GB2225063A - Turbine cooling arrangement - Google Patents
Turbine cooling arrangement Download PDFInfo
- Publication number
- GB2225063A GB2225063A GB8923696A GB8923696A GB2225063A GB 2225063 A GB2225063 A GB 2225063A GB 8923696 A GB8923696 A GB 8923696A GB 8923696 A GB8923696 A GB 8923696A GB 2225063 A GB2225063 A GB 2225063A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- insert
- turbine according
- cooling
- outlet nozzle
- 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.)
- Granted
Links
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
1 2225063 h GAS TURBINE HAVING COOLING MEANS This invention relates to a
turbine comprising a stator and a rotor and means for supplying cooling air from the stator to rotor blades secured on the rotor. 5 A turbine of this type is known from DE-OS 18 14 430 which shows devices co-rotating for connection between the cooling chamber and coolant source. This means that there are large rotating masses in the form of rotating form-fitting spacers between the successive rotors. Further, the cooling air flow in the cooling chamber is deflected by means of cooling flow plates and sealing pieces so that several sealing surfaces are supported at the same time on different bodies. This does not guarantee a complete sealing of the cooling air flow because of the various body joints to be bridged.
In addition an apparatus is known from EP-00 43 300 for supplying cooling air for gas turbine rotor blades. Here a flange acting as a covering disc, sealed axially and in form-fitting manner with respect to the rotor wheel, joins the cooling chambers with the cooling air source arranged below or laterally of the blade bases of a rotor. When the cooling air flows in and through between the co-rotating flange or covering disc and the rotor disc the cooling gas is made turbulent and undergoes high friction losses because of, for example, Coriolis effects and the formation of Ekman layers. The pressure drop in the cooling air, which would be convertible into temperature reduction, is thus disadvantageously reduced. Hence the temperature reduction of the cooling air in covering disc systems is disadvantageously greatly restricted.
A direct low-contact supply of the cooling air from the stator to the rotating cooling chambers on the blade base, as is known from DE-OS 19 42 346, requires a gap seal with a large diameter which can be coupled 1 only at great expense to stator-side devices for adapting the gap to the different operational states of an engine.
According to the invention there is provided a turbine comprising a stator and a rotor and means for supplying cooling air from the stator to rotor blades secured on the rotor, wherein on the rotor the air, supply means includes an insert fitted between each blade base and the rotor disc and forming a deflection chamber closed towards the low pressure side of the rotor, while on the high pressure side the or each insert projects radially inwardly towards the hub over the rotor disc edge so as to form an annular air inlet aperture of the deflection chamber, and on the stator the air supply means includes an annular air outlet nozzle directed generally radially outwardly towards the air inlet aperture.
Embodiments of the invention may provide a turbine where only relatively low rotating masses are necessary, a seal- and contact-free low-loss connection is produced between the stator-side cooling air source and the rotor-side cooling chamber, the air crossing a low-pressure region, and a large temperature drop in the cooling air may be brought about. Advantageously, stator-side expenditure is low, and at the same time the number of necessary sealing surfaces in the cooling chamber may be reduced and the need for devices for gap adaptation may be avoided.
With turbines in accordance with the invention the stator-side cooling air source is connected to a stator-side annular air outlet nozzle which produces a substantially radially outwardly directed cooling air stream which forms a homogenous annular cooling air screen. This cooling air screen hits an incident flow surface in the radially outer boundary region of the rotor disc and is deflected towards the annular rotating air inlet aperture which may be formed from hub-side slots in annularly segmented inserts for the cooling chambers.
In order to adapt the flow from the air outlet nozzle, a static component, to the rotating annular segments of the air inlet aperture a circumferential component of velocity may be imparted to this cooling air stream by means of a further device mounted in front of the air outlet nozzle, such as, for example, a swirl nozzle.
Turbines constructed in accordance with the invention have the advantage that a completely contactfree connection is produced between the statorside cooling air source and the rotor-side consumer and no devices of any kind have to be provided for gap adjustment. The rotating masses in the form of solid covering discs or spacers may be restricted to smallvolume inserts in the cooling chambers which have a minimal additional weight if a suitable material is selected.
It is particularly advantageous to construct the insert as a one-piece unit.
In developments of the invention the insert is connected in form-fitting manner with a single annular press and seal fit towards the blade base. This seal fit of the insert guarantees the complete sealing of the cooling air stream in the cooling chamber since.it is supported against a single component and does not have to pass over any body joints.
