US20070039331A1 - Modular gas turbine - Google Patents
Modular gas turbine Download PDFInfo
- Publication number
- US20070039331A1 US20070039331A1 US10/707,557 US70755703A US2007039331A1 US 20070039331 A1 US20070039331 A1 US 20070039331A1 US 70755703 A US70755703 A US 70755703A US 2007039331 A1 US2007039331 A1 US 2007039331A1
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- United States
- Prior art keywords
- gas turbine
- pressure
- modules
- turbine
- recited
- 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.)
- Granted
Links
- 238000007789 sealing Methods 0.000 claims description 13
- 238000012856 packing Methods 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 3
- 230000005611 electricity Effects 0.000 claims description 2
- 238000012790 confirmation Methods 0.000 claims 2
- 230000000007 visual effect Effects 0.000 claims 2
- 238000000034 method Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 79
- 238000002485 combustion reaction Methods 0.000 description 7
- 239000000567 combustion gas Substances 0.000 description 5
- 230000007704 transition Effects 0.000 description 4
- 238000001816 cooling Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
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- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/40—Use of a multiplicity of similar components
Definitions
- the present invention relates to method and arrangement for providing a gas turbine that includes a duct for carry-ing gas from a gas turbine inlet to a gas turbine outlet and an outer housing arranged radially outside a wall structure which defines the radially outer limits of the gas duct.
- the gas turbine between the inlet and outlet, is constructed from a plurality of modules, each of which includes a part of the outer housing and a part of the wall structure of the gas duct. At least two adjacent parts of the wall structure of the gas duct are arranged at a distance from one another.
- At least one pressure dividing element provided that is configured to divide off a pressure area in the gas duct at the junction between the two adjacent parts of the wall structure from another pressure area situated between the wall structure of the gas duct and the outer housing.
- Gas turbines of the aforementioned type are used, for ex-ample, as engines for vehicles and aircraft, as prime movers in ships, and in power stations for the generation of electricity.
- each of the modules carries various main components of the gas turbine, such as compressor, combustion chamber, turbine and power turbine.
- a gas duct which carries gas from one main component to another furthermore extends through the modules.
- Manufacturing the gas turbine in modules facilitates both assembly and servicing of the gas turbine.
- sealing elements of the metal sealing ring type are generally used.
- the sealing rings are in this case arranged in radial grooves in the gas duct wall structure of the first module and protrude somewhat outside the outer circumferential surface of the wall structure.
- the gas duct wall structure of the second module is designed with an inside diameter somewhat larger than the diameter of the outer circumferential surface of the first gas duct. This makes it possible to introduce the gas duct of the first module into the gas duct of the second module, the sealing rings finishing up in a clamped position between the outer and inner surfaces respectively of the two ducts.
- An object of the present invention is to provide a sealing arrangement in a gas duct extending through a modular gas turbine, and by means of which satisfactory tightness is achieved at high temperatures and temperature differentials, and which makes it possible to visually verify that the sealing arrangement is correctly fitted in that it has assumed its sealing position before final assembly of the gas turbine.
- the pressure wall is connected to the wall structure of the gas duct and the outer housing of one and the same module by means of a bolted connection. This ensures that the module is pressure-tight before it is assembled with the next module. This furthermore permits relatively easy dismantling of the pressure wall, for example when servicing components such as bearings arranged in the module.
- the pressure wall on an outer circumference thereof, is designed with a radial flange through which the bolted connection extends.
- the fact that the flange is intended to be clamped between the outer housing of two adjacent modules when assembling the gas turbine means that the flange functions as a seal packing between the modules.
- the pressure wall is designed with at least one bellows-shaped section. This improves the ability of the pressure wall to absorb movements caused, for example, by thermal expansion and transient gas pressure variations.
- the pressure wall is made of metal. This gives the pressure wall equivalent thermal expansion characteristics to the gas turbine allowing it to follow movements of the gas turbine due to temperature variations.
