WO1998055738A1 - A method in or relating to the start of a power turbine and arrangement in power turbine in order to avoid start damage on turbine wheel/housing - Google Patents

A method in or relating to the start of a power turbine and arrangement in power turbine in order to avoid start damage on turbine wheel/housing Download PDF

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Publication number
WO1998055738A1
WO1998055738A1 PCT/NO1998/000162 NO9800162W WO9855738A1 WO 1998055738 A1 WO1998055738 A1 WO 1998055738A1 NO 9800162 W NO9800162 W NO 9800162W WO 9855738 A1 WO9855738 A1 WO 9855738A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
housing
power turbine
power
wheel
Prior art date
Application number
PCT/NO1998/000162
Other languages
French (fr)
Norwegian (no)
Inventor
Lyder Moen
Original Assignee
Dynatrend Asa
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 Dynatrend Asa filed Critical Dynatrend Asa
Priority to EP98921927A priority Critical patent/EP0985083A1/en
Priority to AU74579/98A priority patent/AU7457998A/en
Publication of WO1998055738A1 publication Critical patent/WO1998055738A1/en

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F01D19/02—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith dependent on temperature of component parts, e.g. of turbine-casing
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/10—Heating, e.g. warming-up before starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/262—Restarting after flame-out
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a method in or relating to the start of a power turbine in order to avoid start damage on the turbine wheel and/or housing.
  • the invention relates to an arrangements in a power turbine which, unitary to the purpose of the method aspect, is intended to prevent damage on the turbine wheel and/or housing, especially in connection with start up.
  • a power turbine is a separate expansion turbine driven by the combustion gas from a gas generator.
  • a cooling jacket cannot prevent a start damage and one has, therefore, tried to solve the problem through monitoring the power turbine's rotational speed. If the turbine does not start or accelerates when admission is given, this is considered as indicative of a non-satisfactory clearance between turbine housing and wheel, and the start trial is interrupted. Before the next trial, one has to wait a while.
  • a substantial disadvantage of such a monitoring of rotational speed is that the turbine wheel may rotate a number of times before the problem is discovered and, then, damage will already have arisen.
  • the main object of the invention is to provide a method and a device to prevent damage upon start of a power turbine.
  • a subordinate aspect of the invention one has aimed at enabling pointing out indications of possible damage risks at such an early point of time that damage would be avoidable.
  • said object is achieved by proceeding in accordance with the method as set forth in claim 1, in which it is proposed to heat the turbine housing before start, respectively by equipping a power turbine housing with a heating jacket disposed outside the housing, generally in connection to a cooling jacket as known per se.
  • the turbine housing Upon a start after a non-planned stop, the turbine housing is first heated such that it becomes approximately as hot as the remainder of the turbine, whereafter the turbine is started.
  • the housing When the turbine has reached the working temperature, the housing may, possibly, be cooled in order to reduce the clearance to the turbine wheel, achieving optimal efficiency.
  • the device Upon pointing out such vibration phenomena, the device is adapted such that a starting trial can be interrupted in time, simultaneously as too much cooling is avoided if a cooling jacket is used, as known per se.
  • Vibration and acoustic signals not due to unbalance are usually to weak to be used for analysis or for influencing shut down systems. The reason is that such signals become "drowned" by the gas turbine after which the power turbine is coupled, a special technology being required to separate out the signals from the background noise.
  • the "envelope” or “enveloping technique” used in connection with the above mentioned vibration measurements has for its purpose to amplify weak signals from e.g. an accelerometer. Through this method, higher frequencies are first separated from low-frequent machine vibrations by excluding unnecessary frequency ranges. The problem is to identify the weak signals. A signal from e.g. a bearing ball rolling in the ball race is very weak, and is diffused across a wide frequency range. Therefore, such a signal is well “hidden” in the remainder of the machine noise.
  • the “envelope circuit” amplifies the filtered signal approximately corresponding to the square thereof. Since the sound of members rotating within the machine is repeatable, they may be simulated by harmonic series of sinus waves corresponding to integer multiples of repeatable signals.
  • Figure 1 shows a side elevational view/axial section of a gas turbine with a power turbine shaped and designed in accordance with the present invention
  • Figure 2 shows a rear partial view of the power turbine
  • Figure 3 shows a detail view III stippled encircled in figure 2, on a larger scale
  • Figure 4 shows a sectional view corresponding to the section line IV-IV in figure 3.
  • reference numerals 10 and 12 respectively, denote a compressor rotor and a gas turbine rotor, 14 indicating the rotor of the power turbine.
  • a compressor shaft 16 is suspended in a front frame bearing 18, an intermediate frame bearing 20 and a rear frame bearing 22, the shaft 16' of the power turbine being suspended in a front bearing 22' and a power turbine bearing 24.
  • the inlet 26 to the compressor portion is trumpet-shaped, the exhaust channel being denoted at 28.
  • the housing 30 of the power turbine is, according to the invention, surrounded by a heating jacket 32 which, within the range of subjects, is mentioned as a "thermal manifold"; 34 denoting a heating coil for supplying heat energy to the heating jacket 32.
  • 14a denotes turbine blades.
  • 36 denotes a seal.
  • S denotes a slot between the seal 36
  • a cooling jacket in combination with the heating jacket 32 (stippled in figures 2 - 4) , may be disposed.
  • the turbine housing 30 Upon start up such a gas generator assigned a power turbine, the turbine housing 30 is first heated when one desires start up a short time after stoppage, so that the turbine housing becomes approximately as hot as the remainder of the turbine, whereafter the turbine is started.
  • a brake (not shown) can be used on the shaft 16' of the power turbine. Subsequently to a stoppage not planned, the brake is activated so that the rotor 14 of the power turbine cannot rotate. Thereafter, compressor and gas turbine are started and, then, hot gas from the gas turbine will heat the housing 30 of the power turbine. When the housing 30 of the power turbine has reached a satisfactory temperature, the brake is released.

