Stator blade for a gas turbine and gas turbine having same

• US 8,801,366 B2
• Filed: 09/28/2010
• Issued: 08/12/2014
• Est. Priority Date: 03/28/2008
• Status: Expired due to Fees

• Current Assignee: Ansaldo Energia IP UK Limited (Ansaldo Energia SPA)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Naik, Shailendra, Schnieder, Martin, Dueckershoff, Roland
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): YOUNGER, SEAN JERRARD
• Application Number:
  US12/892,423
• Publication Number:
  US 20110103932A1
• Time in Patent Office: 1,414 Days
• Field of Search: 415/115, 415/116
• US Class Current: 415/115
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2220/3215 the last stage of the turbine
• CPC Class Codes: F05D 2250/185 serpentine-like
• CPC Class Codes: F05D 2260/2212 by creating turbulence
• CPC Class Codes: F05D 2260/22141 using fins or ribs
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A stator blade for a gas turbine with sequential combustion, has a blade airfoil which extends in the radial direction between a blade tip and a shroud, with cooling passages extending inside the blade airfoil, through which a cooling medium can flow for cooling the blade and can then discharge from the stator blade into the hot gas flow flowing through the turbine. The blade airfoil has a sharply curved shape in space in the radial direction, and three cooling passages, which extend in the radial direction, arranged inside the blade airfoil in series in the hot gas flow direction and are interconnected by deflection regions, which are arranged at ends of the blade airfoil, so that the cooling medium flows through the cooling passages one after the other, with change of direction. The cooling passages follow the curvature of the blade airfoil in space in the radial direction.

Claims

1. A stator blade for a gas turbine, the stator blade having a blade airfoil extending in a radial direction between a blade tip and a shroud, with cooling passages extending inside the blade airfoil, through which a cooling medium flows for cooling the stator blade and then discharges from the stator blade into a hot gas flow which flows through the turbine, the blade airfoil having a sharply curved shape in space in the radial direction, a plurality of cooling passages, which extend in the radial direction, are arranged inside the blade airfoil, in series, in the hot gas flow direction and deflection regions, which are arranged at ends of the blade airfoil, are interconnected so that the cooling medium flows through the cooling passages one after the other, with change of direction, the cooling passages follow a curvature of the blade airfoil in space in the radial direction, wherein an entry of a first cooling passage, via a cooling air inlet which extends through a shroud, is in communication with an outer space which lies above the shroud, and the first cooling passage is connected to a start of a second cooling passage by a first deflection region, and a cross-sectional area at an entry of the second cooling passage is larger than a cross-sectional area at an outlet of the first cooling passage, and a throttling element, for throttling a mass flow of cooling medium which flows through the cooling air inlet, is arranged in a region of the cooling air inlet, the throttling element having the form of a plate which is provided with at least one opening, the throttling element closes off the entry of the cooling air inlet and is soldered into the shroud, wherein a ratio of the cross-sectional area at the entry of the second cooling passage to the cross-sectional area at the outlet of the first cooling passage is about 1.6 and wherein an end of the second cooling passage is connected to a start of a third cooling passage by a second deflection region, a throttling device, for the controlled extraction of cooling medium for the cooling of an outer platform and of a part of a trailing edge, is provided in the second deflection region, a cross-sectional area at an entry of the third cooling passage is smaller than a cross-sectional area at an outlet of the second cooling passage and cross-sectional areas of the three cooling passages halfway up the stator blade are in a ratio of 1:

2;

1.

2. The stator blade as claimed in claim 1, wherein inside the blade airfoil there are at least two cooling passages which extend in the radial direction.

3. The stator blade as claimed in claim 1, wherein a ratio of the cross-sectional area at the entry of the third cooling passage to the cross-sectional area at the outlet of the second cooling passage is about 0.9.

4. The stator blade as claimed in claim 1, wherein the throttling device comprises a plurality of ribs which are oriented transversely to a throughput direction.

5. The stator blade as claimed in claim 1, wherein an arc-shaped deflection element, which extends from the end of the first cooling passage to the start of the second cooling passage, is arranged in the first deflection region, the deflection element divides the cross-sectional area at the outlet of the first cooling passage and the cross-sectional area at the entry of the second cooling passage in each case into two sub-areas of about 33% and 66% of the overall area.

