EP1016773B1 - Kühlbare Schaufel für eine Gasturbine - Google Patents
Kühlbare Schaufel für eine Gasturbine Download PDFInfo
- Publication number
- EP1016773B1 EP1016773B1 EP99811183A EP99811183A EP1016773B1 EP 1016773 B1 EP1016773 B1 EP 1016773B1 EP 99811183 A EP99811183 A EP 99811183A EP 99811183 A EP99811183 A EP 99811183A EP 1016773 B1 EP1016773 B1 EP 1016773B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- vane
- blow
- slot
- trailing edge
- 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.)
- Expired - Lifetime
Links
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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
Definitions
- the invention relates to a coolable blade for a gas turbine or the like according to the preamble of claim 1.
- Such a blade is known for example from US 5,498,133, from the the invention goes out. It is essentially made of a blade, a Shovel foot and a shovel root constructed.
- the airfoil has a suction and a pressure-side wall, which has a front and a rear edge connected to each other.
- the walls define the profile shape and include within a cavity that is used for cooling purposes.
- At least one cooling channel is integrated, that of a cooling medium, as a rule of air, is flowed through.
- the cooling medium can escape.
- the blade succeeds basically enough to cool and thus reach the designed life.
- the exhaust openings in the area of the trailing edge are drilled, cast, eroded, etched or otherwise manufactured and enforce the wall section from the cooling channel to the outer surface.
- the cooling medium reduces the wall temperature by thermal conduction and thereby improves the component life.
- the invention seeks to avoid the disadvantages described. She is the one Task, a coolable blade for a gas turbine or the like specify the type mentioned, which has an increased life and with which it succeeds, in particular the mechanical and thermal loads Lower in the trailing edge region of the blade root.
- this is achieved by providing a coolable blade according to the preamble of claim 1, the blade root at least in the area the trailing edge has a concave curved contour and a the exhaust openings is arranged as a blow-out slot on the blade root.
- the exhaust slot extends in the exit plane at the trailing edge in radial Direction at least over the entire area of the blade root and possesses a cross-sectional shape, at least in the exit plane of the contour the blade root so far follows that wall sections with approximately constant Wall thickness arise.
- the objective is pursued, on the one hand the temperature load lower this critical point and thus the wall temperature.
- the adaptation of the contour curve reduces the stress concentration In consequence, notch effect avoided, which otherwise the advantages in connection would annihilate with the reduced temperature.
- the mechanical and thermal loads in the most vulnerable area to reduce and thus increase the service life.
- blow-out slot forms an airfoil associated radial portion having a constant width, in one of the Blade root associated radial section continuously merges, which the Basic shape of an isosceles triangle with concavely curved legs has. In the area of the trailing edge, this results on both sides of the blow-out slot towards a wall section of constant width, starting from the Area of the blade into the critical area of the blade root into it extends continuously. The mechanical load can be optimal in this area be intercepted.
- blow-out slots described above can be in terms of their exact Arrangement and shaping for predetermined stationary operating states of Optimize the gas turbine so that the outside acting on the blade root Tensile stresses through the inside of the blowout slot due to the Temperature gradient caused compressive stresses are largely compensated. The consequence of this is a reduced load on the outer surface of the Shovel root, which is characterized by the corresponding contouring of the lower, radial given inside area.
- blow-out slot in the radial direction towards the top into the area of the blade and down into the area of the blade root extends into it.
- a first variant is the cross-sectional shape of the blow-out slot continuously between the entry level on the cooling channel and the exit plane maintain the surface of the blade tip. This shape allows a maximum Cooling effect and minimizes the mechanical stress concentration in the Area of the blade wall.
- a second option consists in the form of a to provide radially extending longitudinal slot extending in the flow direction of the cooling medium continuously expanded and into the special cross-sectional shape in the exit level passes.
- the radial extension (length) can be constant whereas the width of the slot is continuous with the Slot geometry merges in the exit plane. This variant stands out through a lower consumption of cooling medium and avoids voltage spikes in the entry level at the cooling channel.
- the blow-out slot is in the flow direction the cooling medium extends radially increasing.
- the cooling medium is thus at a preferably acute angle with respect to the horizontal plane blown out and aligned to the main hot gas flow out.
- the contouring of the blade root leads into Connection with the blow-out slot for improved accessibility of the inside of the airfoil formed cavity.
- the cooling blade according to the invention does not can be used only as a stator, but also as a rotor blade. It is also possible the blow-out slot in the radial direction continuously over the entire trailing edge extend and thus a plurality of individual cooling holes in this Replace area. This variant has manufacturing advantages and leads in addition to an ideally uniform expression in the radial direction the cooling air flow at the trailing edge.
- the basic structure of the coolable blade 1 according to the invention gives in particular from FIGS. 1 and 2.
- the blade 1 has an airfoil 10 and a blade root 30, wherein as a transition region between the blade 10 and the blade root 30, a blade root 40 is formed.