Abstract

Upon start up of a power turbine shortly after stoppage, the turbine housing (30) would have been cooled quicker than the turbine wheel (14); as a result of material shrinkages, the intermediate clearance will be too small, such that the turbine wheel scratches in too large leakage grooves in the adjacent housing or seal portions. Therefore, it is suggested to heat the power turbine housing (30, 36) before the start of the power turbine, especially upon start shortly after last stoppage. In a power turbine, where start damage should be prevented/avoided, comprising a rotor (14) having turbine blades (14a) surrounded by a stator-forming housing (30), preferably equipped with a seal (36) opposed to the radially outer tips of the turbine blades (14a), and where the turbine housing (30, 36) is, preferably, assigned a cooling jacket, it is suggested that the power turbine housing (30, 36) is assigned a heating jacket (32), e.g. in the form of a thermal manifold.

Description

A METHOD IN OR RELATING TO THE START OF A POWER TURBINE AND ARRANGEMENT IN POWER TURBINE IN ORDER TO AVOID START DAMAGE ON TURBINE WHEEL/HOUSING
The invention relates to a method in or relating to the start of a power turbine in order to avoid start damage on the turbine wheel and/or housing. Likewise, the invention relates to an arrangements in a power turbine which, unitary to the purpose of the method aspect, is intended to prevent damage on the turbine wheel and/or housing, especially in connection with start up.
A power turbine is a separate expansion turbine driven by the combustion gas from a gas generator.
When a power turbine stops, the turbine housing is more rapidly cooled than the turbine wheel, so that the clearance between adjacent portions turbine wheel and turbine housing becomes small. When the turbine wheel rotates, heat and centrifugal forces cause the turbine wheel diameter to increase. Upon start up of a power turbine it is, therefore, necessary that a certain clearance exists between turbine housing and wheel. In principle, this presupposes that the power turbine is allowed to settle down after a stop until material expansions due to heat have contracted themselves so much through shrinkage that the clearance conditions between turbine housing and wheel again are satisfactory for start up without any risk of being capable of damaging each other.
However, there often exists a need for starting up a power turbine very shortly after a stop, in other words: too early. Then, it not seldom happens that the turbine wheel makes a groove-like scratch in the turbine housing. Then, when the temperature of the turbine housing reaches working temperature, the groove will give rise to leakage past the turbine wheel, inevitably resulting in a reduced efficiency.
It represents prior art technique to mount a cooling jacket outside the turbine housing in order to cool it and shrink a possible leakage clearance due to a previous start damage.
If it is cooled too much, damage may arise on account thereof. A cooling jacket cannot prevent a start damage and one has, therefore, tried to solve the problem through monitoring the power turbine's rotational speed. If the turbine does not start or accelerates when admission is given, this is considered as indicative of a non-satisfactory clearance between turbine housing and wheel, and the start trial is interrupted. Before the next trial, one has to wait a while. A substantial disadvantage of such a monitoring of rotational speed is that the turbine wheel may rotate a number of times before the problem is discovered and, then, damage will already have arisen.
The main object of the invention is to provide a method and a device to prevent damage upon start of a power turbine. According to a subordinate aspect of the invention, one has aimed at enabling pointing out indications of possible damage risks at such an early point of time that damage would be avoidable. According to the invention, said object is achieved by proceeding in accordance with the method as set forth in claim 1, in which it is proposed to heat the turbine housing before start, respectively by equipping a power turbine housing with a heating jacket disposed outside the housing, generally in connection to a cooling jacket as known per se.
Upon a start after a non-planned stop, the turbine housing is first heated such that it becomes approximately as hot as the remainder of the turbine, whereafter the turbine is started. When the turbine has reached the working temperature, the housing may, possibly, be cooled in order to reduce the clearance to the turbine wheel, achieving optimal efficiency.
