WO2015044266A1 - Innengehäusenabe für eine gasturbine - Google Patents
Innengehäusenabe für eine gasturbine Download PDFInfo
- Publication number
- WO2015044266A1 WO2015044266A1 PCT/EP2014/070483 EP2014070483W WO2015044266A1 WO 2015044266 A1 WO2015044266 A1 WO 2015044266A1 EP 2014070483 W EP2014070483 W EP 2014070483W WO 2015044266 A1 WO2015044266 A1 WO 2015044266A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- inner housing
- housing hub
- gas turbine
- web
- hub
- Prior art date
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- 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
- F01D25/14—Casings modified therefor
Definitions
- the invention relates to an inner housing hub for a gas turbine.
- the inner housing hub can be arranged in the gas turbine to ei ⁇ ne gas turbine shaft and serves as an inventory ⁇ part of an inner housing together with the inner housing the deflecting exiting combustion chambers hot gases on egg nen in the direction of the gas turbine shaft arranged in the turbine inlet area.
- the inner housing hub is thus flown on its side facing away from the gas turbine shaft side of the hot gases to be deflected.
- the inner housing hub comprises at least one substantially cylindrical jacket-shaped fastening portion with a cylinder jacket-shaped base body, on which the
- Inner housing hub is attached to a suitably formed fastening ⁇ tion component of the gas turbine.
- the term "cylinder jacket" is not to be understood in a strictly mathematical sense.
- the attachment portion or the base ⁇ body are formed as a tubular wall.
- the term zy ⁇ lindermantelförmig thus refers only to the circumferential shape of the wall and not on the thickness of the wall.
- the fastening component can be, for example, a component which is fastened indirectly to an outer housing of the gas turbine.
- the base body of the inner housing hub has a hot side facing a hot gas path and a cold gas side facing away from the hot gas path. The cold side is thus facing the gas turbine shaft.
- At least one web-shaped projection is arranged on the cylinder jacket-shaped base body, which projection extends along the cold side and is arranged on the cold side.
- the web-shaped projection is part of a tongue and groove connection between the cylinder jacket-shaped base body and the fastening component.
- the ridge-shaped protrusion may for example form the spring and are arranged for mounting in a ⁇ extending on the fastener component groove.
- the web-shaped projection could also form the groove of the tongue and groove connection by a groove extending in its upper side, which corresponds to a correspondingly formed spring of the fastening component ⁇ .
- the heat protection can be, for example, a thermal barrier coating, in particular a ceramic protective coating. This leads in particular in the region of the attachment portion to a high wear of the inner housing hub due to start-stop-driven fatigue cracks with subsequent crack growth and flaking of the heat protection from the hot side of the body.
- the invention is based on the object
- the object is achieved in an inner housing hub of the type mentioned above in that the web-shaped projection consists of a first material and the base body of a second material, wherein the first material has a larger thermal expansion coefficient than the second material, so that in at least one operating condition the gas turbine, the thermally induced stresses in the region of the fastening portion relative to an integral of the second material integral formation of the base body and the web-shaped projection are reduced.
- the heat protection on the hot side is thus not improved to reduce the wear, but the formation of the base body is improved to reduce thermal stresses. This is inventively no longer integral with the projection.
- the projection and the base are made of different materials. For example, the two can be made separately and joined together by welding or soldering.
- the protruding from the cylinder shell-shaped base body web-shaped projection, which is thus colder than the rest of the base body is made of a material with a higher coefficient of thermal expansion than the warmer base ⁇ body. Due to the larger coefficient of thermal expansion of the main body pulls the body or not so much together. However, the coefficient of thermal expansion should not be so great that the colder projection expands much more in operation despite lower temperature difference in the region of the projection than the main body.
- the first material and the second material is selected such that they meet the require ⁇ approximations to the inner housing hub and the attachment and according to the invention the different istausdehnungsko ⁇ efficient are such that the thermally induced stresses in the area of the attachment portion from a second of the material existing one-piece design of the body and the web-shaped projection are reduced.
- the base body may comprise one or more web-shaped projections designed according to the invention.
- the inner housing hub is exposed between the hot and cold side of the body high temperature differences, so that the inventive design of Befest Trentsab ⁇ section of the inner housing hub allows a substantial extension of the life of the inner housing hub.
- Inner housing hub for its attachment in the gas turbine der- is attachable to a fastening component, that the web-shaped projection can be arranged in a groove encompassed by the fastening component.
- the web-shaped projection thus forms the tongue of the tongue and groove joint.
- the base body may comprise one or more web-shaped projections designed according to the invention. These may be arranged and a common, divided web form which can be arranged in a groove on the mounting component along its longitudinal extent lined up on the cold side at ⁇ play.
