EP1016773A2 - Aube de turbine refroidissable - Google Patents

Aube de turbine refroidissable Download PDF

Info

Publication number: EP1016773A2
Authority: EP; European Patent Office
Prior art keywords: blade; blow; blade root; slot; cooling medium
Prior art date: 1998-12-30
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.): Granted

Application number

EP99811183A

Other languages

German (de)

English (en)

Other versions

EP1016773B1 (fr

EP1016773A3 (fr

Inventor

Alexander Dr. Beeck

Bernhard Dr. Bonhoff

Rainer Conzelmann

Mark Mccarthy

Kenneth Hall

Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)

GE Vernova GmbH

Original Assignee

ABB Alstom Power Switzerland Ltd

Alstom Technology AG

Priority date (The priority date 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 date listed.)

1998-12-30

Filing date

1999-12-21

Publication date

2000-07-05

1999-12-21 Application filed by ABB Alstom Power Switzerland Ltd, Alstom Technology AG filed Critical ABB Alstom Power Switzerland Ltd

2000-07-05 Publication of EP1016773A2 publication Critical patent/EP1016773A2/fr

2003-12-03 Publication of EP1016773A3 publication Critical patent/EP1016773A3/fr

2005-08-03 Application granted granted Critical

2005-08-03 Publication of EP1016773B1 publication Critical patent/EP1016773B1/fr

2019-12-21 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

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 Pat. No. 5,498,133 the invention is based. It is essentially one shovel blade, one Blade base and a blade root built.
the airfoil has one suction-side and a pressure-side wall, which have a front and a rear edge are interconnected.
the walls define the profile shape and enclose within a cavity that is used for cooling purposes.
At least one cooling channel is integrated, which is usually from a cooling medium air is flowing through.
the blade is basically sufficient to cool and thus achieve the designed service life.
the exhaust openings in the area of the rear edge are drilled, cast, eroded, etched or produced in another way and penetrate the wall section from the cooling channel to the outer surface.
the cooling medium reduces the wall temperature through heat conduction and thereby improves component life.
the trailing edge area is particularly critical in this context the blade root, which is often the one that limits lifespan Area of the shovel proves. Despite the reduction in wall temperatures leads to the creation of blow-out openings in the area of the rear edge Increase in stress.
the invention tries to avoid the disadvantages described. You are the Task based on a coolable blade for a gas turbine or the like of the type mentioned at the outset, which has an increased service life and with which it succeeds, in particular the mechanical and thermal loads in the trailing edge area of the blade root.
the blade root at least in the area the trailing edge has a concavely curved contour and one the blow-out openings are arranged as blow-out slots on the blade root.
the outlet slot extends radially in the exit plane at the rear edge Direction at least over the entire area of the blade root and has a cross-sectional shape that at least in the exit plane of the contour the blade root follows so far that wall sections with approximately constant Wall thickness arise.
the objective is pursued, on the one hand, the temperature load this critical point and thus lower the wall temperature.
the stress concentration is reduced by adapting the contour as a result, notch effect avoided, which otherwise combined the advantages would nullify with the reduced temperature.
the mechanical and thermal loads in the particularly endangered area to reduce and thus increase the service life.
blow-out slot fits the airfoil has associated radial section with constant width, which in one of the Radial section associated with the blade root merges continuously, which is the Basic shape of an isosceles triangle with concavely curved legs owns.
the mechanical load can be optimal in this area be intercepted.
blow-out slots described above can be exact Arrangement and shape for given steady-state operating conditions Optimize the gas turbine so that it acts on the outside of the blade root Tension due to the inside of the exhaust slot due to the Pressure gradients caused by temperature gradients are largely compensated for. The consequence of this is a reduced load on the outer surface of the Blade root, through the appropriate contouring of the lower, radial inside area is given.
blow-out slot is in the radial direction upwards into the area of the airfoil and downwards 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 at the cooling channel and the exit level to 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 is the shape of a in the entry level on the cooling channel provide radially extending longitudinal slot, which is in the direction of flow of the cooling medium continuously expanded and in the special cross-sectional shape in passes the exit level.