In order to detect risk for damage at a point of time as early as possible, one may, according to the invention, use a vibration measuring system working in accordance with so- called envelope technique and which is adapted to react on vibrations due to the fact that the turbine wheel has come into contact with the turbine housing. Upon pointing out such vibration phenomena, the device is adapted such that a starting trial can be interrupted in time, simultaneously as too much cooling is avoided if a cooling jacket is used, as known per se. Vibration and acoustic signals not due to unbalance, are usually to weak to be used for analysis or for influencing shut down systems. The reason is that such signals become "drowned" by the gas turbine after which the power turbine is coupled, a special technology being required to separate out the signals from the background noise. To-day's methods for protecting aeroplane-based gas generators with a power turbine connected thereto are so defective that shut-down systems with the task of stopping the turbines/ machines before damage occurs due to technical deficiency, are coupled in at a too late state. This means that when a machine is subjected to malfunctions and is switched off due to the protection systems, an unforeseen shut-down is already accrued, which, in its turn, will require considerable repair costs. Additionally, expenses due to equipment stop and replacement works would occur.
The "envelope" or "enveloping technique" used in connection with the above mentioned vibration measurements, has for its purpose to amplify weak signals from e.g. an accelerometer. Through this method, higher frequencies are first separated from low-frequent machine vibrations by excluding unnecessary frequency ranges. The problem is to identify the weak signals. A signal from e.g. a bearing ball rolling in the ball race is very weak, and is diffused across a wide frequency range. Therefore, such a signal is well "hidden" in the remainder of the machine noise. The "envelope circuit" amplifies the filtered signal approximately corresponding to the square thereof. Since the sound of members rotating within the machine is repeatable, they may be simulated by harmonic series of sinus waves corresponding to integer multiples of repeatable signals.
The drawings show a non-restricting exemplary embodiment, wherein:
Figure 1 shows a side elevational view/axial section of a gas turbine with a power turbine shaped and designed in accordance with the present invention;
Figure 2 shows a rear partial view of the power turbine;
Figure 3 shows a detail view III stippled encircled in figure 2, on a larger scale; and
Figure 4 shows a sectional view corresponding to the section line IV-IV in figure 3.
In figure 1, reference numerals 10 and 12, respectively, denote a compressor rotor and a gas turbine rotor, 14 indicating the rotor of the power turbine. A compressor shaft 16 is suspended in a front frame bearing 18, an intermediate frame bearing 20 and a rear frame bearing 22, the shaft 16' of the power turbine being suspended in a front bearing 22' and a power turbine bearing 24.
In the compressor-gas turbine-power turbine combination, the inlet 26 to the compressor portion is trumpet-shaped, the exhaust channel being denoted at 28.
The housing 30 of the power turbine is, according to the invention, surrounded by a heating jacket 32 which, within the range of subjects, is mentioned as a "thermal manifold"; 34 denoting a heating coil for supplying heat energy to the heating jacket 32.
In figures 2 - 4, 14a denotes turbine blades. 36 denotes a seal. The letter S denotes a slot between the seal 36
(included as a part of the housing 30 when mentioning a clearance between the turbine wheel and housing 30) and the outer tips of a turbine blade 14a. An air stream across this seal design will pass along the inverted V-shaped edge cavities of the seal 36.
In combination with the heating jacket 32 (stippled in figures 2 - 4) , a cooling jacket, known per se, not shown, may be disposed.
Upon start up such a gas generator assigned a power turbine, the turbine housing 30 is first heated when one desires start up a short time after stoppage, so that the turbine housing becomes approximately as hot as the remainder of the turbine, whereafter the turbine is started.
Then, the seal 36 and the housing 30 will have expanded such that a clearance exists to the turbine blades 14a. A brake (not shown) can be used on the shaft 16' of the power turbine. Subsequently to a stoppage not planned, the brake is activated so that the rotor 14 of the power turbine cannot rotate. Thereafter, compressor and gas turbine are started and, then, hot gas from the gas turbine will heat the housing 30 of the power turbine. When the housing 30 of the power turbine has reached a satisfactory temperature, the brake is released.