- FIG. 1 ( FIG. 1 ) is a diagrammatic side view showing a cross section of a modular gas turbine provided with pressure walls configured according to the present invention
- FIG. 2 ( FIG. 2 ) is a diagrammatic perspective view of a pressure wall configured according to the present invention.
- FIG. 3 ( FIG. 3 ) is a diagrammatic side view showing a cross section of a pressure wall for a modular gas turbine configured according to the present invention.
- FIG. 1 shows a diagram of a modular two-shaft gas turbine 1 comprising (including, but not limited to) main components that include a compressor 2 , a combustion chamber 3 , a turbine 4 and a power turbine 5 .
- the gas turbine 1 comprises three modules: a gas generator module 6 , a center module 7 and a drive module 8 , each of which will be described in more detail below.
- a gas duct 11 for carrying gas from one main component 2 , 3 , 4 , 5 to another extends through modules 6 , 7 , 8 of the gas turbine 1 from a gas turbine inlet 9 to a gas turbine outlet 10 .
- the gas duct 11 is defined by a wall structure 12 , 13 , 14 which divides the gas duct 11 off from the spaces 15 , 16 , 17 , 18 that are formed inside the outer housings 19 , 20 , 21 of the gas turbine modules.
- the gas generator module 6 comprises a compressor 2 driven by a turbine 4 .
- the compressor 2 comprises a compressor rotor 22 that is rotationally fixed by way of a shaft 23 to a turbine rotor 25 arranged in a turbine housing 24 .
- the compressor 2 is connected upstream to the gas turbine inlet 9 .
- the air compressed by the compressor 2 is fed to the inlet of the combustion chamber 3 in a line 52 via a recuperator 26 , the function of which will be described later, in which it has the pressure P 1 .
- the line 52 is terminated, but in actual fact it is connected to the recuperator 26 via the opening 53 .
- fuel is introduced by means of a fuel system and combustion occurs with the aid of the compressed air.
- a first pressure wall 27 which seals off the pressure P 1 from the pressure P 3 , is arranged between the turbine housing, which in its extension towards the center module constitutes a part of the wall structure 12 of the gas duct, and the outer housing 19 of the gas turbine module 6 .
- the pressure wall 27 is here formed with an outer flange 28 and an inner flange 29 , which are fixed to the outer housing 19 and wall structure 12 , respectively, by means of bolted connections 30 , 31 .
- the gas generator module 6 with the higher pressure P 1 , is thereby entirely sealed off from the inlet pressure P 3 of the center module 7 without performing any “blind assembly.”
- the pressure wall 27 furthermore means that no sealing element is required at the transition of the gas duct 11 from the gas generator module 6 to the center module 7 .
- the center module 7 comprises a continuation 13 of the wall structure 12 of the gas duct 11 from the turbine housing 24 .
- a plurality of stator blades 32 which by means of an adjusting mechanism in the space 17 can be set to various positions for guiding the working gas, are arranged in the gas duct 11 .
- the center module 7 is supplied with cooling air, at the pressure P 4 , from a compressor.
- the pressure P 4 is only somewhat higher than P 3 and is sealed off by a second pressure wall 33 formed with an outer flange 34 and an inner flange 35 , which are fixed by means of bolted connections 36 , 37 to the outer housing 20 of the center module 7 and the continuation of the wall structure of the gas duct 13 .
- the center module 7 is therefore also a pressure-tight module and no “blind assembly” is involved when connecting it either to the gas generator module 6 or to the downstream drive module 8 .
- the pressure wall 33 furthermore means that no sealing element is required at the transition of the gas duct 13 from the center module 7 to the drive module 8 .
- the working gas now at the pressure P 5 after having passed through the stator blades 32 , flows on to the drive module 8 which comprises the power turbine 5 , in which the final expansion of the combustion gases occurs down almost to atmospheric pressure P 6 .
- the power turbine 5 here comprises two power turbine rotors 39 , 40 arranged in a power turbine housing 38 , which are rotationally fixed to an output shaft 41 , which is the same as the output shaft of the gas turbine.