- the airfoil 10 is composed of a suction-side wall 12 and a pressure-side Wall 14, each opposite via a front edge 16 and a trailing edge 18 are connected together. Between the suction side Wall 12 and the pressure-side wall 14 thus creates a cavity 20 which is located continuously in the radial direction r from the blade 10 in the blade root 30th extends into it.
- the cavity 20 is traversed by a cooling medium K, which extends over the area supplied to the blade root 30, meandering in the region of the airfoil 10 redirected several times and over exhaust openings in the form of through holes 60 and a blow-out slot 50 is blown out.
- a cooling medium K air is usually used from the compressor stage, not shown here is branched off.
- the blade root 40 has in the region of the trailing edge 18 a concave curved Contour shape on, allowing a continuous transition without bending jump is realized by the airfoil 10 in the blade root 30.
- the blow-out slot 50 is arranged, which is continuously between an entrance plane 56 on the cavity 20 and an exit plane 58 extends at the trailing edge 18.
- the exit plane 58 has a cross-sectional shape that the outer contour the blade 40 follows so far that on both sides towards wall sections 42 arise with approximately constant wall thickness d.
- the blow-out slot 50 goes up into a radial section 52, the has a constant width b in the manner of a longitudinal slot.
- the width b is chosen such that even in this radial section 52 a constant Wanddikke d is preserved.
- the blow-out slot (50) has the basic shape of an isosceles Triangle with concave curved thighs.
- Blade foot 30 Downwards, that is towards a radial section 54, the Blade foot 30 is assigned, deviates the contour of the Ausblasschlitzes 50th back, creating a pear-shaped cross-sectional shape. Around Blade root 40 is achieved here the maximum width B.
- the blowout slot 50 thus covers the entire area of the blade root 40 from and projects into the two adjacent areas of the airfoil 10 and the Shovel foot 30 inside.
- the cross-sectional shape in conjunction with the selected Contour profile of the blade root 40 prevents notch stresses in this critical area while providing effective cooling.
- FIGS. 3 and 4 show two variants of a possible cross-sectional profile between the entrance plane 56 at the cavity 20 and the exit plane 58 at the Trailing edge 18 indicated.
- the first variant according to FIG. 3 has a continuous, constant cross-sectional shape on. It allows a high throughput of cooling medium, so that the cooling effect at the trailing edge 18 can be set to the maximum.
- the variant shown in Fig. 4 has a flow direction of the cooling medium K continuously changing cross section.
- At the entry level 56 is a continuous longitudinal slot of constant width present, extending to the exit plane 58 extended there and reached the pear-shaped cross-sectional shape.
- These Variant has the advantage of lower consumption of cooling medium K.
- Hot gas flow occurs when the blow-out slot 50 between the entrance level 56 and the exit plane 58 extends radially rising, as shown in Fig. 1st is indicated.
- the cooling concept described above is suitable for applications in and blades alike.
- the outer contour of the blade root Approximated course of the cross-sectional geometry of the blow-out slot enables the effective reduction of material stress in particular critical area of the trailing edge, which increases the life of the bucket increase significantly overall.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- Fig. 1
- Schaufel in Schnittdarstellung;
- Fig. 2
- Schaufel gemäß Fig. 1 in einer Ansicht von links, vergrößerte Teilansicht;
- Fig. 3
- Ausblasschlitz in perspektivischer Darstellung;
- Fig. 4
- Ausblasschlitz in perspektivischer Darstellung, Variante zu dem Ausblasschlitz gemäß Fig. 3.
- 1
- Schaufel
- 10
- Schaufelblatt
- 12
- saugseitige Wand
- 14
- druckseitige Wand
- 16
- Vorderkante
- 18
- Hinterkante
- 20
- Hohlraum, Kühlkanal
- 30
- Schaufelfuß
- 40
- Schaufelwurzel
- 42
- Wandabschnitt
- 50
- Ausblasschlitz
- 52
- Radialabschnitt
- 53
- Radialabschnitt
- 54
- Radialabschnitt
- 56
- Eintrittsebene
- 58
- Austrittsebene
- 60
- Bohrung
- b
- Schlitzbreite
- B
- Schlitzbreite
- d
- Wanddicke
- r
- radiale Richtung
- K
- Kühlmedium
Claims (8)