A preferred embodiment consists in forming the insert with the blade base by soldering, welding, gluing or sintering to form an integral component, thus advantageously achieving a simplified assembly, a smaller number of component pieces and the complete avoidance of sealing surfaces.
By shaping the insert aerodynamically in the region of the cooling air flow the flow is deflected with low loss, regenerating the cooling air pressure, and is conveyed to the cooling ducts in the blades of the rotor. Hence a greater reduction in the temperature of the cooling gas is possible than with the solutions known from the prior art because of the low-loss conveying.
Lossy, for example turbulent, cooling flow components may moreover be separated during transfer from the air outlet nozzle to the air inlet aperture by an incident flow surface, in the boundary region of the rotor disc, i.e. the region nearest the blade base and generally adjacent to the inlet apertures, having a stream incidence at an angle of 200 to 500, preferably 330. This separated leakage flow has the same order of magnitude as the leakage flows of conventional gap seals.
The axial extent of the annular incident flow surface, which is inclined with respect to the turbine axis, is preferably greater than the operationallydetermined axial movements between the stator-side air outlet nozzle and the rotor disc, so that in all operational states, when the cooling air stream has emerged from the air outlet nozzle, it first of all hits the incident flow surface and then is deflected towards the air inlet aperture. This has the advantage that in all operational conditions the air inlet aperture has an optimal air flow towards it.
In order to optimise the air flow separated before the air inlet nozzle, the air inlet aperture is preferably of narrower construction than the air outlet nozzle. This arrangement has the advantage that a low loss pressure accumulation in the cooling chamber insert is achieved.
It is particularly simple to design the insert as a sintered metal body or a cast metal body. Preferably W 9 blade materials based on nickel or cobalt are used as basic materials for the insert so that they display a heat expansion behaviour which matches the blade bases.
A further embodiment of the invention consists in making the inserts preferably from oxide or sintered ceramic materials since these materials keep the rotating masses small by virtue of their low density.
For a better understanding of the invention, embodiments of it will now be described with reference to the accompanying drawings, in which:
Fig. 1 shows schematically in cross section an apparatus in accordance with the invention for supplying cooling gas for gas turbine rotor blades; Fig. 2 is a detail of Fig. 1 showing an insert in a cooling chamber under a blade base; and Fig. 3 shows a front partial view corresponding to Fig. 1.
Fig. 1 shows schematically an apparatus in accordance with the invention having a stator-side annular air outlet nozzle 1 which produces a homogenous contact-free cooling air stream 2 directed generally radially outwardly in the direction of the arrow. A circumferential component is imparted to this cooling air stream 2 by means of a swirl nozzle 3 which is arranged between two disc-like covering plates 4 and 5. The air outlet nozzle 1 directs the cooling air stream 2 into an annular gap 13 between the stator 6 and the rotor 7, where it encounters an incident flow surface 23 in the boundary region of the rotor disc 7. The incident flow surface 23, which is inclined with respect to the normal plane of the turbine axis, deflects the cooling air flow to an air inlet aperture 8 of an insert 9 of a cooling air chamber 10 under the blade base 11 of a blade 22. The insert 9 deflects the cooling air stream 2 after it has entered the air inlet aperture 8 (see arrows) and conveys it to the cooling air ducts 12, 20 and 21 in the blade base 11.
Fig. 2 shows, from the example according to Fig. 1, a cross-section of the insert 9 in the cooling chamber 10. The insert 9 deflects the generally radially directed cooling air flow 2, after it has entered the air inlet aperture 8 of the insert 9 across the annular gap 13 between the stator 6 and the roor disc 7 after deflection by the incident flow surface 23, into the cooling air ducts 12, 20 and 21 of the blade base 11. The cooling air flows through the deflection area 19, shaped for easy flow. The-insert 9 is connected in form-fitting manner to the blade base 11 by a centering projection 14 annularly surrounding the blade base 11 and is sealed in gas-tight manner by the sealing seat 15. The blades and the insert are secured against axial movements by the securing disc 16 and the annular securing insert 17.
Fig. 3 shows a section of a front view of the embodiment according to Fig. 1 showing three blade positions of a rotor disc 7. The associated inserts 9 project over the edge of the rotor disc 7 and form an air inlet aperture 8 which lies substantially radially outwardly opposite the stator-side air outlet nozzle 1. In the annular gap 13 between the air inlet aperture 8 and the air outlet nozzle 1 lies the incident flow surface 23 in the boundary region of the rotor disc 7. Although the air outlet nozzle 1 is shown as contirluous in Fig. 3 it could also consist of a series of segments.