- the extension of the power turbine housing 38 both up-stream and downstream, constitutes a part of the wall structure of the gas duct 11 .
- a third pressure wall 42 which seals off the pressure P 5 from the pressure P 6 , is arranged between the power turbine housing 38 and the outer housing 21 of the drive module 8 .
- the third pressure wall 42 is formed with an outer flange 43 and an inner flange 44 that are fixed by means of bolted connections 45 , 46 to the outer housing 21 and the power turbine housing 38 , respectively.
- “blind assembly” of the gas turbine 1 is avoided.
- gas duct 11 downstream of the power turbine 5 is connected to a recuperator 26 makes it possible to recover a part of the residual heat present in the combustion gases after they have passed through the turbine 4 and power turbine 5 .
- This residual heat is used to heat the air compressed by the compressor 2 before it reaches the combustion chamber 3 , which contributes to increased efficiency of the gas turbine 1 .
- the combustion gases After the combustion gases have passed through the recuperator 26 , they are finally led out through the gas turbine outlet 10 .
- the output shaft 41 of the gas turbine 1 is in turn rotationally fixed to an intermediate shaft 47 , to which the assembly that the gas turbine is intended to drive, such as a drive shaft of a vehicle, can be coupled.
- FIG. 2 shows a perspective view of a pressure wall configured according to the teachings of the present invention.
- the pressure wall 27 is formed with an outer flange 28 and an inner flange 29 .
- the flanges are provided with a plurality of through-holes 48 , 49 , through which the bolted connections 30 , 31 extend in order to provide a pressure-tight connection between the outer housing 19 and the pressure wall 27 and between the wall structure 12 of the gas duct and the pressure wall 27 .
- pressure wall 27 is designed with a first bellows-shaped section 50 and a second bellows-shaped section 51 as shown in FIG. 3 permits movements of the pressure wall 27 resulting, for example, from thermal expansions and transient pressure variations of the gas flowing through the gas turbine 1 .
- the gas turbine may be of a single-shaft type; that is to say, a gas turbine in which the shaft connecting compressor and turbine in its extension forms the output drive shaft of the gas turbine. Further-more, there may be a greater number of compressor stages, turbine stages and power turbine stages than de-scribed above.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Separation By Low-Temperature Treatments (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
Abstract
Description
- The present application is a continuation patent application of International Application No. PCT/SE02/01235 filed 20 Jun. 2002 which was published in English pursuant to Article 21(2) of the Patent Cooperation Treaty, and which claims priority to Swedish Application No. 0102325-8 filed 28 Jun. 2001. Both applications are expressly incorporated herein by reference in their entireties.
- 1. Technical Field
- The present invention relates to method and arrangement for providing a gas turbine that includes a duct for carry-ing gas from a gas turbine inlet to a gas turbine outlet and an outer housing arranged radially outside a wall structure which defines the radially outer limits of the gas duct. The gas turbine, between the inlet and outlet, is constructed from a plurality of modules, each of which includes a part of the outer housing and a part of the wall structure of the gas duct. At least two adjacent parts of the wall structure of the gas duct are arranged at a distance from one another. At least one pressure dividing element provided that is configured to divide off a pressure area in the gas duct at the junction between the two adjacent parts of the wall structure from another pressure area situated between the wall structure of the gas duct and the outer housing.
- 2. Background
- Gas turbines of the aforementioned type are used, for ex-ample, as engines for vehicles and aircraft, as prime movers in ships, and in power stations for the generation of electricity.
- Manufacturing the gas turbine in modules, which are then assembled into a complete gas turbine, is already known in the case of gas turbines having a compressor driven by a turbine and a combustion chamber arranged between them, together with a power turbine arranged down-stream of the turbine. In this case, each of the modules carries various main components of the gas turbine, such as compressor, combustion chamber, turbine and power turbine. A gas duct which carries gas from one main component to another furthermore extends through the modules.
- Manufacturing the gas turbine in modules facilitates both assembly and servicing of the gas turbine.
