Gas turbine of the axial flow type

• US 8,979,482 B2
• Filed: 11/29/2011
• Issued: 03/17/2015
• Est. Priority Date: 11/29/2010
• Status: Expired due to Fees

• Current Assignee: General Electric Technology GmbH (GE Aerospace)
• 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:
  US13/306,025
• Publication Number:
  US 20120134779A1
• Time in Patent Office: 1,204 Days
• Field of Search: 415/115, 415/116, 415/108, 415/191, 415/177, 415/170.1, 415/173.1, 415/173.5, 415/173.6, 415/174.5, 416/96.R, 416/97.R, 416/97.A, 416/96.A
• US Class Current: 415/115
• CPC Class Codes: F01D 11/10 using sealing fluid, e.g. steam
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• 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

In an axial flow gas turbine (30), a reduction in cooling air mass flow and leakage in combination with an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by providing, within a turbine stage (TS), devices (43-48) to direct cooling air that has already been used to cool, especially the airfoils of the vanes (31) of the turbine stage (TS), into a first cavity (41) located between the outer blade platforms (34) and the opposed stator heat shields (36) for protecting the stator heat shields (36) against the hot gas and for cooling the outer blade platforms (34).

Claims

1. An axial flow gas turbine comprising:

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

a stator including 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 wherein a row of vanes and an adjacent row of blades in the downstream direction define a turbine stage;

wherein the blades comprise tips and outer blade platforms at said tips;

at least one first cavity located between at least one of the outer blade platforms and at least one of the opposed stator heat shields;

means within at least one turbine stage for directing cooling air that has already been used to cool into said at least one first cavity, for protecting the stator heat shields against the hot gas and for cooling the outer blade platforms;

the vanes each comprising an outer vane platform;

the means for directing comprising a second cavity for collecting the cooling air which exits the vane airfoil;

the means for directing also comprising means for discharging the collected cooling air radially into said at least one first cavity;

a shoulder separating the second cavity from the rest of the outer vane platform; and

a sealing screen closing off the second cavity.

2. The axial flow gas turbine according to claim 1, wherein the cooling air that has already been used to cool comprises cooling air already used to cool airfoils of the vanes of the turbine stage.

3. The axial flow gas turbine according to claim 1, wherein the outer blade platforms comprise parallel teeth on an outer side of the outer blade platforms extending circumferentially, and said at least one first cavity is bordered by said parallel teeth.

4. The axial flow gas turbine according to claim 1, wherein the discharging means comprises a projection at a rear wall of each outer vane platform which overlaps first teeth of the outer blade platform in the flow direction of outer blade platforms adjacent to the first teeth, and a screen which covers the projection such that a channel for the cooling air is formed between the projection and the screen which ends in a radial slot just above the at least one first cavity.

5. The axial flow gas turbine according to claim 1, further comprising:

a plurality of holes passing through the rear wall of the outer vane platform and are equally circumferentially spaced;

wherein the second cavity and the means for discharging are connected by said plurality of holes.

6. An axial flow as turbine comprising:

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

a stator including 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 wherein a row of vanes and an adjacent row of blades in the downstream direction define a turbine stage;

wherein the blades comprise tips and outer blade platforms at said tips and wherein the vanes comprise outer vane platforms;

at least one first cavity being located between at least one of the outer blade platforms and at least one of the opposed stator heat shields; and

at least one slit being defined by a screen covering a projection at a rear wall of the outer vane platform of at least one of the vanes, each of the at least one slit being configured such that cooling air that has already been used to cool is directable into said at least one first cavity for protecting the stator heat shields against the hot gas and for cooling the outer blade platforms; and

wherein the outer vane platform has a shoulder that partitions off a second cavity from the outer vane platform.

7. The axial flow gas turbine of claim 6, wherein the projection has a honeycomb that is adjacent to a tooth of the outer blade platform that is positioned underneath the projection.

8. The axial flow gas turbine of claim 7, wherein each of the at least one slit is configured to emit a continuous cooling air sheet of cooling air.

9. The axial flow gas turbine of claim 8, wherein the tooth and the cooling air sheet prevents hot gas from passing into the at least one first cavity, the at least one first cavity being located between teeth on an outer side of the blade platform.

10. The axial flow gas turbine of claim 6, wherein the projection is configured to avoid additional cooling air leakages within a joining zone between the vanes and the stator heat shields.

11. The axial flow gas turbine of claim 6, wherein the stator heat shields have gaps through which the cooling air pass for entering into a backside cavity to prevent stator parts from being overheated.

12. The axial flow gas turbine of claim 6, wherein the second cavity is closed off with a sealing screen such that cooling air passes from the second cavity through at least one hole toward the at least one slit.

13. The axial flow gas turbine of claim 12, wherein the projection has a honeycomb that is adjacent to a tooth of the outer blade platform that is positioned underneath the projection.

14. The axial flow gas turbine of claim 13, wherein the stator heat shields have gaps through which the cooling air pass for entering into a backside cavity to prevent stator parts from being overheated.