CN101619661A - Aft frame with oval-shaped cooling slots and related method - Google Patents
Aft frame with oval-shaped cooling slots and related method Download PDFInfo
- Publication number
- CN101619661A CN101619661A CN200910159430A CN200910159430A CN101619661A CN 101619661 A CN101619661 A CN 101619661A CN 200910159430 A CN200910159430 A CN 200910159430A CN 200910159430 A CN200910159430 A CN 200910159430A CN 101619661 A CN101619661 A CN 101619661A
- Authority
- CN
- China
- Prior art keywords
- framework
- diapire
- cooling
- roof
- oval
- 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.)
- Pending
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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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to an aft frame with oval-shaped cooling slots and a related method. In particular, the invention discloses an aft frame (10) adapted to interface between a combustor transition piece and a first stage turbine nozzle, including: a closed-periphery frame comprised of a top, bottom and pair of side walls (12, 14, 16 and 18). A plurality of cooling holes (26) or apertures having elliptical or oval cross-sectional shapes are provided in one or more of the top, bottom and pair of side walls, extending axially through the closed-periphery frame. The cooling holes have major and minor axes arranged such that the major axes are substantially parallel with the top and bottom walls.
Description
Technical field
The present invention relates to the turbine cooling technology, more particularly, relate to the cooling of the back framework component that between combustor transition section (transition piece) and first order turbine nozzle, is connected as interface (interface).
Background technique
" changeover portion " is interpreted as the pipeline that combustion liner is connected with the first order nozzle of turbine under the background of the endless tube shape burner that is used for electric generation gas turbine.Back framework is the parts that are positioned at the changeover portion outlet end, and thus serves as the interface between changeover portion and the first order turbine nozzle.It is exposed in the high-temperature gas that flows into first order nozzle, and therefore the cooling of back framework component should receive publicity.
More particularly, recirculation in the groove of the high-temperature gas of the changeover portion of flowing through between back framework and first order nozzle causes higher heat gradient.Therefore, need on the rear surface (being framework that side) of back framework, provide effective cooling towards first order nozzle.Current, typical back framework configuration combines the cooling hole that has circular cross-section, so that partial discharge is redirect in these holes via protecting against shock sleeve (this protecting against shock liner ring is around changeover portion), to cool off the back framework.
Yet, still exist demand for the back framework of cooled transition section more effectively.
Summary of the invention
According to exemplary but non-restrictive example of the present invention, avette or oval-shaped cooling hole is provided with around back framework periphery.Because for given section area, avette or oval-shaped hole provides bigger surface area to be used for effective convection current cooling, so the cooling of the back framework that is improved.
Therefore, on the one hand, the present invention relates to be suitable for the back framework that is connected as interface between combustor transition section and first order turbine nozzle, it comprises: the framework that comprises the border seal of roof, diapire and pair of sidewalls; And a plurality of cooling perforates, it runs through one or more in roof, diapire and the pair of sidewalls, and this cooling perforate has oval or avette sectional shape.
On the other hand, the present invention relates to be suitable for the back framework that is connected as interface between combustor transition section and first order turbine nozzle, it comprises: the framework that comprises the border seal of roof, diapire and pair of sidewalls; And a plurality of cooling perforates with oval or avette sectional shape, it is arranged in each roof, diapire and the pair of sidewalls, and extends through framework vertically; And wherein, the cooling perforate has major axis (major axis) and minor axis (minor axis), and they are arranged such that major axis is roughly parallel to roof and diapire.
Another aspect, the present invention relates to form the method for framework behind the turbine, this back framework is suitable for being connected as interface between combustor transition section and first order turbine nozzle, and this method comprises: the back framework that the border seal that comprises roof, diapire and pair of sidewalls a) is provided; And b) form oval-shaped cooling hole at least one in described roof, diapire and pair of sidewalls, this cooling hole extends through the back framework vertically.
In conjunction with following determined accompanying drawing the present invention is explained in more detail now.
Description of drawings
Fig. 1 is the perspective view of framework after the representative transitions section of known structure;
Fig. 2 shows to be formed on the circular cooling hole known in the framework of back or the enlarged detail of cooling bath; And
Fig. 3 is the enlarged detail that shows the avette or elliptical shape of cooling hole, and this cooling hole will for example adopt in the back framework of type shown in Figure 1.
Embodiment
With reference to Fig. 1, the back framework 10 as interface between the changeover portion (not shown) of routine and first order turbine nozzle (also not shown) correspondingly comprises roof 12 and diapire 14 and pair of sidewalls 16,18, and they finish the framework of border seal.Installation metal construction for example support 20 and 22 is convenient to the back framework is connected to first order turbine nozzle.Definite means for attachment is as part of the present invention, yet, under any circumstance can adopt any suitable attach technology.What recognize is that conventional changeover portion is attached to the opposite side of back framework, and extends between first order nozzle and combustion liner.The example of such layout can be referring to U.S. Patent No. 6,412, and 268 and No.6,547,257.