- One problem in connection with assembly of the modules is obtaining satisfactory tightness at the transition of the gas duct between two adjacent modules. At the gas duct transition from a first module to a second module, sealing elements of the metal sealing ring type are generally used. The sealing rings are in this case arranged in radial grooves in the gas duct wall structure of the first module and protrude somewhat outside the outer circumferential surface of the wall structure. In the end section facing the gas duct of the first module, the gas duct wall structure of the second module is designed with an inside diameter somewhat larger than the diameter of the outer circumferential surface of the first gas duct. This makes it possible to introduce the gas duct of the first module into the gas duct of the second module, the sealing rings finishing up in a clamped position between the outer and inner surfaces respectively of the two ducts.
- One problem with the aforementioned type of sealing element, however, is that they are never completely tight and that they are greatly affected by circularity defects in the seal positioning, a condition which often occurs in gas turbine engines due to the high temperatures and temperature differentials which occur in these engines. Another problem in connection with this type of seals is that they only assume their final sealing position when the modules are fully assembled, which means that it is not possible to visually verify that the seals have assumed a correct position.
- An object of the present invention is to provide a sealing arrangement in a gas duct extending through a modular gas turbine, and by means of which satisfactory tightness is achieved at high temperatures and temperature differentials, and which makes it possible to visually verify that the sealing arrangement is correctly fitted in that it has assumed its sealing position before final assembly of the gas turbine.
- According to a preferred embodiment of the invention, the pressure wall is connected to the wall structure of the gas duct and the outer housing of one and the same module by means of a bolted connection. This ensures that the module is pressure-tight before it is assembled with the next module. This furthermore permits relatively easy dismantling of the pressure wall, for example when servicing components such as bearings arranged in the module.
- According to a further preferred embodiment, the pressure wall, on an outer circumference thereof, is designed with a radial flange through which the bolted connection extends. The fact that the flange is intended to be clamped between the outer housing of two adjacent modules when assembling the gas turbine means that the flange functions as a seal packing between the modules.
- According to a further preferred embodiment, the pressure wall is designed with at least one bellows-shaped section. This improves the ability of the pressure wall to absorb movements caused, for example, by thermal expansion and transient gas pressure variations.
- According to a further preferred embodiment, the pressure wall is made of metal. This gives the pressure wall equivalent thermal expansion characteristics to the gas turbine allowing it to follow movements of the gas turbine due to temperature variations.
- The invention will be described below with reference to preferred exemplary embodiments and the accompanying drawings, in which:
-
FIG. 1 (FIG. 1 ) is a diagrammatic side view showing a cross section of a modular gas turbine provided with pressure walls configured according to the present invention; -
FIG. 2 (FIG. 2 ) is a diagrammatic perspective view of a pressure wall configured according to the present invention; and -
FIG. 3 (FIG. 3 ) is a diagrammatic side view showing a cross section of a pressure wall for a modular gas turbine configured according to the present invention. -
FIG. 1 shows a diagram of a modular two-shaft gas turbine 1 comprising (including, but not limited to) main components that include acompressor 2, acombustion chamber 3, a turbine 4 and apower turbine 5. The gas turbine 1 comprises three modules: agas generator module 6, acenter module 7 and adrive module 8, each of which will be described in more detail below. Agas duct 11 for carrying gas from onemain component modules gas turbine outlet 10. Thegas duct 11 is defined by awall structure gas duct 11 off from thespaces outer housings 19, 20, 21 of the gas turbine modules. - The
gas generator module 6 comprises acompressor 2 driven by a turbine 4. Thecompressor 2 comprises acompressor rotor 22 that is rotationally fixed by way of ashaft 23 to aturbine rotor 25 arranged in aturbine housing 24. Thecompressor 2 is connected upstream to the gas turbine inlet 9. The air compressed by thecompressor 2 is fed to the inlet of thecombustion chamber 3 in aline 52 via arecuperator 26, the function of which will be described later, in which it has the pressure P1. InFIG. 1 , theline 52 is terminated, but in actual fact it is connected to therecuperator 26 via theopening 53. In thecombustion chamber 3, fuel is introduced by means of a fuel system and combustion occurs with the aid of the compressed air. - The hot combustion gases, which now have the pressure P2, are then led to the turbine 4 in which a first limited expansion of the combustion gases from the pressure P2 to the lower pressure P3 occurs in order to drive the
