Turbines and their components

• US 20030215330A1
• Filed: 01/21/2003
• Published: 11/20/2003
• Est. Priority Date: 01/18/2002
• Status: Active Grant

• Current Assignee: Siemens AG
• Original Assignee: Alstom Limited (Alstom SA)
• Inventors: Haller, Brian Robert
• Granted Patent: US 6,802,695 B2
• Time in Patent Office: Days
• US Class Current: 415/191
• CPC Class Codes: F01D 25/30 Exhaust heads, chambers, or the like
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/142 of the blades of successive rotor or stator blade-rows
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An axial flow gas turbine comprises a turbine and a turbine exhaust section. The turbine comprises a turbine nozzle containing a low pressure turbine stage having an annular row of stator vanes (V2) followed in axial succession by an annular row of rotor blades (B2). The low pressure turbine stage is characterized by the following parameters: the ratio of vane airfoil pitch to vane airfoil axial width (P/W) at the root end of the vane airfoil (V2) is in the region of 1.0 to 1.2, preferably about 1.12; the ratio of blade airfoil pitch to blade airfoil axial width (P/W)at the root end of the blade airfoil (B2) is in the region of 0.6; the ratio of blade diameter at the tip end of the blade airfoil to blade diameter at the root end of the blade airfoil (blade tip/hub diameter ratio) is in the region of 1.6-1.8, preferably about 1.72; and the ratio of the axial length of the exhaust section to the blade airfoil height (L/H) is no greater than a value in the region of 4:1, preferably 3:1. These parameters are subject to a permitted variation of up to ±10%, preferably up to ±5%. Dimensions of example airfoils are given and are scaleable to produce turbines of any chosen power.

Claims

1. An axial flow gas turbine, comprising:

in axial succession, a turbine and a turbine exhaust section, the turbine comprising a turbine nozzle containing a low pressure turbine stage having an annular row of stator vanes followed in axial succession by an annular row of rotor blades, wherein the low pressure turbine stage is characterized by the following parameters;

a ratio of vane airfoil pitch to vane airfoil axial width at a root end of a vane airfoil (P/W) is in a region of 1.0 to 1.2;

a ratio of blade airfoil pitch to blade airfoil axial width at a root end of a blade airfoil (P/W) is in the region of 0.6;

a ratio of blade diameter at a tip end of the blade airfoil to blade diameter at the root end of the blade airfoil is in a region of 1.6-1.8; and

a ratio of a axial length of the exhaust section to the blade airfoil height (L/H) is no greater than a value in a region of 4;

1;

said parameters being subject to a predetermined amount of variation.

2. The gas turbine according to claim 1, wherein the blade airfoils taper so as to have a smaller axial width at their tips than at their root ends.

3. The gas turbine according to claim 1, wherein the vane airfoils taper so as to have a larger axial width at their tips than at their root ends.

4. The gas turbine according to claim 1, wherein said ratio of vane airfoil pitch to vane airfoil axial width at the root end of the vane airfoil (P/W) is about 1.12.

5. The gas turbine according to claim 1, wherein said ratio of blade diameter at the tip end of the blade airfoil to blade diameter at the root end of the blade airfoil is about 1.72.

6. The gas turbine according to claim 1, wherein said ratio of the axial length of the exhaust section to the blade airfoil height (L/H) is about 3:

1.

7. The gas turbine according to claim 1, wherein the blade airfoil configuration is as defined in Tables 1A to 1C, subject to said predetermined level of variation.

8. The gas turbine according to claim 1, wherein the blade airfoil configuration is defined by the application of a scaling factor to the x, y and z values in Tables 1A to 1C to obtain scaled x, y and z values, said scaling factor being chosen to obtain a predetermined power output from the low pressure turbine, the scaled x, y and z values being subject to said predetermined level of variation.

9. The gas turbine according to claim 1, wherein the vane airfoil configuration is as defined in Tables 2A to 2C, subject to said predetermined level of variation.

10. The gas turbine according to claim 1, wherein the vane airfoil configuration is defined by the application of a scaling factor to the x, y and z values defined in Tables 2A to 2C to obtain scaled x, y and z values, said scaling factor being chosen to obtain a predetermined power output from the low pressure turbine, the scaled x, y and z values being subject to said predetermined level of variation.

11. The gas turbine according to claim 1, wherein the blade airfoil'"'"'s configuration and the vane airfoil'"'"'s configuration are defined by the application of a scaling factor to the x, y and z values defined in Tables 1A to 1C and Tables 2A to 2C respectively, thereby to obtain scaled x, y and z values, said scaling factor being chosen to obtain a predetermined power output from the low pressure turbine, the scaled x, y and z values being subject to said predetermined level of variation.

12. The gas turbine according to claim 1, wherein the configuration of said turbine nozzle is as defined in Table 3, subject to said predetermined level of variation.

13. The gas turbine according to claim 11, wherein the shape of said turbine nozzle is as defined in Table 3, and the dimensions of said turbine nozzle are commensurate with the scaled x, y and z values of the blade and vane airfoils.

14. The gas turbine according to claim 1, wherein the configuration of the exhaust section is as defined in Table 4, subject to said predetermined level of variation.

15. The gas turbine according to claim 8, wherein the shape of said exhaust section is as defined in Table 4, and the dimensions of said exhaust section are commensurate with the scaled x, y and z values of the blade airfoil.

20. The gas turbine according to claim 1, wherein said predetermined level of variation is up to ±

10%.

21. The gas turbine according to claim 20, wherein said predetermined level of variation is up to ±

5%.

16. A blade airfoil for a low pressure turbine stage of a gas turbine, the airfoil having cross-sectional profiles at a root, mid-height, and tip as defined in Tables 1A to 1C respectively, subject to a predetermined level of variation.

22. The blade airfoil according to claim 16, wherein said predetermined level of variation is up to ±

10%.

23. The blade airfoil according to claim 22, wherein said predetermined level of variation is up to ±

5%.

17. A blade airfoil for a low pressure turbine stage of a gas turbine, the blade airfoil'"'"'s configuration being defined by the application of a scaling factor to the x, y and z values in Tables 1A to 1C to obtain scaled x, y and z values, said scaling factor being chosen to obtain a predetermined power output from the low pressure turbine, the scaled x, y and z values being subject to said predetermined level of variation.

18. A vane airfoil for a low pressure turbine stage of a gas turbine, the vane having cross-sectional profiles at a root, mid-height, and tip as defined in Tables 2A to 2C respectively, subject to a predetermined level of variation.

24. The vane airfoil according to claim 18, wherein said predetermined level of variation is up to ±

10%.

25. The vane airfoil according to claim 24, wherein said predetermined level of variation is up to ±

5%.

19. A vane airfoil for a low pressure turbine stage of a gas turbine, the vane airfoil'"'"'s configuration being defined by the application of a scaling factor to the x, y and z values in Tables 2A to 2C to obtain scaled x, y and z values, said scaling factor being chosen to obtain a predetermined power output from the low pressure turbine, the scaled x, y and z values being subject to said predetermined level of variation.