4 !k
Claims (12)
1. A turbine comprising a stator and a rotor and means for supplying cooling air from the stator to rotor blades secured on the rotor, wherein on the rotor the air supply means includes an insert fitted between each blade base and the rotor disc and forming a deflection chamber closed towards the low pressure side of the rotor, while on the high pressure side the or each insert projects radially inwardly towards the hub over the rotor disc edge so as to form an annular air inlet aperture of the deflection chamber, and on the stator the air. supply means includes an annular air outlet nozzle directed generally radially outwardly towards the air inlet aperture.
2. A turbine according to claim 1, wherein the insert is in one piece.
3. A turbine according to claim 1 or 2, wherein the insert is a sintered metal or cast metal body comprising a nickel or cobalt alloy. 20
4. A turbine according to claim 1 to 2, wherein the insert is a sintered body of ceramics.
5. A turbine according to any preceding claim, wherein the insert has a centering projection for the blade base with a single sealing seat between it and the blade base.
6. A turbine according to any preceding claim, wherein the blade base and the insert form an integral component.
7. A turbine according to any preceding claim, wherein the cooling air stream from the air outlet nozzle is directed at an angle of 200 to 500, preferably 330, onto an annular incident flow surface in the region of the rotor disc adjacent to the inlet aperture, for separating turbulent boundary layers of the cooling air stream.
8. A turbine according to claim 7, wherein the 1 1 incident flow surface is inclined with respect to a radial plane and its axial extent is greater than the axial movements which can occur between the stator-side air outlet nozzle and the rotor disc during operation 5 of the turbine.
9. A turbine according to any preceding claim, wherein the annular air inlet aperture has a narrower slot than the air outlet nozzle.
10. A turbine according to any preceding claim, wherein a device for producing a flow component in the circumferential direction is connected in series with the annular air outlet nozzle.
11. A turbine according to any preceding claim, wherein each rotor blade is secured on the rotor in form- and force-fitting manner so as to form, with the rotor, a cooling chamber including the insert and the deflection chamber, the cooling chamber being connected to cooling ducts leading through the blades.
12. A turbine substantially as described herein with reference to the accompanying drawings.
Published 1990 at The Patent Office Stat-eHouse 6C 71 Higli Hc'bcrn. L=dori WCIR 4TP. Further copies maybe obtained from The Patent Office Sales Branch. St Ma:-,- Cray- Orpington. Kent, BFL5 3r%r Printej ty Multiplex techmques ltd- St Mary Cray. Kent. Con 1'87 1 J
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE3835932A DE3835932A1 (en) | 1988-10-21 | 1988-10-21 | DEVICE FOR COOLING AIR SUPPLY FOR GAS TURBINE ROTOR BLADES |
Publications (3)
Publication Number | Publication Date |
---|---|
GB8923696D0 GB8923696D0 (en) | 1989-12-06 |
GB2225063A true GB2225063A (en) | 1990-05-23 |
GB2225063B GB2225063B (en) | 1992-12-02 |
Family
ID=6365646
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB8923696A Expired - Lifetime GB2225063B (en) | 1988-10-21 | 1989-10-20 | Gas turbine having cooling means |
Country Status (4)
Country | Link |
---|---|
DE (1) | DE3835932A1 (en) |
FR (1) | FR2638206B1 (en) |
GB (1) | GB2225063B (en) |
IT (1) | IT1237095B (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0649975A1 (en) * | 1993-10-26 | 1995-04-26 | United Technologies Corporation | Metering of cooling air in turbine blades |
US5440874A (en) * | 1993-07-15 | 1995-08-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbo-engine provided with a device for blowing air onto a rotor element |