compressor 2. Afirst pressure wall 27, which seals off the pressure P1 from the pressure P3, is arranged between the turbine housing, which in its extension towards the center module constitutes a part of thewall structure 12 of the gas duct, and the outer housing 19 of thegas turbine module 6. Thepressure wall 27 is here formed with anouter flange 28 and aninner flange 29, which are fixed to the outer housing 19 andwall structure 12, respectively, by means of boltedconnections gas generator module 6, with the higher pressure P1, is thereby entirely sealed off from the inlet pressure P3 of thecenter module 7 without performing any “blind assembly.” Thepressure wall 27 furthermore means that no sealing element is required at the transition of thegas duct 11 from thegas generator module 6 to thecenter module 7. - From the
gas generator module 6, the working gas flows, at the pressure P3, to thecenter module 7. Thecenter module 7 comprises acontinuation 13 of thewall structure 12 of thegas duct 11 from theturbine housing 24. A plurality ofstator blades 32, which by means of an adjusting mechanism in thespace 17 can be set to various positions for guiding the working gas, are arranged in thegas duct 11. For cooling the adjusting mechanism, thecenter module 7 is supplied with cooling air, at the pressure P4, from a compressor. At this point, the pressure P4 is only somewhat higher than P3 and is sealed off by asecond pressure wall 33 formed with anouter flange 34 and aninner flange 35, which are fixed by means of boltedconnections center module 7 and the continuation of the wall structure of thegas duct 13. Thecenter module 7 is therefore also a pressure-tight module and no “blind assembly” is involved when connecting it either to thegas generator module 6 or to thedownstream drive module 8. Thepressure wall 33 furthermore means that no sealing element is required at the transition of thegas duct 13 from thecenter module 7 to thedrive module 8. - From the
center module 7, the working gas, now at the pressure P5 after having passed through thestator blades 32, flows on to thedrive module 8 which comprises thepower turbine 5, in which the final expansion of the combustion gases occurs down almost to atmospheric pressure P6. Thepower turbine 5 here comprises twopower turbine rotors power turbine housing 38, which are rotationally fixed to anoutput shaft 41, which is the same as the output shaft of the gas turbine. The extension of thepower turbine housing 38, both up-stream and downstream, constitutes a part of the wall structure of thegas duct 11. In the same way as thefirst pressure wall 27 and second 33pressure wall 33 described above, athird pressure wall 42, which seals off the pressure P5 from the pressure P6, is arranged between thepower turbine housing 38 and theouter housing 21 of thedrive module 8. Here, thethird pressure wall 42 is formed with an outer flange 43 and aninner flange 44 that are fixed by means of boltedconnections 45, 46 to theouter housing 21 and thepower turbine housing 38, respectively. Here too, therefore, “blind assembly” of the gas turbine 1 is avoided. - The fact that the
gas duct 11 downstream of thepower turbine 5 is connected to arecuperator 26 makes it possible to recover a part of the residual heat present in the combustion gases after they have passed through the turbine 4 andpower turbine 5. This residual heat is used to heat the air compressed by thecompressor 2 before it reaches thecombustion chamber 3, which contributes to increased efficiency of the gas turbine 1. After the combustion gases have passed through therecuperator 26, they are finally led out through thegas turbine outlet 10. - The
output shaft 41 of the gas turbine 1 is in turn rotationally fixed to anintermediate shaft 47, to which the assembly that the gas turbine is intended to drive, such as a drive shaft of a vehicle, can be coupled. -
FIG. 2 shows a perspective view of a pressure wall configured according to the teachings of the present invention. For the sake of simplicity, only the aforementionedfirst pressure wall 27 will be described because thesecond pressure wall 33 and thethird pressure wall 42 differ only in their geometric design. As previously described, thepressure wall 27 is formed with anouter flange 28 and aninner flange 29. The flanges are provided with a plurality of through-holes connections pressure wall 27 and between thewall structure 12 of the gas duct and thepressure wall 27. - The fact that
pressure wall 27 is designed with a first bellows-shapedsection 50 and a second bellows-shapedsection 51 as shown inFIG. 3 permits movements of thepressure wall 27 resulting, for example, from thermal expansions and transient pressure variations of the gas flowing through the gas turbine 1. - The invention must not be regarded as being limited to the embodiment described above, a number of modifications thereof being possible without departing from the scope of the patent protection. For example, instead of the type described above, the gas turbine may be of a single-shaft type; that is to say, a gas turbine in which the shaft connecting compressor and turbine in its extension forms the output drive shaft of the gas turbine. Further-more, there may be a greater number of compressor stages, turbine stages and power turbine stages than de-scribed above.