- Kühlbare Schaufel für eine Gasturbine oder dergleichen, mitdadurch gekennzeichnet, dass zumindest im Bereich der Hinterkante (18) die Schaufelwurzel (40) einen konkav gekrümmten Konturverlauf aufweist und dass eine der Ausblasöffnungen als Ausblasschlitz (50) an der Schaufelwurzel (40) angeordnet ist, der sich in der Austrittsebene (58) der Hinterkante (18) in radialer Richtung (r) zumindest über den gesamten Bereich der Schaufelwurzel (40) erstreckt und dessen Querschnittsform zumindest in der Austrittsebene (58) dem Konturverlauf der Schaufelwurzel (40) soweit folgt, dass Wandabschnitte (42) mit angenähert konstanter Wanddicke (d) entstehen.einem Schaufelblatt, das aus einer saugseitigen Wand und einer druckseitigen Wand aufgebaut ist, welche unter Bildung eines Hohlraumes über eine Vorderkante und eine Hinterkante verbunden sind,einem Schaufelfuß,einer Schaufelwurzel als Übergangsbereich zwischen dem Schaufelblatt und dem Schaufelfuß,wenigstens einem Kühlkanal, der im Hohlraum integriert und von einem Kühlmedium durchströmbar ist, sowieAusblasöffnungen für das Kühlmedium, die ausgehend von einer Eintritts ebene am Hohlraum durchgehend zu einer Austrittsebene im Bereich der Hinterkante angeordnet sind,
- Schaufel nach Anspruch 1,
dadurch gekennzeichnet, dass der Ausblasschlitz (50) einen dem Schaufelblatt (10) zugeordneten Radialabschnitt (52) konstanter Breite (b) aufweist und in einen der Schaufelwurzel (40) zugeordneten Radialabschnitt (53) kontinuierlich übergeht, der die Grundform eines gleichschenkligen Dreiecks mit konkavgekrümmten Schenkeln besitzt. - Schaufel nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass der Ausblasschlitz (50) einen bimenförmigen Querschnitt aufweist. - Schaufel nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass der Ausblasschlitz (50) eine in Strömungsrichtung des Kühlmediums (K) konstante Querschnittsform aufweist. - Schaufel nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass der Ausblasschlitz (50) in der Eintrittsebene (56) die Form eines radial verlaufenden Längsschlitzes besitzt und in Strömungsrichtung des Kühlmediums (K) kontinuierlich in die Querschnittsform in der Austrittsebene (58) übergeht. - Schaufel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass der Ausblasschlitz (50) einen Radialabschnitt (54) aufweist, der dem Schaufelfuß (30) zugeordnet ist. - Schaufel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass der Ausblasschlitz (50) in Strömungsrichtung des Kühlmediums (K) radial ansteigend verläuft. - Schaufel nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, dass sich der Ausblasschlitz (50) in radialer Richtung (r) im Wesentlichen durchgehend über die Hinterkante (18) erstreckt.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19860788A DE19860788A1 (de) | 1998-12-30 | 1998-12-30 | Kühlbare Schaufel für eine Gasturbine |
| DE19860788 | 1998-12-30 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1016773A2 EP1016773A2 (de) | 2000-07-05 |
| EP1016773A3 EP1016773A3 (de) | 2003-12-03 |
| EP1016773B1 true EP1016773B1 (de) | 2005-08-03 |
Family
ID=7893161
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP99811183A Expired - Lifetime EP1016773B1 (de) | 1998-12-30 | 1999-12-21 | Kühlbare Schaufel für eine Gasturbine |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP1016773B1 (de) |
| DE (2) | DE19860788A1 (de) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19921644B4 (de) * | 1999-05-10 | 2012-01-05 | Alstom | Kühlbare Schaufel für eine Gasturbine |
| WO2003054356A1 (de) | 2001-12-10 | 2003-07-03 | Alstom Technology Ltd | Thermisch belastetes bauteil |
| DE10295864D2 (de) | 2001-12-14 | 2004-11-04 | Alstom Technology Ltd Baden | Gasturbinenanordnung |
| FR2864990B1 (fr) | 2004-01-14 | 2008-02-22 | Snecma Moteurs | Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine haute-pression |
| US10260355B2 (en) | 2016-03-07 | 2019-04-16 | Honeywell International Inc. | Diverging-converging cooling passage for a turbine blade |
| US10815792B2 (en) | 2019-01-04 | 2020-10-27 | Raytheon Technologies Corporation | Gas turbine engine component with a cooling circuit having a flared base |
| US12158083B2 (en) * | 2021-11-18 | 2024-12-03 | Rtx Corporation | Airfoil with axial cooling slot having diverging ramp |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1605180A (en) * | 1974-05-16 | 1983-01-26 | Lls Royce Ltd | Method for manufacturing a blade for a gas turbine engine |
| US3966357A (en) * | 1974-09-25 | 1976-06-29 | General Electric Company | Blade baffle damper |
| US4236870A (en) * | 1977-12-27 | 1980-12-02 | United Technologies Corporation | Turbine blade |
| GB2189553B (en) * | 1986-04-25 | 1990-05-23 | Rolls Royce | Cooled vane |
| US5498133A (en) | 1995-06-06 | 1996-03-12 | General Electric Company | Pressure regulated film cooling |
| JP3316418B2 (ja) * | 1997-06-12 | 2002-08-19 | 三菱重工業株式会社 | ガスタービン冷却動翼 |
-
1998
- 1998-12-30 DE DE19860788A patent/DE19860788A1/de not_active Withdrawn
-
1999
- 1999-12-21 EP EP99811183A patent/EP1016773B1/de not_active Expired - Lifetime
- 1999-12-21 DE DE59912356T patent/DE59912356D1/de not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| DE59912356D1 (de) | 2005-09-08 |
| EP1016773A2 (de) | 2000-07-05 |
| DE19860788A1 (de) | 2000-07-06 |
| EP1016773A3 (de) | 2003-12-03 |
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