Referring now to Fig. 2, circular cooling hole 24 is opened around the peripheral intervals of back framework usually, allows cooling air vertically in the ostium and through framework, cooling structure thus later.
Fig. 3 has shown the cooling hole shape of change, and it can provide better and more efficiently cooling to the back framework.Specifically, cooling hole that some or all extend vertically or perforate 26 have oval or avette sectional shape, therefore, for given section area, can provide bigger surface area for effective convection current cooling.Oval cooling hole or cooling perforate 26 can require to determine to use separately or be used in combination with circular cooling hole (for example the hole 24) according to concrete cooling.The size of slotted eye also requires to change according to cooling.In after oval cooling hole 26 can correspondingly be arranged in roof, diapire and sidewall 12,14,16 and 18 of framework any or a plurality of (or whole).Preferred, the major axis of cooling perforate is roughly parallel to the roof and the diapire of back framework.
Although the present invention is considered as the most practical and most preferred embodiment and is described in conjunction with current, but be to be understood that, the present invention is not limited to the disclosed embodiments, but opposite, the present invention is intended to contain various modification and equivalent arrangements included in the spirit and scope of the appended claims.
Claims (10)
1. one kind is suitable for the back framework (10) that is connected as interface between combustor transition section and first order turbine nozzle, comprising:
The framework that comprises the border seal of roof, diapire and pair of sidewalls (12,14,16 and 18); And
A plurality of cooling perforates, it extends through one or more in described roof, diapire and the pair of sidewalls, and described a plurality of cooling perforates (26) have oval or avette sectional shape.
2. back according to claim 1 framework is characterized in that the one or more cooling perforates (26) in described a plurality of cooling perforates (26) are arranged in each described roof, diapire and the pair of sidewalls (12,14,16 and 18).
3. back according to claim 1 framework is characterized in that described a plurality of cooling perforates (26) extend through the framework of described border seal along axial direction.
4. back according to claim 2 framework is characterized in that described a plurality of cooling perforates (26) extend through the framework of described border seal along axial direction.
5. back according to claim 1 framework is characterized in that described a plurality of cooling perforates (26) have major axis and minor axis, and they are arranged to make described major axis to be roughly parallel to described roof and described diapire.
6. back according to claim 4 framework is characterized in that described a plurality of cooling perforates (26) have major axis and minor axis, and they are arranged to make described major axis to be roughly parallel to described roof and described diapire.
7. one kind is suitable for the back framework (10) that is connected as interface between combustor transition section and first order turbine nozzle, comprising:
The framework that comprises the border seal of roof, diapire and pair of sidewalls (12,14,16 and 18); And
Have a plurality of cooling perforates (26) of oval or avette sectional shape, it is arranged in each described roof, diapire and the pair of sidewalls, extends through the framework of described border seal vertically; And
Wherein, described a plurality of cooling perforates (26) have major axis and minor axis, and they are arranged such that described major axis is roughly parallel to described roof and described diapire.
8. the method for framework (10) behind the formation turbine, described back framework (10) are suitable for being connected as interface between combustor transition section and first order turbine nozzle, and described method comprises:
A) provide have roof, the back framework of the border seal of diapire and pair of sidewalls (12,14,16 and 18); And
B) form oval-shaped cooling hole (26) at least one in described roof, diapire and pair of sidewalls, described cooling hole (26) extends through described back framework vertically.
9. method according to claim 8 is characterized in that, described method comprises: described oval-shaped cooling hole (26) is set in all described roof, diapire and pair of sidewalls.
10. method according to claim 8, it is characterized in that, described oval-shaped cooling hole (26) has major axis and minor axis, and wherein, step b) comprises: be arranged to make described major axis to be roughly parallel to described roof and described diapire described oval-shaped cooling hole.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/216078 | 2008-06-30 | ||
| US12/216,078 US20090324387A1 (en) | 2008-06-30 | 2008-06-30 | Aft frame with oval-shaped cooling slots and related method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101619661A true CN101619661A (en) | 2010-01-06 |
Family
ID=41360901
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910159430A Pending CN101619661A (en) | 2008-06-30 | 2009-06-30 | Aft frame with oval-shaped cooling slots and related method |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20090324387A1 (en) |