Claims (12)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SE0102325A SE519323C2 (en) | 2001-06-28 | 2001-06-28 | Modular gas turbine |
SE0102325-8 | 2001-06-28 | ||
PCT/SE2002/001235 WO2003002851A1 (en) | 2001-06-28 | 2002-06-20 | Modular gas turbine |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/SE2002/001235 Continuation WO2003002851A1 (en) | 2001-06-28 | 2002-06-20 | Modular gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
US20070039331A1 true US20070039331A1 (en) | 2007-02-22 |
US7185498B1 US7185498B1 (en) | 2007-03-06 |
Family
ID=20284674
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/707,557 Expired - Fee Related US7185498B1 (en) | 2001-06-28 | 2003-12-20 | Modular gas turbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US7185498B1 (en) |
EP (1) | EP1407119B8 (en) |
AT (1) | ATE287490T1 (en) |
DE (1) | DE60202680T2 (en) |
SE (1) | SE519323C2 (en) |
WO (1) | WO2003002851A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080042857A1 (en) * | 2004-12-21 | 2008-02-21 | Rolls-Royce Plc | Fire Warning System |
US9492780B2 (en) | 2014-01-16 | 2016-11-15 | Bha Altair, Llc | Gas turbine inlet gas phase contaminant removal |
US10502136B2 (en) | 2014-10-06 | 2019-12-10 | Bha Altair, Llc | Filtration system for use in a gas turbine engine assembly and method of assembling thereof |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE527649C2 (en) * | 2004-06-04 | 2006-05-02 | Volvo Aero Corp | An engine, a vehicle equipped with such an engine, and a connecting element between a first and a second element of an engine |
US7976266B2 (en) * | 2006-06-30 | 2011-07-12 | Solar Turbines Inc | Power system |
US8590151B2 (en) * | 2006-06-30 | 2013-11-26 | Solar Turbines Inc. | System for supporting and servicing a gas turbine engine |
US8672606B2 (en) * | 2006-06-30 | 2014-03-18 | Solar Turbines Inc. | Gas turbine engine and system for servicing a gas turbine engine |
US20080187431A1 (en) * | 2006-06-30 | 2008-08-07 | Ian Trevor Brown | Power system |
EP1895122A1 (en) * | 2006-08-28 | 2008-03-05 | Siemens Aktiengesellschaft | Modular turbine engine |
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US2625013A (en) * | 1948-11-27 | 1953-01-13 | Gen Electric | Gas turbine nozzle structure |
US3077074A (en) * | 1958-09-10 | 1963-02-12 | Gen Motors Corp | Regenerative gas turbine |
US3167914A (en) * | 1961-07-03 | 1965-02-02 | Chrysler Corp | Gas turbine engine housing |
US3761205A (en) * | 1972-03-20 | 1973-09-25 | Avco Corp | Easily maintainable gas turbine engine |
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US4083180A (en) * | 1976-10-01 | 1978-04-11 | Caterpillar Tractor Co. | Gas turbine engine internal insulation |
US4114368A (en) * | 1975-11-10 | 1978-09-19 | Caterpillar Tractor Co. | Support for concentric turbine blade shroud |
US4307568A (en) * | 1979-03-09 | 1981-12-29 | Mtu Motoren-Und Turbinen-Union Munchen Gmbh | Gas turbine power plant having a heat exchanger |
