US20040115059A1 - Cored steam turbine bucket - Google Patents
Cored steam turbine bucket Download PDFInfo
- Publication number
- US20040115059A1 US20040115059A1 US10/317,190 US31719002A US2004115059A1 US 20040115059 A1 US20040115059 A1 US 20040115059A1 US 31719002 A US31719002 A US 31719002A US 2004115059 A1 US2004115059 A1 US 2004115059A1
- Authority
- US
- United States
- Prior art keywords
- steam turbine
- turbine bucket
- dovetail
- bucket airfoil
- tangential
- 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.)
- Abandoned
Links
- 238000000034 method Methods 0.000 claims abstract description 27
- 238000005495 investment casting Methods 0.000 claims abstract description 16
- 230000008569 process Effects 0.000 claims abstract description 8
- 238000005266 casting Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 230000004044 response Effects 0.000 description 4
- 239000000919 ceramic Substances 0.000 description 3
- 239000000047 product Substances 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 230000001052 transient effect Effects 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- 239000007795 chemical reaction product Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003068 static effect Effects 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
Definitions
- the present invention is directed to the investment casting of steam turbine buckets. More particularly, the present invention provides a method for investment casting lightweight yet structurally sound steam turbine buckets.
- a critical design element of steam turbine design is rotor stresses driven by bucket weight. With the given manufacturing processes, however, it is very difficult to reduce bucket weight without compromising mechanical integrity.
- the present invention proposes a investment casting process for hollow steam turbine buckets, which may also include a lattice-work of crossing channels internal to the airfoil to reduce weight while maintaining mechanical integrity.
- the new structural design uses a robust investment casting, facilitates an integral cover (or bucket shroud) design and provides the potential for steam turbine bucket cooling.
- the lattice-work of channels is placed at opposing angles to create a cris-crossed rib structure internal to the airfoil with good stress distribution.
- a cris-crossed rib structure internal to the airfoil with good stress distribution.
- the lattice-work of channels is formed from a highly connected ceramic core piece, which leads to very high yield rates for investment castings.
- the new structural design results in an airfoil having a lower overall weight, which serves to reduce corresponding rotor structures and overall unit size.
- Advantages of the new structural design include weight reduction and an improved rotor thermal transient response due to reduced weight.
- investment cast procedures facilitate design features such as integral covers.
- inventive process provides the ability to tailor design response by altering internal geometry (lattice density).
- FIG. 1 shows a cut-away section of a steam turbine bucket airfoil to have a lattice-work internal core and with the bucket having a tangential fir-tree dovetail;
- FIG. 2 shows a cut-away section of a steam turbine bucket airfoil to have a lattice-work internal core and with the bucket having a tangential slot dovetail;
- FIG. 3 shows a cut-away section of a steam turbine bucket airfoil to have a lattice-work internal core and with the bucket having an axial entry dovetail;
- FIGS. 1 - 3 show in cut-away section, the use of lattice-works 10 , 20 , 30 that respectively provide high solidity ceramic cores which are much more durable for manufacturing.
- these steam turbine buckets could be formed by investment casting without the lattice-work internal cores so as to be hollow.
- FIG. 1 shows a steam turbine bucket having a tangential fir-tree dovetail 11
- FIG. 2 shows a steam turbine bucket having a tangential slot dovetail 21
- FIG. 3 shows a steam turbine bucket having an axial entry dovetail.
- the range of angles for the lattice work crossing channels or ribs is from 25° to 55° on one wall and then ⁇ 25° to ⁇ 55° on the opposite wall.
- the preferred ratio for size of the channels to the thickness of the ribs is 4:1 to 1:1.
- ribs 0.1 inch would be spaced 0.25 inches apart.
- the investment casting process also provides the opportunity to cast-in design features such as integral covers 12 , 22 , 32 that reduce bucket tip steampath leakage.
- the reduced weight of the cast buckets and associated rotor improve thermal transient response to be more consistent with the static shell structures, improving transient response, maintaining tighter clearances and improved unit performance.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Steam turbine buckets are formed by investment casting to be hollow or to have a lightweight lattice-work internal core. The process is also used to integrally form steam turbine buckets having a variety of dovetail configurations, including a tangential fir-tree dovetail, a tangential slot dovetail and an axial gas turbine style dovetail. The investment casting process can also be used to integrally cast a cover at one end of the steam turbine bucket.
Description
- The present invention is directed to the investment casting of steam turbine buckets. More particularly, the present invention provides a method for investment casting lightweight yet structurally sound steam turbine buckets.