- the fastening section is in to a central axis is arranged ⁇ housing wall, which is flowed around by the hot gas path such that the hot side of the base body facing away from the central axis ⁇ .
- a trained as a housing wall mounting portion is due to its small extent perpendicular to the wall particularly susceptible torecigeru ⁇ fenes by thermal stresses fenes bending. The wear of such Gasturbinenkompo ⁇ nents can be reduced particularly strong with the invention.
- a further advantageous embodiment of the invention can provide that the inner housing hub is formed at least in the region of the attachment portion substantially cylinder jacket-shaped and the at least one web-shaped projection along a circular peripheral line is arranged on the base body, so that a continuous or segmentally divided or interrupted annular web on the cold side is arranged.
- Inner housing hub with an end face in a turbine inlet can be arranged access area, wherein the attachment portion is arranged in the region of the end face.
- Another object of the invention is to provide an inner housing of the type mentioned with an inner housing hub suits ⁇ ben, which is subject to reduced wear.
- the inner housing hub is formed according to one of claims 1 to 5.
- Another object of the invention is to provide a gas turbine subject to reduced wear.
- the gas turbine comprises at least one inner housing according to claim 6.
- FIG. 2 schematically shows an inner housing hub according to an embodiment of the invention in a perspective view
- FIG 3 shows a section of the inner housing hub shown in Figure 2 in a longitudinal section
- Figure 4 shows a schematic section of the inner housing hub shown in Figure 2 with arranged on the projection fastening component in a longitudinal section
- 5 shows schematically an inner casing of a gas turbine with
- Inner housing hub which is formed according to Figure 2 in egg ⁇ ner perspective view.
- 1 shows a schematic sectional view of a gas turbine 1 ⁇ according to the prior art.
- the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3 with a shaft 4, which is also referred to as a turbine runner.
- a turbine runner Along the rotor 3 follow one another an intake housing 6, a compressor 8, a combustion system 9 with at least one combustion chamber 10, a turbine 14 and an exhaust housing 15.
- the one or more combustion chambers 10 each comprise a burner assembly 11 and a housing 12 which is for protection before hot gases with a heat shield 20 is lined.
- the at least one combustion chamber 10 may be ei ⁇ ne ring combustion chamber.
- the gas turbine may alternatively also comprise one or more tube combustion chambers or silo separation chambers.
- the combustion system 9 communicates with a beispielswei ⁇ ring hot gas channel.
- Each Turbi ⁇ nencut is formed of blade rings. Viewed in the flow direction of a working medium follows in the hot runner formed by a number 17 vanes row formed from blades 18 row.
- the guide vanes 17 are secured to an inner housing of a stator 19 while the rotor blades 18 ⁇ a number, for example, by means of a Turbi ⁇ nenrace on the rotor 3 are attached.
- Coupled to the rotor 3 is, for example, a generator (not shown).
- the inner housing hub 24 is cylindrical jacket-shaped with a central axis 26.
- the ei ⁇ ne end portion of the inner housing hub forms a fastening ⁇ supply section 28 from.
- the cylinder jacket-shaped fastening ⁇ tion section 28 includes a cylinder shell-shaped base body 30, which comprises a hot gas path (which is schematically illustrated by the arrow 32) facing the hot side 34 and the hot gas path remote from the cold side 36.
- the hot side 34 may be coated with a heat shield (not shown).
- a web-shaped projection 38 is arranged for fastening the inner housing hub 24.
- the web-shaped projection 38 extends along a circular peripheral line along the cold side 36 of the
- the base body and is arranged on the cold side of the zylindermantelför ⁇ -shaped base body 30 so that it is arranged as a umlau ⁇ fender annular ridge on the cold side 36th
- the annular projection 38 is arranged in an annular groove (not shown) running in the fastening component.
- the inner housing hub 24 can be constructed from two half-shells, which are first brought into abutment separately on the fastening component (not shown) and then joined together. In this case, the circumferential ridge-shaped projection 38 is divided into segments.
- its mountings ⁇ constriction portion 28 is such that the hot side 34 faces away about a center axis 26 is arrange ⁇ te housing wall 40, which flows around the hot gas path 32 from the central axis 26th
- the entire inner housing hub 24 may, except for the web-shaped projection, the structure of the mounting portion, so that the subdivision of the inner housing hub in a mounting portion to the line 42 in the vorlie ⁇ ing embodiment can be chosen freely in a certain way.
- FIG. 3 shows a detail of the dargestell ⁇ th in Figure 2 the inner housing hub in a longitudinal section in the region of the fixing portion 28.
- the designed in the form of a housing wall 40 mounting portion 28 includes a cylindrical jacket-shaped body 30 having a hot side 34 and ei ⁇ ner cold side 36th The hot side is coated with a heat shield 44.
- On the cold side 36 is web-like pre ⁇ jump arranged a 38 whose cross-section 46 can be seen in the figure.