Claims

C l a i m s
1. A method in or relating to the start of a power turbine, especially when a start is to take place shortly after stoppage, c h a r a c t e r i z e d i n that the housing (30,36) of the power turbine is heated prior to said start.
2. A method as set forth in claim 1, c h a r a c t e r i z e d i n that the housing (30, 36) of the power turbine upon start up is heated until it is approximately as hot as the turbine wheel (14, 14a) which has not been sufficiently cooled after stoppage, whereafter the turbine is started.
3. Arrangement in a power turbine in order to prevent/ avoid start damage, comprising a rotor (14) having turbine blades (14a) surrounded by a stator-forming housing (30) , preferably provided with a seal (36) opposed to the radially outer tips of the turbine blades (14a) , c h a r a c t e r i z e d i n that the housing (30,36) of the power turbine is assigned a heating jacket (32) , e.g. in the form of a thermal manifold.
4. A method for pointing out risks for start damage on a power turbine, c h a r a c t e r i z e d i n that the power turbine is monitored by means of a vibration system working according to the envelope/enveloping principle and reacting on vibrations caused by contact between the turbine wheel (14,14a) and the turbine housing (30), possibly the seal (36) of the latter opposed to the turbine wheel
(14,14a), pointing out of such vibrations during start up giving rise to an interruption of the start up trial.
5. A method in or relating to the start of a power turbine, especially when a start is to take place shortly after stoppage, c h a r a c t e r i z e d i n that the shaft (16') of the power turbine is locked, whereafter compressor and gas turbine are started, so that hot gas heats the housing (30) of the power turbine, said locking being nullified when the housing (30) has been sufficiently heated.
6. Arrangements as set forth in claim 5, c h a r a c t e r i z e d i n that the shaft (16') of the power turbine is assigned a brake.
PCT/NO1998/000162 1997-06-05 1998-06-02 A method in or relating to the start of a power turbine and arrangement in power turbine in order to avoid start damage on turbine wheel/housing WO1998055738A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP98921927A EP0985083A1 (en) 1997-06-05 1998-06-02 A method in or relating to the start of a power turbine and arrangement in power turbine in order to avoid start damage on turbine wheel/housing
AU74579/98A AU7457998A (en) 1997-06-05 1998-06-02 A method in or relating to the start of a power turbine and arrangement in powerturbine in order to avoid start damage on turbine wheel/housing

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NO972553A NO306271B1 (en) 1997-06-05 1997-06-05 Procedure in connection with the start of a power turbine and a method for demonstrating the risk of a power turbine start injury
NO972553 1997-06-05

Publications (1)

Publication Number Publication Date
WO1998055738A1 true WO1998055738A1 (en) 1998-12-10

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PCT/NO1998/000162 WO1998055738A1 (en) 1997-06-05 1998-06-02 A method in or relating to the start of a power turbine and arrangement in power turbine in order to avoid start damage on turbine wheel/housing

Country Status (4)

Country Link
EP (1) EP0985083A1 (en)
AU (1) AU7457998A (en)
NO (1) NO306271B1 (en)
WO (1) WO1998055738A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006005162A1 (en) * 2004-07-09 2006-01-19 Pratt & Whitney Canada Corp. Cooling arrangement for an accessory gearbox and method of cooling
EP1717419A1 (en) * 2005-04-28 2006-11-02 Siemens Aktiengesellschaft Method and device for adjustement of a radial clearance in an axial turbomachine and compressor
CN102128061A (en) * 2010-01-12 2011-07-20 西门子公司 Heating system for a turbine
US20120167584A1 (en) * 2009-09-08 2012-07-05 Snecma Controlling blade tip clearances in a turbine engine
US9932862B2 (en) 2013-02-06 2018-04-03 Volvo Truck Corporation Method and apparatus for heating an expansion machine of a waste heat recovery apparatus