- Current steam turbine buckets are machined from plate stock and as such are solid buckets. This includes steam turbine buckets with traditional tangential fir-tree dovetails, tangential slot dovetails, and axial entry dovetails.
- A critical design element of steam turbine design is rotor stresses driven by bucket weight. With the given manufacturing processes, however, it is very difficult to reduce bucket weight without compromising mechanical integrity.
- The prior art technology for high pressure and intermediate pressure steam turbine rotating bucket airfoils is primarily custom components machined from plate stock. These solid airfoils are necessarily heavy and necessitate significant rotor structures to support them.
- It is desirable to replace the conventionally machined solid buckets with lighter parts manufactured by investment casting without compromising structural integrity. The present invention accomplishes the goal of providing a lightweight yet strong, steam turbine airfoil.
- The present invention proposes a investment casting process for hollow steam turbine buckets, which may also include a lattice-work of crossing channels internal to the airfoil to reduce weight while maintaining mechanical integrity. The new structural design uses a robust investment casting, facilitates an integral cover (or bucket shroud) design and provides the potential for steam turbine bucket cooling.
- The lattice-work of channels is placed at opposing angles to create a cris-crossed rib structure internal to the airfoil with good stress distribution. Preferably, there are no internal main ribs in the design, but could be if mechanical design considerations required such main ribs.
- The lattice-work of channels is formed from a highly connected ceramic core piece, which leads to very high yield rates for investment castings. The new structural design results in an airfoil having a lower overall weight, which serves to reduce corresponding rotor structures and overall unit size.
- Advantages of the new structural design include weight reduction and an improved rotor thermal transient response due to reduced weight. In addition, investment cast procedures facilitate design features such as integral covers. Moreover, the inventive process provides the ability to tailor design response by altering internal geometry (lattice density).
- The use of investment casting provides a high casting yield relative to traditional gas turbine designs. Finally, the use of investment casting provides the potential for steam turbine bucket cooling.
- FIG. 1 shows a cut-away section of a steam turbine bucket airfoil to have a lattice-work internal core and with the bucket having a tangential fir-tree dovetail;
- FIG. 2 shows a cut-away section of a steam turbine bucket airfoil to have a lattice-work internal core and with the bucket having a tangential slot dovetail;
- FIG. 3 shows a cut-away section of a steam turbine bucket airfoil to have a lattice-work internal core and with the bucket having an axial entry dovetail; and
- Due to the custom nature of conventional steam turbine designs, steam turbine buckets are traditionally manufactured from plate stock using flexible machining processes. The present inventors were the first to realize that as steam turbine products become more structured or pre-engineered, as are gas turbine products, the re-use of steam turbine bucket designs made an investment casting manufacturing process more feasible.
- They were also the first to realize that while investment casting provided an opportunity for significant bucket weight reduction, the fragile nature of traditional gas turbine cores with a few internal radial ribs, often lead to a high rate of ceramic core breakage and variability in cast wall thickness. The proposed investment cast process addresses these problems and issues.
- FIGS. 1-3 show in cut-away section, the use of lattice-
works - The lattice-works 10, 20, 30, however, allow greater control of wall thickness in the end product, and improve the mechanical integrity relative to the traditional alternative with large internal cavities. FIG. 1 shows a steam turbine bucket having a tangential fir-
tree dovetail 11, FIG. 2 shows a steam turbine bucket having atangential slot dovetail 21, FIG. 3 shows a steam turbine bucket having an axial entry dovetail. - Preferably, the range of angles for the lattice work crossing channels or ribs is from 25° to 55° on one wall and then −25° to −55° on the opposite wall. The preferred ratio for size of the channels to the thickness of the ribs is 4:1 to 1:1. For example, for the midpoint of the range, ribs 0.1 inch would be spaced 0.25 inches apart.
- The investment casting process also provides the opportunity to cast-in design features such as
integral covers - In a structured steam turbine product line HP and IP buckets will be re-used from unit to unit as steampaths are duplicated. This re-use makes casting tooling and casting buckets as a manufacturing process feasible. Casting opens the opportunity to significantly reduce bucket weight and the associated rotor mass by the use of cores.
- While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (32)
1. A method of forming a steam turbine bucket airfoil by using an investment casting process and forming a hollow steam turbine bucket airfoil.
2. The method as claimed in claim 1 , wherein a cover is integrally cast with the hollow steam turbine bucket airfoil.
3. The method as claimed in claim 1 , wherein the formed hollow steam turbine bucket airfoil is integrally cast with a tangential fir-tree dovetail.
