EP0231952A2
Expired / Lapsed
EP
⏱️ 0.0 years remaining
Method and apparatus for controlling temperatures of turbine casing and turbine rotor
Assignee: Hitachi Ltd
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Filing: 1987-02-06
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Granted: —
•
Expires: 2007-02-06
Abstract
Abstract A method and apparatus for controlling the temperature of a turbine casing (12) and a turbine rotor (14) in a gas turbine (3), which enables the maintenance of an optimum gap at a tip of the rotor blades of the gas turbine over an entire operating range by independently controlling the temperature and the amount of cooling air supplied to the turbine casing and rotor.
Inventors
- 👤 Kazuhiko Kumata
- 👤 Nobuyuki Iizuka
- 👤 Masashi Kunihiro
- 👤 Souichi Kurosawa
Bibliographic Details
Application Number
—
Jurisdiction
EP
Data Source
google_patents
Last Synchronized
2026-10-30 16:54
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/08; F01D11/14; F01D11/20; F01D11/24; F01D19/00; F01D19/02; F01D5/00; F01D5/02; F01D5/08
Claims Analysis
Total Claims: 32
Claim 1
Independent Claim
247 words
An apparatus for controlling temperatures of a turbine casing at a turbine rotor, the apparatus comprising a gas turbine 3 including a turbine casing 12, a turbine rotor 14 rotatably disposed in said turbine casing and a high temperature gas passage means P disposed between said turbine casing and said turbine rotor; compressor means 1 for compressing intake air supplied to the gas turbine 3; means for supplying said compressed air having a controlled temperature through said first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12; means for supplying said compressed air having a controlled temperature through a second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14, said spaces formed in said turbine casing 12 and said turbine rotor 14 communicating with said high temperature gas passage means P; detecting means 20 for detecting an amount of thermal expansion in the radial directions of said turbine casing 12 and said turbine rotor 14; and means for controlling, in response to output signals of said detecting means, amounts of heat energy to be supplied to said spaces of said turbine casing 12 and said turbine rotor 14 through said first and second supplying means, whereby the amount of heat energy supplied to said space of said turbine casing is independent controlled from the amount of heat energy supplied to said space of said turbine rotor 14.
Claim 2
Independent Claim
247 words
An apparatus for controlling temperatures of a turbine casing at a turbine rotor, the apparatus comprising a gas turbine 3 including a turbine casing 12, a turbine rotor 14 rotatably disposed in said turbine casing and a high temperature gas passage means P disposed between said turbine casing and said turbine rotor; compressor means 1 for compressing intake air supplied to the gas turbine 3; means for supplying said compressed air having a controlled temperature through said first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12; means for supplying said compressed air having a controlled temperature through a second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14, said spaces formed in said turbine casing 12 and said turbine rotor 14 communicating with said high temperature gas passage means P; detecting means 20 for detecting an amount of thermal expansion in the radial directions of said turbine casing 12 and said turbine rotor 14; and means for controlling, in response to output signals of said detecting means, amounts of heat energy to be supplied to said spaces of said turbine casing 12 and said turbine rotor 14 through said first and second supplying means, whereby the amount of heat energy supplied to said space of said turbine casing is independent controlled from the amount of heat energy supplied to said space of said turbine rotor 14.
Claim 3
Dependent Claim
41 words
An apparatus according to claim 1, wherein said means for supplying compressed air having a controlled temperature includes at least one intercooler means 7a, 7b for receiving the compressed air and supplying the same to said first and second controlling means.
Claim 4
Dependent Claim
65 words
An apparatus according to claim 2, wherein said first and second controlling means includes at least two air flow rate control valve means 8a, 8b disposed downstream of said at least one intercooler means 7a, 7b for controlling the air flow rate of the temperature controlling air to the spaced formed in the turbine casing 12 and the space formed in the turbine rotor 14.
Claim 5
Dependent Claim
61 words
An apparatus according to claim 2, wherein said means for controlling includes a computer means 18 for receiving the output signal from said detecting means 20, and a flow rate control means 17 for controlling a position of the at least two air flow control rate valve means 8a, 8b in response to an output signal from said computer means 18.
Claim 6
Dependent Claim
62 words
An apparatus according to claim 3, wherein at least one further flow rate control valve means 16a, 16b is disposed on an upstream side of said at least one intercooler means 7a, 7b and wherein said flow rate controller means 17 is adapted to provide a controlling output signal to said at least one further flow rate control valve means 16a, 16b.