US4534700A (en) * | 1983-01-18 | 1985-08-13 | Bbc Brown, Boveri & Company, Limited | Externally mounted exhaust-gas turbocharger with uncooled gas duct |
US5127606A (en) * | 1990-11-16 | 1992-07-07 | Allied-Signal Inc. | Aircraft engine mount adapter and method |
US6131384A (en) * | 1997-10-16 | 2000-10-17 | Rolls-Royce Deutschland Gmbh | Suspension device for annular gas turbine combustion chambers |
US6309177B1 (en) * | 1999-06-08 | 2001-10-30 | Pratt & Whitney Canada Corp. | Concentricity ring |
-
2001
- 2001-06-28 SE SE0102325A patent/SE519323C2/en not_active IP Right Cessation
-
2002
- 2002-06-20 WO PCT/SE2002/001235 patent/WO2003002851A1/en not_active Application Discontinuation
- 2002-06-20 DE DE60202680T patent/DE60202680T2/en not_active Expired - Lifetime
- 2002-06-20 EP EP02744034A patent/EP1407119B8/en not_active Expired - Lifetime
- 2002-06-20 AT AT02744034T patent/ATE287490T1/en not_active IP Right Cessation
-
2003
- 2003-12-20 US US10/707,557 patent/US7185498B1/en not_active Expired - Fee Related
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Publication number | Priority date | Publication date | Assignee | Title |
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US2625013A (en) * | 1948-11-27 | 1953-01-13 | Gen Electric | Gas turbine nozzle structure |
US3077074A (en) * | 1958-09-10 | 1963-02-12 | Gen Motors Corp | Regenerative gas turbine |
US3167914A (en) * | 1961-07-03 | 1965-02-02 | Chrysler Corp | Gas turbine engine housing |
US3761205A (en) * | 1972-03-20 | 1973-09-25 | Avco Corp | Easily maintainable gas turbine engine |
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US5127606A (en) * | 1990-11-16 | 1992-07-07 | Allied-Signal Inc. | Aircraft engine mount adapter and method |
US6131384A (en) * | 1997-10-16 | 2000-10-17 | Rolls-Royce Deutschland Gmbh | Suspension device for annular gas turbine combustion chambers |
US6309177B1 (en) * | 1999-06-08 | 2001-10-30 | Pratt & Whitney Canada Corp. | Concentricity ring |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20080042857A1 (en) * | 2004-12-21 | 2008-02-21 | Rolls-Royce Plc | Fire Warning System |
US9492780B2 (en) | 2014-01-16 | 2016-11-15 | Bha Altair, Llc | Gas turbine inlet gas phase contaminant removal |
US10502136B2 (en) | 2014-10-06 | 2019-12-10 | Bha Altair, Llc | Filtration system for use in a gas turbine engine assembly and method of assembling thereof |
Also Published As
Publication number | Publication date |
---|---|
DE60202680D1 (en) | 2005-02-24 |
EP1407119B1 (en) | 2005-01-19 |
US7185498B1 (en) | 2007-03-06 |
DE60202680T2 (en) | 2006-01-12 |
EP1407119A1 (en) | 2004-04-14 |
SE0102325D0 (en) | 2001-06-28 |
EP1407119B8 (en) | 2005-06-15 |
SE0102325L (en) | 2002-12-29 |
SE519323C2 (en) | 2003-02-11 |
ATE287490T1 (en) | 2005-02-15 |
WO2003002851A8 (en) | 2005-07-28 |
WO2003002851A1 (en) | 2003-01-09 |
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