4. The method as claimed in claim 1 , wherein the formed hollow steam turbine bucket airfoil is integrally cast with a tangential slot dovetail.
5. The method as claimed in claim 1 , wherein the formed hollow steam turbine bucket airfoil is integrally cast with an axial entry dovetail.
6. The method as claimed in claim 2 , wherein the formed hollow steam turbine bucket airfoil is integrally cast with a tangential fir-tree dovetail.
7. The method as claimed in claim 2 , wherein the formed hollow steam turbine bucket airfoil is integrally cast with a tangential slot dovetail.
8. The method as claimed in claim 2 , wherein the formed hollow steam turbine bucket airfoil is integrally cast with an axial entry dovetail.
9 A method of forming a steam turbine bucket airfoil, said method comprising utilizing an investment casting process to form an internal core of the steam turbine bucket airfoil having a lattice-work.
10. The method as claimed in claim 9 , wherein a cover is integrally cast with the steam turbine bucket airfoil having a lattice work.
11. The method as claimed in claim 9 , wherein the formed steam turbine bucket airfoil is integrally cast with a tangential fir-tree dovetail.
12. The method as claimed in claim 9 , wherein the formed steam turbine bucket airfoil is integrally cast with a tangential slot dovetail.
13. The method as claimed in claim 9 , wherein the formed steam turbine bucket airfoil is integrally cast with an axial entry dovetail.
14. The method as claimed in claim 10 , wherein the formed steam turbine bucket airfoil is integrally cast with a tangential fir-tree dovetail.
15. The method as claimed in claim 10 , wherein the formed steam turbine bucket airfoil is integrally cast with a tangential slot dovetail.
16. The method as claimed in claim 10 , wherein the formed steam turbine bucket airfoil is integrally cast with an axial entry dovetail.