Claim 7
Dependent Claim
41 words
An apparatus according to claim 1, wherein said means for supplying compressed air having a controlled temperature includes at least two intercooler means 7a, 7b for receiving the compressed air and supplying the same to said first and second controlling means.
Claim 8
Dependent Claim
63 words
An apparatus according to claim 6, wherein said first and second controlling means includes a first pair of air flow rate control valve means 8a, 8b respectively disposed upstream of the at least two intercooler means 7a, 7b, and a second pair of air flow rate control valve means 16a, 16b respectively disposed downstream of the at least two intercooler means 7a, 7b.
Claim 9
Dependent Claim
64 words
An apparatus according to claim 7, wherein said means for controlling includes a computer means 18 for receiving the output signal from said detecting means, and a flow rate controller means 17 for controlling a position of the first and second pair of air flow rate control valve means 7a, 7b, 16a, 16b, in response to an output signal from said computer means 18.
Claim 10
Dependent Claim
53 words
An apparatus according to claim 6, wherein said first controlling means includes an air flow rate control valve means 16a disposed downstream of one 7a of said intercooler means 7a, 7b, said second controlling means includes a flow rate control orifice means 16b disposed downstream of the other 7b of said intercooler means.
Claim 11
Dependent Claim
58 words
An apparatus according to claim 9, wherein said means for controlling includes a computer means 18 for receiving the output signal from said detecting means 20, and a flow rate controller means 17 for controlling a position of the air flow rate control valve means 16a, 16b in response to an output signal from said computer means 18.
Claim 12
Dependent Claim
64 words
An apparatus according to claim 10, wherein said first and second controlling means further includes at least two further air flow rate control valve means 8a, 8b respectively disposed upstream of said intercooler means 7a, 7b, and wherein said flow rate controller means 17 is adapted to provide a controlling output signal to said two further air flow rate control valve means 8a, 8b.
Claim 13
Dependent Claim
52 words
An apparatus according to claim 5, wherein said first controlling means includes a flow rate control orifice means 16a disposed downstream of one 7a of said intercooler means, and the second controlling means includes an air flow rate control valve means 16b disposed downstream of the other 7b of said intercooler means.
Claim 14
Dependent Claim
57 words
An apparatus according to claim 12, wherein said means for controlling includes a computer means 18 for receiving the output signal from said detecting means, and a flow rate controller means 17 for controlling a position of the air flow rate control valve means 16a, 16b in response to an output signal from said computer means 18.
Claim 15
Dependent Claim
64 words
An apparatus according to claim 13, wherein said first and second controlling means further includes at least two further air flow rate control valve means 8a, 8b respectively disposed upstream of said intercooler means, 7a, 7b and wherein said flow rate controller means 17 is adapted to provide a controlling output signal to said two further air flow rate control valve means 8a, 8b.
Claim 16
Dependent Claim
64 words
An apparatus according to claim 2, further comprising a second detecting means 22 for detecting an exhaust gas temperature of said gas turbine, and wherein said means for controlling includes a computer means 18 for receiving output signals from both of said detecting means, 20, 22 and a flow rate controller means 17 for controlling an operation of said first and second controlling means.
Claim 17
Dependent Claim
65 words
An apparatus according to claim 15, wherein said first and second controlling means includes at least two air flow rate control valve means 16a, 16b disposed downstream of said at least one intercooler means 7a, 7b for controlling the air flow rate of the temperature controlling air to the space formed in the turbine casing 12 and the space formed in the turbine rotor 14.
Claim 18
Dependent Claim
62 words
An apparatus according to claim 16, wherein at least one further flow rate control valve means 8a, 8b is disposed on an upstream side of said at least one intercooler means 7a, 7b, and wherein said flow rate controller means 17 is adapted to provide a controlling output signal to said at least one further flow rate control valve means 8a, 8b.
Claim 19
Dependent Claim
41 words
An apparatus according to claim 15, wherein said means for supplying compressed air having a controlled temperature includes at least two intercooler means 7a, 7b for receiving the compressed air and supplying the same to said first and second controlling means.
Claim 20
Dependent Claim
63 words
An apparatus according to claim 18, wherein said first and second controlling means includes a first pair of air flow rate control valve means 8a, 8b respectively disposed upstream of the at least two intercooler means 7a, 7b and a second pair of air flow rate control valve means 16a, 16b respectively disposed downstream of the at least two intercooler means 7a, 7b.
