Axial flow gas turbine

• US 8,974,174 B2
• Filed: 11/29/2011
• Issued: 03/10/2015
• Est. Priority Date: 11/29/2010
• Status: Expired due to Fees

• Current Assignee: General Electric Technology GmbH (GE Vernova, Inc.)
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Khanin, Alexander Anatolievich, Kostege, Valery
• Primary Examiner(s): Wiehe, Nathaniel
• Assistant Examiner(s): Lambert, Wayne A
• Application Number:
  US13/306,042
• Publication Number:
  US 20120134785A1
• Time in Patent Office: 1,197 Days
• Field of Search: 415/115, 415/191, 415/177
• US Class Current: 415/115
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 9/00 Stators
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2260/205 Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Abstract

An axial flow gas turbine (35) has a rotor with alternating rows of air-cooled blades (40) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (41) and stator heat shields (47) mounted on inner rings (46A) reduction in cooling air mass flow and an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by adapting the stator heat shields (47) and outer vane platforms (38) within a turbine stage (TS) to one another such that air (37) leaking through the joints between the outer vane platforms (38) and the adjacent stator heat shields (47) into the hot gas path (42) is directed onto the blade crown (32) of the blades (40).

Claims

1. An axial gas turbine comprising:

a rotor with alternating rows of air-cooled blades and rotor heat shields;

a stator with a vane carrier, alternating rows of air-cooled vanes, and stator heat shields mounted on the vane carrier, wherein the stator coaxially surrounds the rotor to define a hot gas path therebetween, such that the rows of blades and stator heat shields, and the rows of vanes and rotor heat shields, are opposite to each other, respectively, and a row of vanes and an adjacent row of blades in the downstream direction define a turbine stage;

a cavity on a backside of each stator heat shield; and

holes at downstream and upstream sides of the stator heat shield;

wherein the stator heat shields within the turbine stage are cooled when cooling air is introduced into the cavity of each stator heat shield, the cooling air being discharged into the hot gas path through the holes of the stator heat shield;

wherein the blades of the turbine stage each comprise a tip and a blade crown on the tip, and the vanes of the turbine stage each comprise an outer vane platform;

wherein the stator heat shields and the outer vane platforms within the turbine stage are adapted to one another such that air leaking through joints between the outer vane platforms and adjacent stator heat shields into the hot gas path is directed onto the blade crowns of the blades;

wherein each of the outer vane platforms comprises a downstream projection at a rear wall, and each of the adjacent stator heat shields comprises a recess, the projection extends downstream to a leading edge of the blade crown of a respective one of the blades and into a respective recess;

a hole and a cavity on the backside of the outer vane platform of each vane, and holes running downstream through said projection;

wherein the vanes within the turbine stage are cooled when introducing cooling air through the hole on the backside of each outer vane platform, and jets of cooling air are directed onto the blade crowns from said cavity on the backside of each stator heat shield by the holes running downstream through said projection of each outer vane platform;

slits running downstream through said projection, the slits being configured and arranged to direct cooling air into an interstice between circumferentially adjacent stator heat shields; and

additional holes at the outer blades platforms configured and arranged to direct cooling air from the cavity on the backside of each of the outer vane platforms downstream onto the blade crowns of the blades below said projections of the outer vane platforms.

2. The axial gas turbine according to claim 1, wherein the outer vane platforms of the vanes are configured such that the cooling air flowing through said holes in said projections have already been used before to cool the respective vanes.

3. The axial gas turbine of claim 1, wherein the holes running downstream through said projection are positioned to bring the cooling air close to the respective one of the blades to a maximum extent.

4. The axial gas turbine of claim 1, wherein the slits are arranged so that cooling air is fed to the slits and the blade crowns through a minimum possible distance.

5. The axial gas turbine of claim 1, wherein the projection of each of the outer vane platforms is positioned such that an end of the projection is close to the respective one of the blades to a maximum extent via the recess receiving that end of the projection.