JP2002540347A (en) * | 1999-03-29 | 2002-11-26 | シーメンス アクチエンゲゼルシヤフト | Apparatus and method for manufacturing cast gas turbine blade through which coolant flows and distribution chamber of gas turbine blade |
US6933459B2 (en) * | 2003-02-03 | 2005-08-23 | General Electric Company | Methods and apparatus for fabricating a turbine engine blade |
GB2413598A (en) * | 2004-05-01 | 2005-11-02 | Rolls Royce Plc | Providing cooling gas to turbine blade and disc in gas turbine engine |
US6964557B2 (en) * | 2003-02-03 | 2005-11-15 | General Electric Company | Methods and apparatus for coupling a component to a turbine engine blade |
US6974306B2 (en) | 2003-07-28 | 2005-12-13 | Pratt & Whitney Canada Corp. | Blade inlet cooling flow deflector apparatus and method |
US7198466B2 (en) | 2002-11-28 | 2007-04-03 | Rolls-Royce Plc | Blade cooling |
GB2435909A (en) * | 2006-03-07 | 2007-09-12 | Rolls Royce Plc | Turbine blade arrangement |
EP2725191A1 (en) | 2012-10-23 | 2014-04-30 | Alstom Technology Ltd | Gas turbine and turbine blade for such a gas turbine |
CN103922103A (en) * | 2014-04-17 | 2014-07-16 | 中发电气(铜陵)海德精密工业有限公司 | High-bearing-load waterproof carrier roller sealing device |
US9664051B2 (en) | 2011-06-16 | 2017-05-30 | Siemens Aktiengesellschaft | Rotor blade root section with cooling passage and method for supplying cooling fluid to a rotor blade |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2661946B1 (en) * | 1990-05-14 | 1994-06-10 | Alsthom Gec | ACTION TURBINE STAGE WITH REDUCED SECONDARY LOSSES. |
DE4422965A1 (en) * | 1994-06-30 | 1996-01-04 | Mtu Muenchen Gmbh | Device for separating foreign particles from the cooling air to be supplied to the rotor blades of a turbine |
US5511945A (en) * | 1994-10-31 | 1996-04-30 | Solar Turbines Incorporated | Turbine motor and blade interface cooling system |
DE19854908A1 (en) | 1998-11-27 | 2000-05-31 | Rolls Royce Deutschland | Blade and rotor of a turbomachine |
US6272844B1 (en) * | 1999-03-11 | 2001-08-14 | Alm Development, Inc. | Gas turbine engine having a bladed disk |
US6397576B1 (en) | 1999-10-12 | 2002-06-04 | Alm Development, Inc. | Gas turbine engine with exhaust compressor having outlet tap control |
US6363708B1 (en) | 1999-10-12 | 2002-04-02 | Alm Development, Inc. | Gas turbine engine |
US6460324B1 (en) | 1999-10-12 | 2002-10-08 | Alm Development, Inc. | Gas turbine engine |
US6442945B1 (en) | 2000-08-04 | 2002-09-03 | Alm Development, Inc. | Gas turbine engine |
FR2823794B1 (en) | 2001-04-19 | 2003-07-11 | Snecma Moteurs | REPORTED AND COOLED DAWN FOR TURBINE |
US8708652B2 (en) * | 2007-06-27 | 2014-04-29 | United Technologies Corporation | Cover plate for turbine rotor having enclosed pump for cooling air |
CN102713202B (en) | 2009-09-13 | 2015-07-22 | 贫焰公司 | Combustion cavity layouts for fuel staging in trapped vortex combustors |
RU2543100C2 (en) | 2010-11-29 | 2015-02-27 | Альстом Текнолоджи Лтд | Working blade for gas turbine, manufacturing method for such blade and gas turbine with such blade |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1814430A1 (en) * | 1967-12-21 | 1969-07-24 | Gen Electric | Cooling and sealing arrangement for a gas turbine rotor blade |
GB2010404A (en) * | 1977-12-17 | 1979-06-27 | Rolls Royce | Cooling Turbine Rotor Blades |
GB2042643A (en) * | 1979-01-02 | 1980-09-24 | Rolls Royce | Cooled Gas Turbine Engine |
US4666368A (en) * | 1986-05-01 | 1987-05-19 | General Electric Company | Swirl nozzle for a cooling system in gas turbine engines |
GB2189845A (en) * | 1986-04-30 | 1987-11-04 | Gen Electric | Gas turbine cooling air transferring apparatus |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3286461A (en) * | 1965-07-22 | 1966-11-22 | Gen Motors Corp | Turbine starter and cooling |
DE1942346A1 (en) * | 1969-08-20 | 1971-03-04 | Motoren Turbinen Union | Device for sealing the rotor with respect to the stator in a turbine belonging to a gas turbine engine |