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GB301298A (en) * 1927-11-26 1929-05-03 Bbc Brown Boveri & Cie Improvements in and relating to steam or gas turbines
US4302813A (en) * 1978-02-22 1981-11-24 Hitachi, Ltd. Method of controlling operation of rotary machines by diagnosing abnormal conditions
US4422333A (en) * 1982-04-29 1983-12-27 The Franklin Institute Method and apparatus for detecting and identifying excessively vibrating blades of a turbomachine
US4584836A (en) * 1985-01-29 1986-04-29 Westinghouse Electric Corp. Steam turbine restart temperature maintenance system and method
CH670480A5 (en) * 1986-09-11 1989-06-15 Bbc Brown Boveri & Cie Steam turbine with heated flanges - avoids damage from differential thermal expansion by using steam to heat flanges of turbine casing via suitable channels
US4896537A (en) * 1988-06-02 1990-01-30 Westinghouse Electric Corp. Shrouded turbine blade vibration monitor
US5172553A (en) * 1992-01-21 1992-12-22 Westinghouse Electric Corp. Convective, temperature-equalizing system for minimizing cover-to-base turbine casing temperature differentials
EP0522795A1 (en) * 1991-07-09 1993-01-13 General Electric Company Heat shield
EP0537307A1 (en) * 1991-03-26 1993-04-21 Sevillana De Electricidad, S.A Method for maintaining warm turbines

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB301298A (en) * 1927-11-26 1929-05-03 Bbc Brown Boveri & Cie Improvements in and relating to steam or gas turbines
US4302813A (en) * 1978-02-22 1981-11-24 Hitachi, Ltd. Method of controlling operation of rotary machines by diagnosing abnormal conditions
US4422333A (en) * 1982-04-29 1983-12-27 The Franklin Institute Method and apparatus for detecting and identifying excessively vibrating blades of a turbomachine
US4584836A (en) * 1985-01-29 1986-04-29 Westinghouse Electric Corp. Steam turbine restart temperature maintenance system and method
GB2170556A (en) * 1985-01-29 1986-08-06 Westinghouse Electric Corp Steam turbine restart temperature maintenance system and method
CH670480A5 (en) * 1986-09-11 1989-06-15 Bbc Brown Boveri & Cie Steam turbine with heated flanges - avoids damage from differential thermal expansion by using steam to heat flanges of turbine casing via suitable channels
US4896537A (en) * 1988-06-02 1990-01-30 Westinghouse Electric Corp. Shrouded turbine blade vibration monitor
EP0537307A1 (en) * 1991-03-26 1993-04-21 Sevillana De Electricidad, S.A Method for maintaining warm turbines
EP0522795A1 (en) * 1991-07-09 1993-01-13 General Electric Company Heat shield
US5172553A (en) * 1992-01-21 1992-12-22 Westinghouse Electric Corp. Convective, temperature-equalizing system for minimizing cover-to-base turbine casing temperature differentials

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006005162A1 (en) * 2004-07-09 2006-01-19 Pratt & Whitney Canada Corp. Cooling arrangement for an accessory gearbox and method of cooling
US7373771B2 (en) 2004-07-09 2008-05-20 Pratt & Whitney Canada Corp. Cooling arrangement for an accessory gearbox and method of cooling
EP1717419A1 (en) * 2005-04-28 2006-11-02 Siemens Aktiengesellschaft Method and device for adjustement of a radial clearance in an axial turbomachine and compressor
US7766611B2 (en) 2005-04-28 2010-08-03 Siemens Aktiengesellschaft Method for setting a radial gap of an axial-throughflow turbomachine and compressor
US20120167584A1 (en) * 2009-09-08 2012-07-05 Snecma Controlling blade tip clearances in a turbine engine
US9353641B2 (en) * 2009-09-08 2016-05-31 Snecma Controlling blade tip clearances in a turbine engine
CN102128061A (en) * 2010-01-12 2011-07-20 西门子公司 Heating system for a turbine
EP2351912A1 (en) * 2010-01-12 2011-08-03 Siemens Aktiengesellschaft Turbine with heating system, and corresponding solar power plant and operating method
US8695342B2 (en) 2010-01-12 2014-04-15 Siemens Aktiengesellschaft Heating system for a turbine
US9932862B2 (en) 2013-02-06 2018-04-03 Volvo Truck Corporation Method and apparatus for heating an expansion machine of a waste heat recovery apparatus

Also Published As

Publication number Publication date
NO972553L (en) 1998-12-07
EP0985083A1 (en) 2000-03-15
NO306271B1 (en) 1999-10-11
AU7457998A (en) 1998-12-21
NO972553D0 (en) 1997-06-05

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