EP3018290B1 - Gas turbine blade - Google Patents
Gas turbine blade Download PDFInfo
- Publication number
- EP3018290B1 EP3018290B1 EP15190456.2A EP15190456A EP3018290B1 EP 3018290 B1 EP3018290 B1 EP 3018290B1 EP 15190456 A EP15190456 A EP 15190456A EP 3018290 B1 EP3018290 B1 EP 3018290B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- groove
- gas turbine
- trailing edge
- turbine blade
- 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.)
- Active
Links
- 230000035882 stress Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 230000008646 thermal stress 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving 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
- 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 invention relates to a gas turbine blade in accordance with the preamble of claim 1.
- a gas turbine blade is described in US 6,390,775 B1 .
- the said gas turbine blade comprises a blade platform having a blade trailing edge side, a blade convex side, a blade concave side and a blade leading edge side.
- a blade profile portion is connected to the blade platform.
- a groove is formed in the blade trailing edge side of the blade platform, wherein the groove runs form the blade concave side to the blade trailing edge side.
- Such grooves are normally called an "undercut". The said groove begins on the blade concave side und exits on the blade trailing edge side.
- the groove runs along a straight line and is at an angle of 90 degrees with respect to a mean camber line of a trailing edge of the blade profile portion.
- the said groove results in a reduced mechanical and thermal stress condition in a root trailing edge of the blade profile portion and a higher stressed condition in the groove. This is possible because the groove is located in a region of cooler metal temperature having greater material fatigue strength.
- Such a gas turbine blade is also described in US 2012/251331 A1 . In view of this, it is in particular the object of the invention to propose a gas turbine blade with very high thermal and mechanical load capacities. This object is satisfied in accordance with the invention by a gas turbine blade having the features of claim 1.
- the gas turbine blade comprises a blade platform having a blade trailing edge side, a blade convex side, a blade concave side and a blade leading edge side.
- a blade profile portion is connected to the blade platform.
- a groove is formed in the blade trailing edge side of the blade platform, wherein the groove runs form the blade concave side to the blade trailing edge side.
- the groove comprises a first portion which is curved with respect to a mean camber line of a trailing edge of the blade profile portion. This leads advantageously to a very effective transfer of stress to the groove and so to a very low trailing edge stress.
- the first portion of the groove in particular runs in a plane parallel to the surface of the blade platform. But it is also possible that the groove is inclined to said surface. Often the groove comprises not only the first portion, but also a second and perhaps a third portion. But it's also possible that the groove consists only of the first portion.
- the first portion of the groove runs along a circular arc.
- the radius of the circular arc in particular is between5 and 20 mm. This leads to a particularly low trailing edge stress.
- the groove comprises a second portion which runs from the blade convex side to the blade concave side of the blade platform.
- the second portion of the groove in particular is straight and has a constant depth between 2 and 15 mm.
- the combination of the first and second portion of the groove leads to a particularly low trailing edge stress. It's also possible that the second portion of the groove is curved.
- the second portion of the groove in particular has a constant height between 4 and 10 mm.
- the second portion of the groove in particular runs in the same plane as the first portion of the groove. It's also possible that there is an third, intermediate section which connects the first and the second portion of the groove.
- An inner part of the groove has for example a substantially round or elliptical cross-section
- an outer part of the groove has for example a rectangular cross-section, whereby the outer and inner part of the groove merge into each other.
- other forms of cross sections are also possible.
- a gas turbine blade 10 comprises a blade platform 11 having a blade trailing edge side 12, a blade convex side 13 (not visible in Fig. 1 , see Fig. 2 ), a blade concave side 14 and a blade leading edge side 15.
- a blade profile portion 16 is connected to the blade platform 11.
- the sides of the blade platform 11 are labeled according to their position relative to the blade profile portion 16.
- a groove 17 is provided in the blade platform 11, such that the groove runs from the blade concave side 14 to the blade convex side 13.
- the groove 17 runs in a plane parallel to a surface 18 (see also Fig. 2 ) of the blade platform 11.
- the groove 17 (indicated as a dotted line) comprises a first portion 19 and a second portion 20.
- the first portion of the groove 19 begins at the blade concave side 14 and runs along a circular arc, so it is curved with respect to a mean camber line 21 of a trailing edge 22 of the blade profile portion 16.
- the said circular arc has a radius R (see Fig. 3 ).
- the radius R is for example between 5 and 20 mm.