the radial extension (length) can be constant are kept, whereas the width of the slot is continuously on the Slot geometry in the exit plane merges. This variant stands out due to a lower consumption of cooling medium and avoids voltage peaks in the entrance level at the cooling channel.
the outlet slot is in the direction of flow of the cooling medium increases radially.
the cooling medium is thus at a preferably acute angle with respect to the horizontal plane blown out and aligned with the main hot gas flow.
the contouring of the blade root leads to Connection with the exhaust slot for improved accessibility of the inside of the airfoil formed cavity.
This aspect wins in particular a decisive one when using the gas turbine in regions with high dust pollution Role, because there the cavity is flushed at certain intervals got to.
the cooling blade according to the invention is not can only be used as a stator, but also as a rotor blade. It is also possible the exhaust slot in the radial direction continuously over the entire rear edge to extend and thus a variety of individual cooling holes in this Area to replace. This variant has manufacturing advantages and leads in addition to an ideally uniform appearance when viewed in the radial direction the cooling air flow at the rear edge.
the basic structure of the coolable blade 1 according to the invention results can be seen in particular from FIGS. 1 and 2.
the blade 1 has an airfoil 10 and a blade root 30, with the transition area between the airfoil 10 and the blade root 30 a blade root 40 is formed.
the airfoil 10 consists of a suction side wall 12 and a pressure side Wall 14 constructed, each opposite a front edge 16 and a trailing edge 18 are connected to each other. Between the suction side Wall 12 and the pressure side wall 14 thus creates a cavity 20, which is continuously in the radial direction r from the blade 10 into the blade root 30 extends into it.
the cavity 20 is flowed through by a cooling medium K, which over the area of the blade root 30, meandering in the area of the blade 10 deflected several times and through discharge openings in the form of through holes 60 and a blowout slot 50 is blown out.
a cooling medium K is usually used air that comes from the compressor stage, not shown here is branched off.
the blade root 40 has a concave curve in the area of the rear edge 18 Contour course on, so that a continuous transition without a jump in curvature is realized by the blade 10 in the blade root 30.
the blowout slot 50 is arranged, which is continuously between an entry level 56 on the cavity 20 and an exit level 58 extends at the rear edge 18.
the area of the blade root 40 it has a cross-sectional shape in the exit plane 58 which corresponds to the outer contour the blade 40 follows so far that wall sections on both sides 42 with approximately constant wall thickness d.
the blow-out slot 50 merges upwards into a radial section 52 which has a constant width b in the manner of a longitudinal slot.
the width is b chosen such that a constant wall thickness is also present in this radial section 52 d remains.
the blowout slot 50 has the basic shape of an isosceles Triangles with concave legs.
the blowout slot 50 thus covers the entire area of the blade root 40 and protrudes into the two adjacent areas of the airfoil 10 and the Blade root 30 into it.
the cross-sectional shape in connection with the chosen one Contour course of the blade root 40 prevents notch stresses in it critical area and at the same time enables effective cooling.
3 and 4 are two variants of a possible cross-sectional profile between the entrance plane 56 on the cavity 20 and the exit plane 58 on the Trailing edge 18 indicated.
the first variant according to FIG. 3 has a continuous, constant cross-sectional shape on. It enables a high throughput of cooling medium, so that the cooling effect on the rear edge 18 can be adjusted to a maximum.
the variant shown in Fig. 4 has one in the flow direction of the cooling medium K continuously changing cross section.
At entry level 56 is a continuous longitudinal slot of constant width available, which extends to the exit plane 58 expanded and reached there the pear-shaped cross-sectional shape.
This Variant has the advantage of lower cooling medium K consumption.
Hot gas flow occurs when the blow-out slot 50 is between the entry level 56 and the exit plane 58 extends radially as shown in FIG. 1 is indicated.
the cooling concept described above is suitable for applications in control and blades equally well.
the outer contour of the blade root approximate 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, increasing the lifespan of the bucket can be increased significantly overall.