Claim 21
Independent Claim
230 words
An apparatus for controlling temperatures of a turbine casing and a turbine rotor, the apparatus comprising: a gas turbine including a turbine casing 12, a turbine rotor 14 rotatably disposed in said turbine casing and a high temperature gas passage means P disposed between said turbine casing 12 and said turbine rotor 14; means for supplying air having a controlled temperature through first controlling means for controlling a temperature of said air to a space formed in said turbine casing 12; means for supplying air having a controlled temperature through second controlling means for controlling a temperature of said air to a space formed in said turbine rotor 14, said spaces formed in said turbine casing 12 and said turbine rotor 14 communicating with said high temperature gas passage means P; detecting means 20 for detecting an amount of thermal expansion in radial directions of said turbine casing 12 and said turbine rotor 14; means 17, 18 for controlling, in response to output signals of said detecting means, amounts of heat energy to be supplied to said spaces of said turbine casing and said turbine rotor through said first and second supplying means, whereby the amounts of heat energy to be supplied to said space of said turbine casing 12 is independently controlled for the amount of heat energy to be supplied to the space of said turbine rotor 14.
Claim 22
Independent Claim
230 words
An apparatus for controlling temperatures of a turbine casing and a turbine rotor, the apparatus comprising: a gas turbine including a turbine casing 12, a turbine rotor 14 rotatably disposed in said turbine casing and a high temperature gas passage means P disposed between said turbine casing 12 and said turbine rotor 14; means for supplying air having a controlled temperature through first controlling means for controlling a temperature of said air to a space formed in said turbine casing 12; means for supplying air having a controlled temperature through second controlling means for controlling a temperature of said air to a space formed in said turbine rotor 14, said spaces formed in said turbine casing 12 and said turbine rotor 14 communicating with said high temperature gas passage means P; detecting means 20 for detecting an amount of thermal expansion in radial directions of said turbine casing 12 and said turbine rotor 14; means 17, 18 for controlling, in response to output signals of said detecting means, amounts of heat energy to be supplied to said spaces of said turbine casing and said turbine rotor through said first and second supplying means, whereby the amounts of heat energy to be supplied to said space of said turbine casing 12 is independently controlled for the amount of heat energy to be supplied to the space of said turbine rotor 14.
Claim 23
Independent Claim
298 words
An apparatus for controlling temperatures of a turbine casing and a turbine rotor, the apparatus comprising: a gas turbine 3 including a turbine casing 12, a turbine rotor 14 rotatably disposed in said turbine casing 12, and a high temperature gas passage means P disposed between said turbine casing 12 and said turbine rotor 14; a compressor means 1 for compressing intake air supplied to the gas turbine 3; means for supplying said compressed air having a controlled temperature through said first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12 thereby increasing a temperature of said turbine casing 12 to a predetermined temperature; means for supplying said compressed air having a controlled temperature through second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14 thereby increasing a temperature of said turbine rotor 3 to a predetermined temperature, said spaces formed in said turbine casing 12 and turbine rotor 14 communicating with said high-temperature gas passage means P; detecting means 20 for detecting an amount of thermal expansion in radial directions of said turbine casing 12 and said turbine rotor 14; means 17, 18 for controlling, in response to the output signals of said detecting means 20, amounts of heat energy to be supplied to said spaces of said turbine casing 12 said turbine rotor 14 through said first and second supply means, whereby the amount of heat energy supplied to said space of said turbine casing 12 is independently controlled from the amount of heat energy supplied to said space of said turbine rotor 14 so that a speed of the thermal expansion of said turbine casing 12 and said turbine rotor 14 is substantially equally adjusted.
Claim 24
Independent Claim
298 words
An apparatus for controlling temperatures of a turbine casing and a turbine rotor, the apparatus comprising: a gas turbine 3 including a turbine casing 12, a turbine rotor 14 rotatably disposed in said turbine casing 12, and a high temperature gas passage means P disposed between said turbine casing 12 and said turbine rotor 14; a compressor means 1 for compressing intake air supplied to the gas turbine 3; means for supplying said compressed air having a controlled temperature through said first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12 thereby increasing a temperature of said turbine casing 12 to a predetermined temperature; means for supplying said compressed air having a controlled temperature through second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14 thereby increasing a temperature of said turbine rotor 3 to a predetermined temperature, said spaces formed in said turbine casing 12 and turbine rotor 14 communicating with said high-temperature gas passage means P; detecting means 20 for detecting an amount of thermal expansion in radial directions of said turbine casing 12 and said turbine rotor 14; means 17, 18 for controlling, in response to the output signals of said detecting means 20, amounts of heat energy to be supplied to said spaces of said turbine casing 12 said turbine rotor 14 through said first and second supply means, whereby the amount of heat energy supplied to said space of said turbine casing 12 is independently controlled from the amount of heat energy supplied to said space of said turbine rotor 14 so that a speed of the thermal expansion of said turbine casing 12 and said turbine rotor 14 is substantially equally adjusted.