17. A steam turbine bucket airfoil for use in a steam turbine comprising a lattice-work internal core.
18. The steam turbine bucket airfoil as claimed in claim 17 , further comprising a cover formed at one end.
19. The steam turbine bucket airfoil claimed in claim 17 , further comprising a tangential fir-tree dovetail.
20. The steam turbine bucket airfoil claimed in claim 17 , further comprising a tangential slot dovetail.
21. The steam turbine bucket airfoil claimed in claim 17 , further comprising an axial entry dovetail.
22. The steam turbine bucket airfoil claimed in claim 18 , further comprising a tangential fir-tree dovetail.
23. The steam turbine bucket airfoil claimed in claim 18 , further comprising a tangential slot dovetail.
24. The steam turbine bucket airfoil claimed in claim 18 , further comprising an axial entry dovetail.
25. A steam turbine bucket airfoil for use in a steam turbine comprising a hollow airfoil core.
26. The steam turbine bucket airfoil as claimed in claim 25 , further comprising a cover formed at one end.
27. The steam turbine bucket airfoil claimed in claim 25 , further comprising a tangential fir-tree dovetail.
28. The steam turbine bucket airfoil claimed in claim 25 , further comprising a tangential slot dovetail.
29. The steam turbine bucket airfoil claimed in claim 25 , further comprising an axial entry dovetail.
30. The steam turbine bucket airfoil claimed in claim 26 , further comprising a tangential fir-tree dovetail.
31. The steam turbine bucket airfoil claimed in claim 26 , further comprising a tangential slot dovetail.
32. The steam turbine bucket airfoil claimed in claim 26 , further comprising an axial entry dovetail.
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/317,190 US20040115059A1 (en) | 2002-12-12 | 2002-12-12 | Cored steam turbine bucket |
| DE10358166A DE10358166B4 (en) | 2002-12-12 | 2003-12-10 | Core trained steam turbine blade |
| JP2003412659A JP2004190681A (en) | 2002-12-12 | 2003-12-11 | Cored steam turbine bucket |
| CNB2003101205072A CN1321759C (en) | 2002-12-12 | 2003-12-12 | Steam turbine blade with core |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US10/317,190 US20040115059A1 (en) | 2002-12-12 | 2002-12-12 | Cored steam turbine bucket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US20040115059A1 true US20040115059A1 (en) | 2004-06-17 |
Family
ID=32392949
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US10/317,190 Abandoned US20040115059A1 (en) | 2002-12-12 | 2002-12-12 | Cored steam turbine bucket |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20040115059A1 (en) |
| JP (1) | JP2004190681A (en) |
| CN (1) | CN1321759C (en) |
| DE (1) | DE10358166B4 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1707742A1 (en) * | 2005-03-09 | 2006-10-04 | ABB Turbo Systems AG | Turbine blade with dirt collector |
Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3304052A (en) * | 1965-03-30 | 1967-02-14 | Westinghouse Electric Corp | Rotor structure for an elastic fluid utilizing machine |
| US3306577A (en) * | 1964-08-25 | 1967-02-28 | Sagara Hideo | Turbine device |
| US3762835A (en) * | 1971-07-02 | 1973-10-02 | Gen Electric | Foreign object damage protection for compressor blades and other structures and related methods |
| US3904317A (en) * | 1974-11-27 | 1975-09-09 | Gen Electric | Bucket locking mechanism |
| US4526512A (en) * | 1983-03-28 | 1985-07-02 | General Electric Co. | Cooling flow control device for turbine blades |
| US5286169A (en) * | 1992-12-15 | 1994-02-15 | General Electric Company | Bucket for the next-to-last stage of a steam turbine |
| US5350277A (en) * | 1992-11-20 | 1994-09-27 | General Electric Company | Closed-circuit steam-cooled bucket with integrally cooled shroud for gas turbines and methods of steam-cooling the buckets and shrouds |
| US5429877A (en) * | 1993-10-20 | 1995-07-04 | The United States Of America As Represented By The Secretary Of The Air Force | Internally reinforced hollow titanium alloy components |
| US5584660A (en) * | 1995-04-28 | 1996-12-17 | United Technologies Corporation | Increased impact resistance in hollow airfoils |
| US5660525A (en) * | 1992-10-29 | 1997-08-26 | General Electric Company | Film cooled slotted wall |
| US5752801A (en) * | 1997-02-20 | 1998-05-19 | Westinghouse Electric Corporation | Apparatus for cooling a gas turbine airfoil and method of making same |
| US5947688A (en) * | 1997-12-22 | 1999-09-07 | General Electric Company | Frequency tuned hybrid blade |
| US6000908A (en) * | 1996-11-05 | 1999-12-14 | General Electric Company | Cooling for double-wall structures |
| US6179556B1 (en) * | 1999-06-01 | 2001-01-30 | General Electric Company | Turbine blade tip with offset squealer |
| US6196794B1 (en) * | 1998-04-08 | 2001-03-06 | Honda Giken Kogyo Kabushiki Kaisha | Gas turbine stator vane structure and unit for constituting same |
| US6234755B1 (en) * | 1999-10-04 | 2001-05-22 | General Electric Company | Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture |
| US6257828B1 (en) * | 1997-07-29 | 2001-07-10 | Siemens Aktiengesellschaft | Turbine blade and method of producing a turbine blade |
| US6364001B1 (en) * | 2000-08-15 | 2002-04-02 | Pcc Airfoils, Inc. | Method of casting an article |
| US6382907B1 (en) * | 1998-05-25 | 2002-05-07 | Abb Ab | Component for a gas turbine |
| US6427327B1 (en) * | 2000-11-29 | 2002-08-06 | General Electric Company | Method of modifying cooled turbine components |