6. The stator blade as claimed in claim 1, wherein two arc-shaped deflection elements, which extend between the middle of the second deflection region and the start of the third cooling passage, are arranged in the second deflection region, the deflection elements divide a cross-sectional area of a middle of the second deflection region into three sub-areas of about 33% of the overall area in each case, and divide the cross-sectional area at the entry of the third cooling passage into three sub-areas of about 36%, 36% and 28% of the overall area.

7. The stator blade as claimed in claim 1, wherein the blade airfoil extends from a leading edge to a trailing edge in a flow direction of the hot gas flow, the blade airfoil has a pressure side and a suction side, on the pressure side, in front of the trailing edge, a cooling slot extends parallel to the trailing edge through which the cooling medium is able to discharge from the third cooling passage over the entire length of the stator blade and is able to cool the trailing edge of the stator blade.

8. The stator blade as claimed in claim 7, wherein the cooling slot comprises control elements, distributed in a longitudinal direction thereof, for adjusting cooling medium flow through the cooling slot.

9. The stator blade as claimed in claim 1, wherein the third cooling passage has a cross-sectional area which reduces in the radial direction, outside inwards, and wherein a rate of reduction of the cross-sectional area from the outside inwards is lower over the first 70% of the passage length than over the last 30%.

10. The stator blade as claimed in claim 1, wherein turbulator ribs are arranged in the cooling passages for improving a cooling effect.

11. The stator blade as claimed in claim 10, wherein the turbulator ribs are arranged obliquely to a flow direction in the cooling passages.

12. The stator blade as claimed in claim 10, wherein the first cooling passage has a triangular cross section which tapers towards a leading edge, the second cooling passage has a rectangular cross section, and the third cooling passage has a triangular cross section which tapers towards a trailing edge, and wherein the turbulator ribs in the first and third cooling passages become flatter towards the leading edge or trailing edge, respectively, the turbulator ribs in the second cooling passage having a constant height.

13. The stator blade as claimed in claim 7, wherein the cooling slot comprises cams distributed over a surface of the slot to improve heat transfer.

14. A gas turbine with a stator blade having a blade airfoil extending in a radial direction between a blade tip and a shroud, with cooling passages extending inside the blade airfoil, through which a cooling medium flows for cooling the stator blade and then discharges from the stator blade into a hot gas flow which flows through the turbine, the blade airfoil having a sharply curved shape in space in the radial direction, a plurality of cooling passages, which extend in the radial direction, are arranged inside the blade airfoil, in series, in the hot gas flow direction and deflection regions, which are arranged at ends of the blade airfoil, are interconnected so that the cooling medium flows through the cooling passages one after the other, with change of direction, the cooling passages follow a curvature of the blade airfoil in space in the radial direction, an entry of a first cooling passage, via a cooling air inlet which extends through the shroud, is in communication with an outer space which lies above the shroud, and the first cooling passage is connected to a start of a second cooling passage by a first deflection region, and a cross-sectional area at an entry of the second cooling passage is larger than a cross-sectional area at an outlet of the first cooling passage, and a throttling element, for throttling a mass flow of cooling medium which flows through the cooling air inlet, is arranged in a region of the cooling air inlet, the throttling element having the form of a plate which is provided with at least one opening, the throttling element closes off the entry of the cooling air inlet and is soldered into the shroud, wherein the gas turbine functions with sequential combustion and has two combustion chambers in series in a flow direction, with a subsequent turbine in each case, the stator blade is arranged in the second turbine, wherein a ratio of the cross-sectional area at the entry of the second cooling passage to the cross-sectional area at the outlet of the first cooling passage is about 1.6 and wherein an end of the second cooling passage is connected to a start of a third cooling passage by a second deflection region, a throttling device, for the controlled extraction of cooling medium for the cooling of an outer platform and of a part of a trailing edge, is provided in the second deflection region, a cross-sectional area at an entry of the third cooling passage is smaller than a cross-sectional area at an outlet of the second cooling passage and cross-sectional areas of the three cooling passages halfway up the stator blade are in a ratio of 1:

2;

1.

15. The gas turbine as claimed in claim 14, wherein the second turbine comprises a plurality of rows of stator blades and rotor blades in series in the flow direction, the stator blade is arranged in a middle stator blade row between two rotor blades.