Claim 25
Independent Claim
345 words
An apparatus for controlling temperatures of a turbine casing and a turbine rotor, the apparatus comprising: a gas turbine 3 including a turbine casing 12, a turbine rotor 14 rotatably disposed in said turbine casing 12 and a high-temperature gas passage means P disposed between said turbine casing 12 and said turbine rotor 14; a compressor means 1 for compressing intake air for the gas turbine 3; means for supplying said compressed air having a controlled temperature through said first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12 to thereby increase a temperature of said turbine casing 12 through a predetermined temperature; means for supplying said compressed air having a controlled temperature through second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14 to thereby increase a temperature of the turbine rotor 14 to a predetermined tempera ture, said spaces formed in said turbine casing 12 and turbine rotor 14 are in communication with said high temperature gas passage means P; first detecting means 20 for detecting an amount of thermal expansion in radial directions of said turbine casing 12 and said turbine rotor 14; second detecting means 22 for detecting an exhaust gas temperature of said gas turbine 3; means 17, 18 for controlling, in response to output signals of said first and second detecting means 20, 22, amounts of heat energy to be supplied to said spaces of said turbine casing 12 and said turbine rotor 14 through said first and second supplying means, whereby the amount of heat energy supplied to said space of said turbine casing 12 is independently controlled from the amount of heat energy supplied to said space of said turbine rotor 14, so that a speed of thermal expansion of said turbine casing 12 and said turbine rotor 14 is substantially equally adjusted and the flow rate of the compressed air can be controlled to minimum necessary values relative to output ratios of the gas turbine 3.
Claim 26
Independent Claim
345 words
An apparatus for controlling temperatures of a turbine casing and a turbine rotor, the apparatus comprising: a gas turbine 3 including a turbine casing 12, a turbine rotor 14 rotatably disposed in said turbine casing 12 and a high-temperature gas passage means P disposed between said turbine casing 12 and said turbine rotor 14; a compressor means 1 for compressing intake air for the gas turbine 3; means for supplying said compressed air having a controlled temperature through said first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12 to thereby increase a temperature of said turbine casing 12 through a predetermined temperature; means for supplying said compressed air having a controlled temperature through second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14 to thereby increase a temperature of the turbine rotor 14 to a predetermined tempera ture, said spaces formed in said turbine casing 12 and turbine rotor 14 are in communication with said high temperature gas passage means P; first detecting means 20 for detecting an amount of thermal expansion in radial directions of said turbine casing 12 and said turbine rotor 14; second detecting means 22 for detecting an exhaust gas temperature of said gas turbine 3; means 17, 18 for controlling, in response to output signals of said first and second detecting means 20, 22, amounts of heat energy to be supplied to said spaces of said turbine casing 12 and said turbine rotor 14 through said first and second supplying means, whereby the amount of heat energy supplied to said space of said turbine casing 12 is independently controlled from the amount of heat energy supplied to said space of said turbine rotor 14, so that a speed of thermal expansion of said turbine casing 12 and said turbine rotor 14 is substantially equally adjusted and the flow rate of the compressed air can be controlled to minimum necessary values relative to output ratios of the gas turbine 3.
Claim 27
Independent Claim
256 words
A method of controlling temperatures of a turbine casing and a turbine rotor of a gas turbine including a turbine casing, a turbine rotor rotatably disposed in said turbine casing and a high temperature gas passage means disposed between said turbine casing and said turbine rotor, the method comprising the steps of: supplying compressed air from a compressor means 1 connected to said gas turbine 3 having a controlled temperature through first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12; supplying said compressed air having a controlled temperature through second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14, said spaces formed in said turbine casing 12 and said turbine rotor 14 communicating with said high temperature gas passage means P; detecting an amount of thermal expansion in the radial directions of said turbine casing 12 and said turbine rotor 14 and providing an output signal 20′ indicative thereof; and controlling, in response to the output signal of a detected amount of thermal expansion, amounts of heat energy to be supplied to said spaces of said turbine casing 12 and said turbine rotor 14, whereby the amount of heat energy supplied to said space of said turbine casing 12 is independently controlled from the amount of heat energy supplied to said space of said turbine rotor 14 so that a speed of thermal expansion of said turbine casing and turbine rotor is substantially equally adjusted.