GB1350471A (en) * | 1971-05-06 | 1974-04-18 | Secr Defence | Gas turbine engine |
GB1479332A (en) * | 1974-11-06 | 1977-07-13 | Rolls Royce | Means for retaining blades to a disc or like structure |
DE2941866C2 (en) * | 1978-10-26 | 1982-08-19 | Rolls-Royce Ltd., London | Turbine for a gas turbine engine with air-cooled turbine blades |
JPS6056883B2 (en) * | 1979-02-28 | 1985-12-12 | 株式会社東芝 | gas turbine moving blades |
GB2054046A (en) * | 1979-07-12 | 1981-02-11 | Rolls Royce | Cooling turbine rotors |
FR2485632B1 (en) * | 1980-06-30 | 1985-07-05 | Snecma | IMPROVEMENT IN VENTILATION SYSTEMS OF BLADES AND TURBINE DISCS |
-
1988
- 1988-10-21 DE DE3835932A patent/DE3835932A1/en active Granted
-
1989
- 1989-10-13 FR FR8913409A patent/FR2638206B1/en not_active Expired - Fee Related
- 1989-10-18 IT IT02205389A patent/IT1237095B/en active IP Right Grant
- 1989-10-20 GB GB8923696A patent/GB2225063B/en not_active Expired - Lifetime
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1814430A1 (en) * | 1967-12-21 | 1969-07-24 | Gen Electric | Cooling and sealing arrangement for a gas turbine rotor blade |
GB2010404A (en) * | 1977-12-17 | 1979-06-27 | Rolls Royce | Cooling Turbine Rotor Blades |
GB2042643A (en) * | 1979-01-02 | 1980-09-24 | Rolls Royce | Cooled Gas Turbine Engine |
GB2189845A (en) * | 1986-04-30 | 1987-11-04 | Gen Electric | Gas turbine cooling air transferring apparatus |
US4666368A (en) * | 1986-05-01 | 1987-05-19 | General Electric Company | Swirl nozzle for a cooling system in gas turbine engines |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5440874A (en) * | 1993-07-15 | 1995-08-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbo-engine provided with a device for blowing air onto a rotor element |
EP0649975A1 (en) * | 1993-10-26 | 1995-04-26 | United Technologies Corporation | Metering of cooling air in turbine blades |
JP2002540347A (en) * | 1999-03-29 | 2002-11-26 | シーメンス アクチエンゲゼルシヤフト | Apparatus and method for manufacturing cast gas turbine blade through which coolant flows and distribution chamber of gas turbine blade |
US7198466B2 (en) | 2002-11-28 | 2007-04-03 | Rolls-Royce Plc | Blade cooling |
US6933459B2 (en) * | 2003-02-03 | 2005-08-23 | General Electric Company | Methods and apparatus for fabricating a turbine engine blade |
US6964557B2 (en) * | 2003-02-03 | 2005-11-15 | General Electric Company | Methods and apparatus for coupling a component to a turbine engine blade |
US6974306B2 (en) | 2003-07-28 | 2005-12-13 | Pratt & Whitney Canada Corp. | Blade inlet cooling flow deflector apparatus and method |
GB2413598A (en) * | 2004-05-01 | 2005-11-02 | Rolls Royce Plc | Providing cooling gas to turbine blade and disc in gas turbine engine |
GB2435909A (en) * | 2006-03-07 | 2007-09-12 | Rolls Royce Plc | Turbine blade arrangement |
US9664051B2 (en) | 2011-06-16 | 2017-05-30 | Siemens Aktiengesellschaft | Rotor blade root section with cooling passage and method for supplying cooling fluid to a rotor blade |
EP2725191A1 (en) | 2012-10-23 | 2014-04-30 | Alstom Technology Ltd | Gas turbine and turbine blade for such a gas turbine |
US9482094B2 (en) | 2012-10-23 | 2016-11-01 | General Electric Technology Gmbh | Gas turbine and turbine blade for such a gas turbine |
CN103922103A (en) * | 2014-04-17 | 2014-07-16 | 中发电气(铜陵)海德精密工业有限公司 | High-bearing-load waterproof carrier roller sealing device |
Also Published As
Publication number | Publication date |
---|---|
IT8922053A0 (en) | 1989-10-18 |
IT8922053A1 (en) | 1991-04-18 |
DE3835932A1 (en) | 1990-04-26 |
FR2638206A1 (en) | 1990-04-27 |
FR2638206B1 (en) | 1994-07-08 |
IT1237095B (en) | 1993-05-18 |
GB8923696D0 (en) | 1989-12-06 |
GB2225063B (en) | 1992-12-02 |
DE3835932C2 (en) | 1992-04-02 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20001020 |