Landscapes

Engineering & Computer Science (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Turbine Rotor Nozzle Sealing (AREA)

EP99811183A 1998-12-30 1999-12-21 Aube de turbine refroidissable Expired - Lifetime EP1016773B1 (fr)

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 true EP1016773A2 (fr)	2000-07-05
EP1016773A3 EP1016773A3 (fr)	2003-12-03
EP1016773B1 EP1016773B1 (fr)	2005-08-03

Family

ID=7893161

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP99811183A Expired - Lifetime EP1016773B1 (fr)	1998-12-30	1999-12-21	Aube de turbine refroidissable

Country Status (2)

Country	Link
EP (1)	EP1016773B1 (fr)
DE (2)	DE19860788A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
FR2864990A1 (fr) *	2004-01-14	2005-07-15	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
EP3677750A1 (fr) *	2019-01-04	2020-07-08	United Technologies Corporation	Composant de moteur à turbine à gaz avec une fente de décharge sur le bord de fuite
US20230151737A1 (en) *	2021-11-18	2023-05-18	Raytheon Technologies Corporation	Airfoil with axial cooling slot having diverging ramp

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
DE19921644B4 (de)	1999-05-10	2012-01-05	Alstom	Kühlbare Schaufel für eine Gasturbine
AU2002342500A1 (en)	2001-12-10	2003-07-09	Alstom Technology Ltd	Thermally loaded component
WO2003052240A2 (fr)	2001-12-14	2003-06-26	Alstom Technology Ltd	Systeme de turbine a gaz

Citations (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US5498133A (en)	1995-06-06	1996-03-12	General Electric Company	Pressure regulated film cooling

Family Cites Families (5)

* Cited by examiner, † Cited by third party
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
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/fr not_active Expired - Lifetime
- 1999-12-21 DE DE59912356T patent/DE59912356D1/de not_active Expired - Lifetime

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US5498133A (en)	1995-06-06	1996-03-12	General Electric Company	Pressure regulated film cooling

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
FR2864990A1 (fr) *	2004-01-14	2005-07-15	Snecma Moteurs	Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine haute-pression
EP1555390A1 (fr) *	2004-01-14	2005-07-20	Snecma Moteurs	Fentes d'évacuation de l'air de refroidissement d'aubes de turbine
US7278827B2 (en)	2004-01-14	2007-10-09	Snecma Moteurs	Cooling air evacuation slots of turbine blades
US10260355B2 (en)	2016-03-07	2019-04-16	Honeywell International Inc.	Diverging-converging cooling passage for a turbine blade
EP3677750A1 (fr) *	2019-01-04	2020-07-08	United Technologies Corporation	Composant de moteur à turbine à gaz avec une fente de décharge sur le bord de fuite
US10815792B2 (en)	2019-01-04	2020-10-27	Raytheon Technologies Corporation	Gas turbine engine component with a cooling circuit having a flared base
US20230151737A1 (en) *	2021-11-18	2023-05-18	Raytheon Technologies Corporation	Airfoil with axial cooling slot having diverging ramp
EP4183981A1 (fr) *	2021-11-18	2023-05-24	Raytheon Technologies Corporation	Aube, moteur à turbine à gaz et noyeu de moulage de précision
US12158083B2 (en)	2021-11-18	2024-12-03	Rtx Corporation	Airfoil with axial cooling slot having diverging ramp

Also Published As

Publication number	Publication date
EP1016773B1 (fr)	2005-08-03
DE59912356D1 (de)	2005-09-08
DE19860788A1 (de)	2000-07-06
EP1016773A3 (fr)	2003-12-03

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