- the first portion of the groove 19 merges into the second portion of the groove 20 which ends at the blade convex side 13.
- the second portion of the groove 20 runs in the same plane as the first portion of the groove 19. It has a depth t (see Fig. 3 or 4 ) which lies for example between 2 and 15 mm.
- the second portion of the groove 20 has a cross-section which comprises an inner part 23 with a round cross-section and an outer part 24 with a rectangular cross section. It's also possible that the inner part of the cross section of the second portion of the groove has an elliptical cross section.
- the second portion of the groove 20 has a height h in the direction of the blade profile portion 16) which lies for example between 4 and 10 mm.
- the first portion of the groove 19 has similar cross sections, whereby different cross sections has different depths. The different depths are caused by different outer parts of the groove.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- The invention relates to a gas turbine blade in accordance with the preamble of claim 1.
A gas turbine blade is described inUS 6,390,775 B1 . The said gas turbine blade comprises a blade platform having a blade trailing edge side, a blade convex side, a blade concave side and a blade leading edge side. A blade profile portion is connected to the blade platform. A groove is formed in the blade trailing edge side of the blade platform, wherein the groove runs form the blade concave side to the blade trailing edge side. Such grooves are normally called an "undercut". The said groove begins on the blade concave side und exits on the blade trailing edge side. The groove runs along a straight line and is at an angle of 90 degrees with respect to a mean camber line of a trailing edge of the blade profile portion. The said groove results in a reduced mechanical and thermal stress condition in a root trailing edge of the blade profile portion and a higher stressed condition in the groove. This is possible because the groove is located in a region of cooler metal temperature having greater material fatigue strength.
Such a gas turbine blade is also described inUS 2012/251331 A1 .
In view of this, it is in particular the object of the invention to propose a gas turbine blade with very high thermal and mechanical load capacities. This object is satisfied in accordance with the invention by a gas turbine blade having the features of claim 1.
The gas turbine blade comprises a blade platform having a blade trailing edge side, a blade convex side, a blade concave side and a blade leading edge side. A blade profile portion is connected to the blade platform. A groove is formed in the blade trailing edge side of the blade platform, wherein the groove runs form the blade concave side to the blade trailing edge side. In accordance with the invention, the groove comprises a first portion which is curved with respect to a mean camber line of a trailing edge of the blade profile portion. This leads advantageously to a very effective transfer of stress to the groove and so to a very low trailing edge stress. - The first portion of the groove in particular runs in a plane parallel to the surface of the blade platform. But it is also possible that the groove is inclined to said surface. Often the groove comprises not only the first portion, but also a second and perhaps a third portion. But it's also possible that the groove consists only of the first portion.
- In an aspect of the invention, the first portion of the groove runs along a circular arc. The radius of the circular arc in particular is between5 and 20 mm. This leads to a particularly low trailing edge stress.
- In an aspect of the invention, the groove comprises a second portion which runs from the blade convex side to the blade concave side of the blade platform. The second portion of the groove in particular is straight and has a constant depth between 2 and 15 mm. The combination of the first and second portion of the groove leads to a particularly low trailing edge stress. It's also possible that the second portion of the groove is curved.
- The second portion of the groove in particular has a constant height between 4 and 10 mm.
- The second portion of the groove in particular runs in the same plane as the first portion of the groove. It's also possible that there is an third, intermediate section which connects the first and the second portion of the groove.
- An inner part of the groove has for example a substantially round or elliptical cross-section, an outer part of the groove has for example a rectangular cross-section, whereby the outer and inner part of the groove merge into each other. But other forms of cross sections are also possible.
- Further advantages, features and details of the invention result with reference to the following description of embodiments and with reference to the drawings in which elements which are the same or have the same function are provided with identical reference numerals.
