EP3000991A1 - Casing of a turbo machine, method for manufacturing such a casing and gas turbine with such a casing - Google Patents
Casing of a turbo machine, method for manufacturing such a casing and gas turbine with such a casing Download PDFInfo
- Publication number
- EP3000991A1 EP3000991A1 EP14186851.3A EP14186851A EP3000991A1 EP 3000991 A1 EP3000991 A1 EP 3000991A1 EP 14186851 A EP14186851 A EP 14186851A EP 3000991 A1 EP3000991 A1 EP 3000991A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- casing
- apertures
- turbo machine
- axial
- axially extending
- 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.)
- Withdrawn
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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
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- 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
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the present invention relates to the technology of turbo machines. It refers to a casing of a turbo machine according to the preamble of claim 1.
- Fig. 3 shows in a perspective view an example of a turbo machine in form of a gas turbine of the applicant of type GT24.
- the gas turbine 20 of Fig. 3 comprises a rotor 21 rotating about a machine axis and being enclosed by an (inner) casing 22.
- gas turbine 20 comprises an air intake 23, a compressor 24, a first combustor 25, a first, high pressure (HP) turbine 26, a second combustor 27, a second, low pressure (LP) turbine 28 and an exhaust gas outlet 29.
- HP high pressure
- LP low pressure
- the resulting hot gas drives HP turbine 26.
- the reheated hot gas then drives LP turbine 28 and leaves the machine at exhaust gas outlet 29.
- the root cause for the radial, thermal deformation is circumferential stresses in the casing coming from different temperatures in the casing.
- the hotter part, which tries to expand, is under pressure, but it is held back by the adjacent colder part, which tries to contract, and is therewith under tension.
- the result is radial deformation of the casing between ideal, independent deformation of the colder and ideal, independent deformation of the hotter section as they are linked together.
- Document US 4,522,559 deals with a compressor section of a gas turbine engine, comprising a double wall casing, wherein a nonstructural inner wall is removably attached to a thin, structural outer casing.
- the inner wall isolates the thin stator outer casing during transient turbine operations of throttle burst and throttle chop.
- throttle burst and chop the nonstructural inner wall delays rapid heating and cooling of the relatively thin-walled outer casing, and reduces radial misalignment between the stator casing and rotor due to uneven thermal expansion and contraction.
- the non structural inner wall evens-out thermal expansion and contraction of the stator casing with respect to the rotor.
- thermal insulation material is used between the nonstructural inner wall and outer casing.
- a casing of a turbo machine according to the invention extends along a machine axis of said turbo machine and coaxially surrounds a rotor of said turbo machine, thereby defining an annular hot gas path.
- the casing is characterized in that it comprises at least one axial section, wherein a plurality of axially extending apertures are provided in the wall of said casing and distributed around its circumference in order to reduce the individual influence of said at least one axial section on an overall radial deformation by reducing thermally induced circumferential stresses in said at least one axial section.
- said axially extending apertures have the form of axial slots, each said slot having an axial length and a width.
- each of said slots has a width between 0,5mm and 10 mm and an axial length between 1 mm and 400mm, preferably between 1 mm and 200mm.
- the number of said apertures that are distributed around the circumference of said casing in said at least one axial section is between 1 and 50.
- said axially extending apertures are machined apertures.
- said at least one section with said plurality of axially extending apertures is a separate element, which is axially connected to the remaining part of said casing.
- each of said apertures is equipped with a seal.
- each of said apertures is sealed with a sealing plate, especially in form of a sheet metal plate.
- the width of said apertures is defined in such a way as to achieve a minimum width in the apertures during targeted, thermally stable conditions of said turbo machine.
- the inventive method for manufacturing a casing according to the invention is characterized in that said at least one section is equipped with said axial apertures when being separated from said remaining part of said casing, and is then connected to said remaining part of said casing.
- the gas turbine according to the invention comprises a rotor, which rotates around a machine axis and is surrounded by an axially extending casing in a coaxial arrangement. It is characterized in that said casing is a casing according the invention.
- the invention comprises (in one embodiment) the "slotting" of the casing of an axial turbo machine, especially a gas turbine, in areas with a temperature profile or a temperature gradient in axial direction.
- Fig. 1 (a) shows a part of such a turbo machine 10 comprising a rotor 11 with rotating blades 14, which extends along and rotates around a machine axis 12, and is coaxially surrounded by a casing 13, which is equipped on its inner side with stationary guiding vanes 15.
- the casing 13 shows a temperature gradient with temperature T2 at the right end being higher than temperature T1 at a distance to the left (T2 > T1) or vice versa.
- the casing 13 which is assembled from an upper half-shell 13a and a lower half-shell 13b in a parting plane by means of flanges 18a and 18b, comprises an equally distributed plurality of slots 16 (the embodiment of Fig. 2 has 5 slots 16 in upper half-shell 13a and 5 slots 16 in the lower half-shell 13b).
- each slot 16 is sealed with a sealing plate 19 (see Figs. 1(b) and 2 ).
- This sealing plate 19 may especially be a sheet metal plate.
- the casing 13 of a turbo machine 10 receives at distinct sections a distinct number of axial apertures, especially slots 16, over its entire height/wall thickness, distributed around its circumference, with the purpose to prevent the individual influence of said sections on the overall radial deformation by reducing circumferential stresses in said section.
- Said sections influence the overall radial deformation of said casing 13 due to thermally induced stresses.
- said axially extending apertures around the circumference of solid casing are machined.
- said section with said apertures is axially separated from the remaining part of said casing 13. Moreover the axially separated section is first equipped with said axial apertures around its circumference and then reconnected to the casing 13.
- the width W of said apertures (slots) is defined in such a way to achieve a minimum width in the apertures during targeted, thermally stable conditions.
- apertures are defined in such a way as to meet also the geometrical requirements of interfacing parts.
- the number of said apertures (slots) around the circumference of said casing 13 may vary between 1 and 50.
- the width W is preferably between 0,5mm and 10mm and an axial length L between 1 mm and 200mm.
- Said apertures may additionally be equipped with seals. Especially, they may be sealed with sheet metal plates.
- Said apertures are especially used to influence asymmetric deformations of said casing during transient and stead state conditions.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a casing (13) of a turbo machine (10), which extends along a machine axis (12) of said turbo machine (10) and coaxially surrounds a rotor (11) of said turbo machine (10) thereby defining an annular hot gas path.
Said casing (13) comprises at least one axial section, wherein a plurality of axially extending apertures (16) are provided in the wall of said casing (13) and distributed around its circumference in order to reduce the individual influence of said at least one axial section on an overall radial deformation by reducing thermally induced circumferential stresses in said at least one axial section.
Method for manufacturing such a casing and gas turbine comprising such a casing.
Description
- The present invention relates to the technology of turbo machines. It refers to a casing of a turbo machine according to the preamble of claim 1.
- It further relates to a method for manufacturing such a casing.
- It finally relates to a gas turbine with such a casing.
-
Fig. 3 shows in a perspective view an example of a turbo machine in form of a gas turbine of the applicant of type GT24. Thegas turbine 20 ofFig. 3 comprises arotor 21 rotating about a machine axis and being enclosed by an (inner)casing 22. Arranged along the machineaxis gas turbine 20 comprises anair intake 23, acompressor 24, afirst combustor 25, a first, high pressure (HP)turbine 26, asecond combustor 27, a second, low pressure (LP)turbine 28 and anexhaust gas outlet 29. - In operation, air enters the machine through
air intake 23, is compressed bycompressor 24, and is fed tofirst combustor 25 to be used to burn a fuel. The resulting hot gas drives HPturbine 26. As it still contains air, it is then reheated by means ofsecond combustor 27, where fuel is injected into the hot gas stream. The reheated hot gas then drivesLP turbine 28 and leaves the machine atexhaust gas outlet 29. - Due to temperature gradients or temperature profiles along the axis of the casing a distinct radial, thermal deflection arises. Due to the fact that the hotter and the colder sections of the casing are connected together, the radial deflection is influenced by both. Reasons for the temperature gradient could be different temperatures of the surrounding flows in different sections of the casing.
- The root cause for the radial, thermal deformation is circumferential stresses in the casing coming from different temperatures in the casing. The hotter part, which tries to expand, is under pressure, but it is held back by the adjacent colder part, which tries to contract, and is therewith under tension. The result is radial deformation of the casing between ideal, independent deformation of the colder and ideal, independent deformation of the hotter section as they are linked together.