- ⁇ DERS specifics about the transition region of the base body and stegförmigem projection 38 around generated in the operation of the one-piece, known from the prior art configuration of the fixing section, high thermal stresses.
- FIG. 4 shows a detail of the inner housing hub 24 shown in FIG. 2 in the region of the fastening section 28 in a longitudinal section. It is the simplicity illustrated only the main body 30 with the ridge-shaped projection 38 ⁇ half of mounting portion 28th (The on the hot side 34 arranged heat shield 44 was omitted in the figure). Opposite the hot side 34 extends the cold side 36 of the main body 30, wherein in the region of the end face 50 of the main body 30 of the web-shaped projection 38 is disposed on the cold side 36.
- FIG. 5 shows an inner housing 56 of a gas turbine with an inner housing hub 58 according to the invention arranged centrally in the inner housing.
- the inner housing hub 58 encloses a gas turbine shaft (not shown) extending along the central axis 26.
- the inner housing 56 has two inputs 60 and 62 and an annular output 64. At the back 66, the inner housing is closed.
- the inputs 60 and 62 can each be arranged on a combustion chamber outlet of a combustion chamber (not shown).
- the output 64 is at a turbine inlet area (not shown)
- the inner housing 56 serves to deflect the hot gases emerging from the two combustion chambers along the hot gas path 32, which is illustrated schematically by an arrow.
- the hot gases inter alia, flow through this. along the heat-insulated 44 sheathed inner housing hub 58 through the inner housing back through.
- Inner housing hub 58 in the region of its end face 50 by means of the web-shaped, on the cold side 36 circumferentially arranged projection 38 attached to a surrounding of the hub mounting ⁇ component (not shown).
- the inner housing hub 58 according to the invention.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14780800.0A EP3008293B1 (de) | 2013-09-27 | 2014-09-25 | Innengehäusenabe für eine gasturbine |
US15/023,395 US20160208628A1 (en) | 2013-09-27 | 2014-09-25 | Inner housing hub for a gas turbine |
CN201480052858.0A CN105579669B (zh) | 2013-09-27 | 2014-09-25 | 用于燃气涡轮的内壳体毂 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102013219612 | 2013-09-27 | ||
DE102013219612.1 | 2013-09-27 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015044266A1 true WO2015044266A1 (de) | 2015-04-02 |
Family
ID=51660455
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2014/070483 WO2015044266A1 (de) | 2013-09-27 | 2014-09-25 | Innengehäusenabe für eine gasturbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US20160208628A1 (de) |
EP (1) | EP3008293B1 (de) |
CN (1) | CN105579669B (de) |
WO (1) | WO2015044266A1 (de) |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7000406B2 (en) * | 2003-12-03 | 2006-02-21 | Pratt & Whitney Canada Corp. | Gas turbine combustor sliding joint |
EP1744016A1 (de) * | 2005-07-11 | 2007-01-17 | Siemens Aktiengesellschaft | Heissgasführendes Gehäuseelement, Wellenschutzmantel und Gasturbinenanlage |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1118806A1 (de) * | 2000-01-20 | 2001-07-25 | Siemens Aktiengesellschaft | Thermisch belastbare Wand und Verfahren zur Abdichtung eines Spaltes in einer thermisch belasteten Wand |
EP1249577B1 (de) * | 2001-04-12 | 2007-06-06 | Siemens Aktiengesellschaft | Gasturbine mit axial verschiebbaren Gehäuseteilen |
US6910853B2 (en) * | 2002-11-27 | 2005-06-28 | General Electric Company | Structures for attaching or sealing a space between components having different coefficients or rates of thermal expansion |
-
2014
- 2014-09-25 EP EP14780800.0A patent/EP3008293B1/de not_active Not-in-force
- 2014-09-25 US US15/023,395 patent/US20160208628A1/en not_active Abandoned
- 2014-09-25 WO PCT/EP2014/070483 patent/WO2015044266A1/de active Application Filing
- 2014-09-25 CN CN201480052858.0A patent/CN105579669B/zh not_active Expired - Fee Related
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7000406B2 (en) * | 2003-12-03 | 2006-02-21 | Pratt & Whitney Canada Corp. | Gas turbine combustor sliding joint |
EP1744016A1 (de) * | 2005-07-11 | 2007-01-17 | Siemens Aktiengesellschaft | Heissgasführendes Gehäuseelement, Wellenschutzmantel und Gasturbinenanlage |
Also Published As
Publication number | Publication date |
---|---|
US20160208628A1 (en) | 2016-07-21 |
EP3008293A1 (de) | 2016-04-20 |
CN105579669B (zh) | 2017-07-07 |
CN105579669A (zh) | 2016-05-11 |
EP3008293B1 (de) | 2017-11-29 |
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