- There are shown:
- Fig. 1
- a side view of a gas turbine blade from a concave side of the turbine blade,
- Fig. 2
- a top view of the turbine blade of
Fig. 1 , - Fig. 3
- a part of a sectional view of the turbine blade of
Fig. 2 and - Fig. 4
- a cross-section of a groove of the turbine blade of
Fig. 1 . - In accordance with
Fig. 1 , agas turbine blade 10 comprises ablade platform 11 having a blade trailingedge side 12, a blade convex side 13 (not visible inFig. 1 , seeFig. 2 ), a bladeconcave side 14 and a blade leadingedge side 15. Ablade profile portion 16 is connected to theblade platform 11. The sides of theblade platform 11 are labeled according to their position relative to theblade profile portion 16. Agroove 17 is provided in theblade platform 11, such that the groove runs from the bladeconcave side 14 to the blade convexside 13. Thegroove 17 runs in a plane parallel to a surface 18 (see alsoFig. 2 ) of theblade platform 11. - In accordance with
Fig. 2 the groove 17 (indicated as a dotted line) comprises afirst portion 19 and asecond portion 20. The first portion of thegroove 19 begins at the bladeconcave side 14 and runs along a circular arc, so it is curved with respect to amean camber line 21 of atrailing edge 22 of theblade profile portion 16. The said circular arc has a radius R (seeFig. 3 ). The radius R is for example between 5 and 20 mm. - The first portion of the
groove 19 merges into the second portion of thegroove 20 which ends at the blade convexside 13. The second portion of thegroove 20 runs in the same plane as the first portion of thegroove 19. It has a depth t (seeFig. 3 or 4 ) which lies for example between 2 and 15 mm. - In accordance with
Fig. 4 , the second portion of thegroove 20 has a cross-section which comprises aninner part 23 with a round cross-section and anouter part 24 with a rectangular cross section. It's also possible that the inner part of the cross section of the second portion of the groove has an elliptical cross section. - The second portion of the
groove 20 has a height h in the direction of the blade profile portion 16) which lies for example between 4 and 10 mm. - The first portion of the
groove 19 has similar cross sections, whereby different cross sections has different depths. The different depths are caused by different outer parts of the groove.
Claims (6)
- A gas turbine blade comprising:- a blade platform (11) havinga blade trailing edge side (12),a blade convex side (13),a blade concave side (14) anda blade leading edge side (15);- a blade profile portion (16) connected to the blade platform (11) at a surface (18);- a groove (17) formed in the blade trailing edge side (12) as well as the blade concave side (14) of the blade platform (11),characterized in that the groove (17) comprises a first portion (19) forming an arc, wherein the arc begins at the blade concave side (14) on a first side of a mean camber line (21) of a trailing edge (22) of the blade profile portion (16), and curves in a plane beneath the surface (18) to the blade trailing edge side (12) on a second side of the mean camber line.
- A gas turbine blade in accordance with claim 1, characterized in that the first portion forms a circular arc.
- A gas turbine blade in accordance with claim 2, characterized in that the circular arc has a radius R between 5 and 20 mm.
- A gas turbine blade in accordance with claims 1 to 3, characterized in that the groove (17) comprises a second portion (20) which runs from the blade convex side (13) to the blade concave side (14) of the blade platform (11).
- A gas turbine blade in accordance with claim 4, characterized in that the second portion of the groove (20) has a depth t between 2 and 15 mm.
- A gas turbine blade in accordance with claim 5, characterized in that the second portion of the groove (20) has a height h between 4 and 10 mm.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP15190456.2A EP3018290B1 (en) | 2014-11-05 | 2015-10-19 | Gas turbine blade |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14191932 | 2014-11-05 | ||
EP15190456.2A EP3018290B1 (en) | 2014-11-05 | 2015-10-19 | Gas turbine blade |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3018290A1 EP3018290A1 (en) | 2016-05-11 |
EP3018290B1 true EP3018290B1 (en) | 2019-02-06 |
Family
ID=51846553
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15190456.2A Active EP3018290B1 (en) | 2014-11-05 | 2015-10-19 | Gas turbine blade |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP3018290B1 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP7406920B2 (en) * | 2019-03-20 | 2023-12-28 | 三菱重工業株式会社 | Turbine blades and gas turbines |
FR3097262B1 (en) * | 2019-06-14 | 2023-03-31 | Safran Aircraft Engines Pi Aji | TURBOMACHINE BLADE WITH OPTIMIZED HEEL AND METHOD FOR OPTIMIZING A BLADE PROFILE |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6390775B1 (en) | 2000-12-27 | 2002-05-21 | General Electric Company | Gas turbine blade with platform undercut |
US7594799B2 (en) * | 2006-09-13 | 2009-09-29 | General Electric Company | Undercut fillet radius for blade dovetails |
US8550783B2 (en) * | 2011-04-01 | 2013-10-08 | Alstom Technology Ltd. | Turbine blade platform undercut |
-
2015
- 2015-10-19 EP EP15190456.2A patent/EP3018290B1/en active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
EP3018290A1 (en) | 2016-05-11 |
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