- Document
US 4,522,559 deals with a compressor section of a gas turbine engine, comprising a double wall casing, wherein a nonstructural inner wall is removably attached to a thin, structural outer casing. The inner wall isolates the thin stator outer casing during transient turbine operations of throttle burst and throttle chop. During throttle burst and chop, the nonstructural inner wall delays rapid heating and cooling of the relatively thin-walled outer casing, and reduces radial misalignment between the stator casing and rotor due to uneven thermal expansion and contraction. The non structural inner wall evens-out thermal expansion and contraction of the stator casing with respect to the rotor. To fine tune the actual clearances between stator and rotor and prevent the casing outer wall from overheating, thermal insulation material is used between the nonstructural inner wall and outer casing. - However, such a double wall casing is of high structural complexity and requires a substantial additional amount of work during assembly and disassembly.
- It is an object of the present invention to provide in a casing comparably simple means for reducing the influence of either the hotter or the colder section on the overall radial, thermal deflection of the casing of a turbo machine, especially a gas turbine, via reducing the circumferential, thermal stresses as root cause for the deflection.
- It is another object of the invention to provide a method for manufacturing such a casing.
- It is just another object of the invention to provide a gas turbine with such casing.
- These and other objects are obtained by a turbo machine according to Claim 1, a method according to
Claim 10, and a gas turbine according toClaim 11. - A casing of a turbo machine according to the invention extends along a machine axis of said turbo machine and coaxially surrounds a rotor of said turbo machine, thereby defining an annular hot gas path.
- The casing is characterized in that it comprises at least one axial section, wherein a plurality of axially extending apertures are provided in the wall of said casing and distributed around its circumference in order to reduce the individual influence of said at least one axial section on an overall radial deformation by reducing thermally induced circumferential stresses in said at least one axial section.
- According to an embodiment of the invention said axially extending apertures have the form of axial slots, each said slot having an axial length and a width.
- Specifically, each of said slots has a width between 0,5mm and 10 mm and an axial length between 1 mm and 400mm, preferably between 1 mm and 200mm.
- According to another embodiment of the invention the number of said apertures that are distributed around the circumference of said casing in said at least one axial section is between 1 and 50.
- According to a further embodiment of the invention said axially extending apertures are machined apertures.
- According to just another embodiment of the invention said at least one section with said plurality of axially extending apertures is a separate element, which is axially connected to the remaining part of said casing.
- According to a further embodiment of the invention each of said apertures is equipped with a seal.
- Specifically, each of said apertures is sealed with a sealing plate, especially in form of a sheet metal plate.
- According to another embodiment of the invention the width of said apertures is defined in such a way as to achieve a minimum width in the apertures during targeted, thermally stable conditions of said turbo machine.
- The inventive method for manufacturing a casing according to the invention is characterized in that said at least one section is equipped with said axial apertures when being separated from said remaining part of said casing, and is then connected to said remaining part of said casing.
- The gas turbine according to the invention comprises a rotor, which rotates around a machine axis and is surrounded by an axially extending casing in a coaxial arrangement. It is characterized in that said casing is a casing according the invention.
- The present invention is now to be explained more closely by means of different embodiments and with reference to the attached drawings.
- Fig. 1
- shows two different views (a) and (b) of a detail of a turbo machine according to an embodiment of the invention;
- Fig. 2
- shows a section through a turbo machine according to another embodiment of the invention perpendicular to the machine axis; and
- Fig. 3
- shows in a perspective view an example of a turbo machine in form of a gas turbine of the applicant of type GT24 (with sequential combustion).
- The invention comprises (in one embodiment) the "slotting" of the casing of an axial turbo machine, especially a gas turbine, in areas with a temperature profile or a temperature gradient in axial direction.