| US6637500B2 (en) * | 2001-10-24 | 2003-10-28 | United Technologies Corporation | Cores for use in precision investment casting |
| US6773231B2 (en) * | 2002-06-06 | 2004-08-10 | General Electric Company | Turbine blade core cooling apparatus and method of fabrication |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US3494709A (en) * | 1965-05-27 | 1970-02-10 | United Aircraft Corp | Single crystal metallic part |
| US5002460A (en) * | 1989-10-02 | 1991-03-26 | General Electric Company | Internally cooled airfoil blade |
| US5296308A (en) * | 1992-08-10 | 1994-03-22 | Howmet Corporation | Investment casting using core with integral wall thickness control means |
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| JPH10245658A (en) * | 1997-03-05 | 1998-09-14 | Mitsubishi Heavy Ind Ltd | High cr precision casting material and turbine blade |
| JP3676051B2 (en) * | 1997-09-11 | 2005-07-27 | 三菱重工業株式会社 | Steam turbine blades |
| GB2346340A (en) * | 1999-02-03 | 2000-08-09 | Rolls Royce Plc | A ceramic core, a disposable pattern, a method of making a disposable pattern, a method of making a ceramic shell mould and a method of casting |
| JP2000248901A (en) * | 1999-02-26 | 2000-09-12 | Mitsubishi Heavy Ind Ltd | Hollow blade and its intrinsic vibration number tuning method |
| JP2000297606A (en) * | 1999-04-13 | 2000-10-24 | Hmy Ltd | Manufacturing method for stator blade of steam turbine |
| DE60032824T2 (en) * | 1999-10-26 | 2007-11-08 | Howmet Research Corp., Whitehall | MULTI-WALL CORE AND PROCEDURE |
| EP1127635A1 (en) * | 2000-02-25 | 2001-08-29 | Siemens Aktiengesellschaft | Apparatus and method for casting a workpiece and workpiece |
-
2002
- 2002-12-12 US US10/317,190 patent/US20040115059A1/en not_active Abandoned
-
2003
- 2003-12-10 DE DE10358166A patent/DE10358166B4/en not_active Expired - Fee Related
- 2003-12-11 JP JP2003412659A patent/JP2004190681A/en active Pending
- 2003-12-12 CN CNB2003101205072A patent/CN1321759C/en not_active Expired - Fee Related
Patent Citations (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3306577A (en) * | 1964-08-25 | 1967-02-28 | Sagara Hideo | Turbine device |
| US3304052A (en) * | 1965-03-30 | 1967-02-14 | Westinghouse Electric Corp | Rotor structure for an elastic fluid utilizing machine |
| US3762835A (en) * | 1971-07-02 | 1973-10-02 | Gen Electric | Foreign object damage protection for compressor blades and other structures and related methods |
| US3904317A (en) * | 1974-11-27 | 1975-09-09 | Gen Electric | Bucket locking mechanism |
| US4526512A (en) * | 1983-03-28 | 1985-07-02 | General Electric Co. | Cooling flow control device for turbine blades |
| US5660525A (en) * | 1992-10-29 | 1997-08-26 | General Electric Company | Film cooled slotted wall |
| US5350277A (en) * | 1992-11-20 | 1994-09-27 | General Electric Company | Closed-circuit steam-cooled bucket with integrally cooled shroud for gas turbines and methods of steam-cooling the buckets and shrouds |
| US5286169A (en) * | 1992-12-15 | 1994-02-15 | General Electric Company | Bucket for the next-to-last stage of a steam turbine |
| US5429877A (en) * | 1993-10-20 | 1995-07-04 | The United States Of America As Represented By The Secretary Of The Air Force | Internally reinforced hollow titanium alloy components |
| US5584660A (en) * | 1995-04-28 | 1996-12-17 | United Technologies Corporation | Increased impact resistance in hollow airfoils |
| US6000908A (en) * | 1996-11-05 | 1999-12-14 | General Electric Company | Cooling for double-wall structures |
| US5752801A (en) * | 1997-02-20 | 1998-05-19 | Westinghouse Electric Corporation | Apparatus for cooling a gas turbine airfoil and method of making same |
| US6257828B1 (en) * | 1997-07-29 | 2001-07-10 | Siemens Aktiengesellschaft | Turbine blade and method of producing a turbine blade |
| US5947688A (en) * | 1997-12-22 | 1999-09-07 | General Electric Company | Frequency tuned hybrid blade |
| US6196794B1 (en) * | 1998-04-08 | 2001-03-06 | Honda Giken Kogyo Kabushiki Kaisha | Gas turbine stator vane structure and unit for constituting same |
| US6382907B1 (en) * | 1998-05-25 | 2002-05-07 | Abb Ab | Component for a gas turbine |
| US6179556B1 (en) * | 1999-06-01 | 2001-01-30 | General Electric Company | Turbine blade tip with offset squealer |
| US6234755B1 (en) * | 1999-10-04 | 2001-05-22 | General Electric Company | Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture |
| US6364001B1 (en) * | 2000-08-15 | 2002-04-02 | Pcc Airfoils, Inc. | Method of casting an article |
| US6427327B1 (en) * | 2000-11-29 | 2002-08-06 | General Electric Company | Method of modifying cooled turbine components |
| US6637500B2 (en) * | 2001-10-24 | 2003-10-28 | United Technologies Corporation | Cores for use in precision investment casting |
| US6773231B2 (en) * | 2002-06-06 | 2004-08-10 | General Electric Company | Turbine blade core cooling apparatus and method of fabrication |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1707742A1 (en) * | 2005-03-09 | 2006-10-04 | ABB Turbo Systems AG | Turbine blade with dirt collector |
Also Published As
| Publication number | Publication date |
|---|---|
| DE10358166A1 (en) | 2004-06-24 |
| JP2004190681A (en) | 2004-07-08 |
| CN1321759C (en) | 2007-06-20 |
| DE10358166B4 (en) | 2009-06-10 |
| CN1506181A (en) | 2004-06-23 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:KEHL, RICHARD EUGENE;BUNKER, RONALD SCOTT;REEL/FRAME:013566/0890 Effective date: 20021210 |
|
| STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |