 are penetrated in the axial direction of a turbine rotor 2 mounted into a turbine casing 1, heating sources 4 (For example, electric heating sources) are installed to several holes among the holes 3 and conductors connected to the heating sources are extracted from a center hole 5 and connected to a temperature controller. When starting in the case when a turbine is cool, the turbine can be started heating the surface and the inside of the rotor at the same speed by means of the temperature controller. When during the warming-up starting of the turbine and the stopping of the turbine, temperature difference between the surface of the rotor and the center hole can be reduced by passing a cooling fluid through the holes 3 and the center hole 5 because the temperature of the surface of the rotor is higher than the temperature of the center hole.
COPYRIGHT: (C)1979,JPO&Japio
JP2162278A 1978-02-28 1978-02-28 Thermal stress reducing method of turbine rotor Pending JPS54114620A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2162278A JPS54114620A (en) 1978-02-28 1978-02-28 Thermal stress reducing method of turbine rotor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2162278A JPS54114620A (en) 1978-02-28 1978-02-28 Thermal stress reducing method of turbine rotor

Publications (1)

Publication Number Publication Date
JPS54114620A true JPS54114620A (en) 1979-09-06

Family

ID=12060151

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2162278A Pending JPS54114620A (en) 1978-02-28 1978-02-28 Thermal stress reducing method of turbine rotor

Country Status (1)

Country Link
JP (1) JPS54114620A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4880354A (en) * 1987-11-25 1989-11-14 Hitachi, Ltd. Warming structure of gas turbine rotor
US6593547B1 (en) 2000-11-30 2003-07-15 Pacific Scientific Electro Kinetics Division Air gap deicing device
EP1895095A1 (en) * 2006-09-04 2008-03-05 Siemens Aktiengesellschaft Turbine engine and method of operating the same

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4880354A (en) * 1987-11-25 1989-11-14 Hitachi, Ltd. Warming structure of gas turbine rotor
US6593547B1 (en) 2000-11-30 2003-07-15 Pacific Scientific Electro Kinetics Division Air gap deicing device
EP1895095A1 (en) * 2006-09-04 2008-03-05 Siemens Aktiengesellschaft Turbine engine and method of operating the same
WO2008028792A1 (en) * 2006-09-04 2008-03-13 Siemens Aktiengesellschaft Turbine engine and method of operating the same

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