-
Fig. 1 (a) shows a part of such aturbo machine 10 comprising arotor 11 with rotatingblades 14, which extends along and rotates around amachine axis 12, and is coaxially surrounded by acasing 13, which is equipped on its inner side with stationary guidingvanes 15. At the right end of machine thecasing 13 shows a temperature gradient with temperature T2 at the right end being higher than temperature T1 at a distance to the left (T2 > T1) or vice versa. - Due to this temperature gradient the hotter part of the
casing 13 tries to expand whereas the colder part tries to contract. The root cause therefore is circumferential, thermal stresses induced by the temperature gradient. These circumferential stresses lead to a radial deflection as thecasing 13 is behaving like a ring. - The result is an "overall average deflection" between hotter and colder section as they are not decoupled from each other. By preventing the circumferential stresses via
slots 16, which extend in axial direction with a width W and an axial length L, distributed around the circumference ofcasing 13, either in the hotter part of the casing 13 (as shown inFig. 1 ) or the colder part of the casing, the overall radial deflection is driven by the "non-slotted" part of the casing. - As shown in
Fig. 2 , thecasing 13, which is assembled from an upper half-shell 13a and a lower half-shell 13b in a parting plane by means offlanges Fig. 2 has 5slots 16 in upper half-shell 13a and 5slots 16 in the lower half-shell 13b). - To close the
slots 16 against a bleeding of gas from an inner flow path, e.g. the annular hot gas path betweencasing 13 androtor 11, eachslot 16 is sealed with a sealing plate 19 (seeFigs. 1(b) and 2 ). Thissealing plate 19 may especially be a sheet metal plate. - There are various options and features possible within the scope of the invention:
- The circumferentially distributed apertures can be easily achieved in connection with an axial split of the casing between hotter and colder sections. Either the hotter or colder, axially separated part is provided with the apertures (slots) before the segments (parts) are reconnected at the axial split.
- Dependent on the surrounding fluid flows and their pressures, it is possible to equip the apertures with additional seals to reduce leakages.
- Dependent on the interfacing parts, the number and the design of the apertures (slots) can be adjusted in such a way to meet the geometrical requirements of the interfacing parts as well as the requirements of the slotted casing itself.
- The apertures can be designed in such a way, to achieve a minimum width in the apertures during targeted, thermally stable conditions.
- Slots can be additionally equipped with additional features, e.g. stress relief bores to improve the lifetime of the casing.
- Thus, the
casing 13 of aturbo machine 10 receives at distinct sections a distinct number of axial apertures, especiallyslots 16, over its entire height/wall thickness, distributed around its circumference, with the purpose to prevent the individual influence of said sections on the overall radial deformation by reducing circumferential stresses in said section. - Said sections influence the overall radial deformation of said
casing 13 due to thermally induced stresses. - Preferably, said axially extending apertures around the circumference of solid casing are machined.
- Preferably, said section with said apertures is axially separated from the remaining part of said
casing 13. Moreover the axially separated section is first equipped with said axial apertures around its circumference and then reconnected to thecasing 13. - The width W of said apertures (slots) is defined in such a way to achieve a minimum width in the apertures during targeted, thermally stable conditions.
- Furthermore, said apertures are defined in such a way as to meet also the geometrical requirements of interfacing parts.
- The number of said apertures (slots) around the circumference of said
casing 13 may vary between 1 and 50. The width W is preferably between 0,5mm and 10mm and an axial length L between 1 mm and 200mm. - Said apertures may additionally be equipped with seals. Especially, they may be sealed with sheet metal plates.
- Said apertures are especially used to influence asymmetric deformations of said casing during transient and stead state conditions.
-
- 10
- turbo machine (e.g. gas turbine)
- 11
- rotor
- 12
- machine axis (of rotation)
- 13
- casing (stator)
- 13a,b
- half-shell
- 14
- blade
- 15
- vane
- 16
- slot (axial)
- 17
- parting plane
- 18a,b
- flange
- 19
- sealing plate
- 20
- gas turbine (z.B. GT24)
- 21
- rotor
- 22
- (inner) casing
- 23
- air intake
- 24
- compressor
- 25
- combustor (z.B. EV)
- 26
- turbine (HP)
- 27
- combustor (z.B. SEV)
- 28
- turbine (LP)
- 29
- exhaust gas outlet
- L
- length (axial)
- W
- width (slot)
- T1,T2
- temperature
Claims (11)
- A casing (13) of a turbo machine (10), which extends along a machine axis (12) of said turbo machine (10) and coaxially surrounds a rotor (11) of said turbo machine (10) thereby defining an annular hot gas path, characterized in that said casing (13) comprises at least one axial section, wherein a plurality of axially extending apertures (16) are provided in the wall of said casing (13) and distributed around its circumference in order to reduce the individual influence of said at least one axial section on an overall radial deformation by reducing thermally induced circumferential stresses in said at least one axial section.