| JP (1) | JP2010014113A (en) |
| CN (1) | CN101619661A (en) |
| DE (1) | DE102009026015A1 (en) |
| FR (1) | FR2933139A1 (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110162378A1 (en) * | 2010-01-06 | 2011-07-07 | General Electric Company | Tunable transition piece aft frame |
| US9121279B2 (en) * | 2010-10-08 | 2015-09-01 | Alstom Technology Ltd | Tunable transition duct side seals in a gas turbine engine |
| US9255484B2 (en) | 2011-03-16 | 2016-02-09 | General Electric Company | Aft frame and method for cooling aft frame |
| US10113435B2 (en) * | 2011-07-15 | 2018-10-30 | United Technologies Corporation | Coated gas turbine components |
| US9115808B2 (en) * | 2012-02-13 | 2015-08-25 | General Electric Company | Transition piece seal assembly for a turbomachine |
| US9243508B2 (en) | 2012-03-20 | 2016-01-26 | General Electric Company | System and method for recirculating a hot gas flowing through a gas turbine |
| US20140000267A1 (en) * | 2012-06-29 | 2014-01-02 | General Electric Company | Transition duct for a gas turbine |
| JP6619307B2 (en) * | 2016-09-05 | 2019-12-11 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| US10718224B2 (en) * | 2017-10-13 | 2020-07-21 | General Electric Company | AFT frame assembly for gas turbine transition piece |
| US10684016B2 (en) * | 2017-10-13 | 2020-06-16 | General Electric Company | Aft frame assembly for gas turbine transition piece |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3767322A (en) * | 1971-07-30 | 1973-10-23 | Westinghouse Electric Corp | Internal cooling for turbine vanes |
| CN1047905A (en) * | 1989-02-06 | 1990-12-19 | 西屋电气公司 | Gas turbine with air-cooled vanes |
| US5414999A (en) * | 1993-11-05 | 1995-05-16 | General Electric Company | Integral aft frame mount for a gas turbine combustor transition piece |
| US6412268B1 (en) * | 2000-04-06 | 2002-07-02 | General Electric Company | Cooling air recycling for gas turbine transition duct end frame and related method |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4923371A (en) * | 1988-04-01 | 1990-05-08 | General Electric Company | Wall having cooling passage |
| US5233828A (en) * | 1990-11-15 | 1993-08-10 | General Electric Company | Combustor liner with circumferentially angled film cooling holes |
| JPH09119322A (en) * | 1995-10-27 | 1997-05-06 | Ishikawajima Harima Heavy Ind Co Ltd | Cooling liner of aircraft engine |
| JPH09144504A (en) * | 1995-11-22 | 1997-06-03 | Ishikawajima Harima Heavy Ind Co Ltd | Turbine cooling blade and its working method |
| US6287075B1 (en) * | 1997-10-22 | 2001-09-11 | General Electric Company | Spanwise fan diffusion hole airfoil |
| US6186741B1 (en) * | 1999-07-22 | 2001-02-13 | General Electric Company | Airfoil component having internal cooling and method of cooling |
| US6368060B1 (en) * | 2000-05-23 | 2002-04-09 | General Electric Company | Shaped cooling hole for an airfoil |
| US6375425B1 (en) * | 2000-11-06 | 2002-04-23 | General Electric Company | Transpiration cooling in thermal barrier coating |
| US6547257B2 (en) | 2001-05-04 | 2003-04-15 | General Electric Company | Combination transition piece floating cloth seal and stage 1 turbine nozzle flexible sealing element |
| US6743350B2 (en) * | 2002-03-18 | 2004-06-01 | General Electric Company | Apparatus and method for rejuvenating cooling passages within a turbine airfoil |
| US6984100B2 (en) * | 2003-06-30 | 2006-01-10 | General Electric Company | Component and turbine assembly with film cooling |
| US7066716B2 (en) * | 2004-09-15 | 2006-06-27 | General Electric Company | Cooling system for the trailing edges of turbine bucket airfoils |
| JP4381276B2 (en) * | 2004-10-08 | 2009-12-09 | 三菱重工業株式会社 | gas turbine |
| JP4898253B2 (en) * | 2005-03-30 | 2012-03-14 | 三菱重工業株式会社 | High temperature components for gas turbines |
| US7296967B2 (en) * | 2005-09-13 | 2007-11-20 | General Electric Company | Counterflow film cooled wall |
| US7377743B2 (en) * | 2005-12-19 | 2008-05-27 | General Electric Company | Countercooled turbine nozzle |
-
2008
- 2008-06-30 US US12/216,078 patent/US20090324387A1/en not_active Abandoned
-
2009
- 2009-06-17 JP JP2009143807A patent/JP2010014113A/en active Pending
- 2009-06-23 DE DE102009026015A patent/DE102009026015A1/en not_active Withdrawn
- 2009-06-25 FR FR0954340A patent/FR2933139A1/en active Pending
- 2009-06-30 CN CN200910159430A patent/CN101619661A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3767322A (en) * | 1971-07-30 | 1973-10-23 | Westinghouse Electric Corp | Internal cooling for turbine vanes |
| CN1047905A (en) * | 1989-02-06 | 1990-12-19 | 西屋电气公司 | Gas turbine with air-cooled vanes |
| US5414999A (en) * | 1993-11-05 | 1995-05-16 | General Electric Company | Integral aft frame mount for a gas turbine combustor transition piece |
| US6412268B1 (en) * | 2000-04-06 | 2002-07-02 | General Electric Company | Cooling air recycling for gas turbine transition duct end frame and related method |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2010014113A (en) | 2010-01-21 |
| FR2933139A1 (en) | 2010-01-01 |
| US20090324387A1 (en) | 2009-12-31 |
| DE102009026015A1 (en) | 2009-12-31 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20100106 |