Claim 28
Independent Claim
256 words
A method of controlling temperatures of a turbine casing and a turbine rotor of a gas turbine including a turbine casing, a turbine rotor rotatably disposed in said turbine casing and a high temperature gas passage means disposed between said turbine casing and said turbine rotor, the method comprising the steps of: supplying compressed air from a compressor means 1 connected to said gas turbine 3 having a controlled temperature through first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12; supplying said compressed air having a controlled temperature through second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14, said spaces formed in said turbine casing 12 and said turbine rotor 14 communicating with said high temperature gas passage means P; detecting an amount of thermal expansion in the radial directions of said turbine casing 12 and said turbine rotor 14 and providing an output signal 20′ indicative thereof; and controlling, in response to the output signal of a detected amount of thermal expansion, amounts of heat energy to be supplied to said spaces of said turbine casing 12 and said turbine rotor 14, whereby the amount of heat energy supplied to said space of said turbine casing 12 is independently controlled from the amount of heat energy supplied to said space of said turbine rotor 14 so that a speed of thermal expansion of said turbine casing and turbine rotor is substantially equally adjusted.
Claim 29
Dependent Claim
78 words
A method of controlling temperatures of a turbine casing and a turbine rotor of a gas turbine according to claim 23, further comprising the step of: detecting an exhaust gas temperature of the gas turbine and supplying an output signal 22′ indicative of the detected temperature, and wherein the step of controlling is responsive to the output signals 20′, 22′ indictive of the detected amount of thermal energy and the detected exhaust gas temperature of the gas turbine.
Claim 30
Independent Claim
273 words
A method of controlling temperatures of a turbine casing and a turbine rotor of a gas turbine including a turbine casing and a turbine rotor rotatably disposed in said turbine casing and a high-temperature gas passage means disposed between said turbine casing and said turbine rotor, the method comprising the steps of: supplying compressed air from a compressor means 1 connected to said gas turbine 3 having a controlled temperature through first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12; supplying said compressed air having a controlled temperature through second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14, said spaces formed in said turbine casing 12 and said turbine rotor 14 being communicated with said high temperature gas passage means P; detecting an amount of thermal expansion in radial directions of said turbine casing and said turbine rotorand providing an output signal 20′ indicative thereof; and controlling, in response to the output signal 20′ of a detected amount of thermal expansion, amounts of heat energy to be supplied to said spaces of said turbine casing 12 and said turbine rotor 14, whereby the amount of heat energy supplied to said space of said turbine casing 12 is independently controlled from the amount of heat energy supplied to said space of said turbine rotor 14 so that a speed of the thermal expansion in the radial direction of said turbine casing is larger than a thermal expansion of said turbine rotor from a start-up condition to a rated-condition of said gas turbine.
Claim 31
Independent Claim
273 words
A method of controlling temperatures of a turbine casing and a turbine rotor of a gas turbine including a turbine casing and a turbine rotor rotatably disposed in said turbine casing and a high-temperature gas passage means disposed between said turbine casing and said turbine rotor, the method comprising the steps of: supplying compressed air from a compressor means 1 connected to said gas turbine 3 having a controlled temperature through first controlling means for controlling a temperature of said compressed air to a space formed in said turbine casing 12; supplying said compressed air having a controlled temperature through second controlling means for controlling a temperature of said compressed air to a space formed in said turbine rotor 14, said spaces formed in said turbine casing 12 and said turbine rotor 14 being communicated with said high temperature gas passage means P; detecting an amount of thermal expansion in radial directions of said turbine casing and said turbine rotorand providing an output signal 20′ indicative thereof; and controlling, in response to the output signal 20′ of a detected amount of thermal expansion, amounts of heat energy to be supplied to said spaces of said turbine casing 12 and said turbine rotor 14, whereby the amount of heat energy supplied to said space of said turbine casing 12 is independently controlled from the amount of heat energy supplied to said space of said turbine rotor 14 so that a speed of the thermal expansion in the radial direction of said turbine casing is larger than a thermal expansion of said turbine rotor from a start-up condition to a rated-condition of said gas turbine.
Claim 32
Dependent Claim
78 words
A method of controlling temperatures of a turbine casing and a turbine rotor of a gas turbine according to claim 25, further comprising the step of: detecting an exhaust gas temperature of the gas turbine and supplying an output signal 22′ indicative of the detected temperature, and wherein the step of controlling is responsive to the output signals 20′, 22′ indicative of the detected amount of thermal energy and the detected exhaust gas temperature of the gas turbine.
References Cited (Backward Citations)
No citation records indexed.
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