- A casing as claimed in Claim 1, characterized in that said axially extending apertures have the form of axial slots (16), each said slot (16) having an axial length (L) and a width (W).
- A casing as claimed in Claim 2, characterized in that each of said slots (16) has a width (W) between 0,5mm and 10mm and an axial length (L) between 1 mm and 400mm, preferably between 1 mm and 200mm.
- A casing as claimed in Claim 1, characterized in that the number of said apertures (16) that are distributed around the circumference of said casing in said at least one axial section, is between 1 and 50.
- A casing as claimed in Claim 1, characterized in that said axially extending apertures (16) are machined apertures.
- A casing as claimed in Claim 1, characterized in that said at least one section with said plurality of axially extending apertures (16) is a separate element, which is axially connected to the remaining part of said casing.
- A casing as claimed in Claim 1, characterized in that each of said apertures (16) is equipped with a seal (19).
- A casing as claimed in Claim 7, characterized in that each of said apertures (16) is sealed with a sealing plate (19), especially in form of a sheet metal plate.
- A casing as claimed in Claim 2, characterized in that the width (W) of said apertures (16) is defined in such a way as to achieve a minimum width in the apertures during targeted, thermally stable conditions of said turbo machine.
- Method for manufacturing a casing as claimed in Claim 6, characterized in that said at least one section is equipped with said axial apertures (16) when being separated from said remaining part of said casing, and is then connected to said remaining part of said casing.
- A gas turbine comprising a rotor (11), which rotates around a machine axis (12) and is surrounded by an axially extending casing (13) in a coaxial arrangement, characterized in that said casing (13) is a casing according to one of the Claims 1 to 9.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14186851.3A EP3000991A1 (en) | 2014-09-29 | 2014-09-29 | Casing of a turbo machine, method for manufacturing such a casing and gas turbine with such a casing |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14186851.3A EP3000991A1 (en) | 2014-09-29 | 2014-09-29 | Casing of a turbo machine, method for manufacturing such a casing and gas turbine with such a casing |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3000991A1 true EP3000991A1 (en) | 2016-03-30 |
Family
ID=51625920
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14186851.3A Withdrawn EP3000991A1 (en) | 2014-09-29 | 2014-09-29 | Casing of a turbo machine, method for manufacturing such a casing and gas turbine with such a casing |
Country Status (1)
Country | Link |
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EP (1) | EP3000991A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110219708A (en) * | 2018-03-01 | 2019-09-10 | 通用电气公司 | Shell with adjustable lattice structure |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0073689A1 (en) * | 1981-08-31 | 1983-03-09 | Elliott Turbomachinery Company, Inc. | Method and apparatus for controlling thermal growth |
US4522559A (en) | 1982-02-19 | 1985-06-11 | General Electric Company | Compressor casing |
US20050132707A1 (en) * | 2001-11-20 | 2005-06-23 | Andreas Gebhardt | Gas turbo set |
US20090097968A1 (en) * | 2007-10-12 | 2009-04-16 | General Electric Company | Apparatus and method for clearance control of turbine blade tip |
EP2623719A1 (en) * | 2012-01-30 | 2013-08-07 | Pratt & Whitney Canada Corp. | Stress Relieving Slots for Turbine Vane Ring |
-
2014
- 2014-09-29 EP EP14186851.3A patent/EP3000991A1/en not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0073689A1 (en) * | 1981-08-31 | 1983-03-09 | Elliott Turbomachinery Company, Inc. | Method and apparatus for controlling thermal growth |
US4522559A (en) | 1982-02-19 | 1985-06-11 | General Electric Company | Compressor casing |
US20050132707A1 (en) * | 2001-11-20 | 2005-06-23 | Andreas Gebhardt | Gas turbo set |
US20090097968A1 (en) * | 2007-10-12 | 2009-04-16 | General Electric Company | Apparatus and method for clearance control of turbine blade tip |
EP2623719A1 (en) * | 2012-01-30 | 2013-08-07 | Pratt & Whitney Canada Corp. | Stress Relieving Slots for Turbine Vane Ring |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110219708A (en) * | 2018-03-01 | 2019-09-10 | 通用电气公司 | Shell with adjustable lattice structure |
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