RELATIONSHIP BETWEEN FAN AND PRIMARY EXHAUST STREAM VELOCITIES IN A GEARED GAS TURBINE ENGINE

• US 20140205438A1
• Filed: 01/21/2013
• Published: 07/24/2014
• Est. Priority Date: 01/21/2013
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Hasel, Karl L.
• Application Number:
  US13/984,579
• Publication Number:
  US 20140205438A1
• Time in Patent Office: Days
• US Class Current: 415/124.1
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2260/4031 as in toothed gearing

Abstract

Please replace the abstract with the following rewritten abstract. No new matter has been added.

An example gas turbine engine includes, among other things, a geared architecture rotatably coupling a fan drive shaft to an engine fan, the geared architecture having a speed reduction ratio that is greater than or equal to 2.4. The gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90.

Claims

6. A gas turbine engine comprising:

a geared architecture rotatably coupling a fan drive shaft to a fan of a gas turbine engine, the geared architecture having a speed reduction ratio that is greater than or equal to 2.4;

a fan stream exhaust of the gas turbine engine; and

a primary stream exhaust of the gas turbine engine, wherein the gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90.

7. The gas turbine engine of claim 6, wherein the engine is configured so that the Exhaust Velocity Ratio is in the range when cruising at 35,000 feet and when operating at a 0.80 Mach number cruise power condition.

8. The gas turbine engine of claim 6, wherein a Fan Pressure Ratio for the engine is less than 1.45 at 35,000 feet and when operating at a 0.80 Mach number cruise power condition.

9. The gas turbine engine of claim 6, wherein a Bypass Ratio of the engine is greater than 8.0.

10. The gas turbine engine of claim 6, wherein the engine is configured so that the Exhaust Velocity Ratio is in the range when the fan stream exhaust velocity is less than 1175 feet per second.

11-15. -15. (canceled)

16. A gas turbine engine comprising:

a geared architecture rotatably coupling a fan drive shaft to a fan of a gas turbine engine, the geared architecture having a speed reduction ratio that is less than or equal to 4.2,

wherein the gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90.

1. A gas turbine engine comprising:

a geared architecture rotatably coupling a fan drive shaft to a fan of a gas turbine engine, the geared architecture having a speed reduction ratio that is greater than or equal to 2.4,

wherein the gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90.

2. The gas turbine engine of claim 1, wherein the engine is configured so that the Exhaust Velocity Ratio is in the range when cruising at 35,000 feet and when operating at a 0.80 Mach number cruise power condition.

3. The gas turbine engine of claim 1, wherein a Fan Pressure Ratio for the engine is less than 1.45 at 35,000 feet and when operating at a 0.80 Mach number cruise power condition.

4. The gas turbine engine of claim 1, wherein a Bypass Ratio of the engine is greater than 8.0.

5. The gas turbine engine of claim 1, wherein the engine is configured so that the Exhaust Velocity Ratio is in the range when the fan stream exhaust velocity is less than 1175 feet per second.

17. The gas turbine engine of claim 16, wherein the engine is configured so that the Exhaust Velocity Ratio is in the range when cruising at 35,000 feet and when operating at a 0.80 Mach number cruise power condition.

18. The gas turbine engine of claim 16, wherein a Fan Pressure Ratio for the engine is less than 1.45 at 35,000 feet and when operating at a 0.80 Mach number cruise power condition.

19. The gas turbine engine of claim 16, wherein a Bypass Ratio of the engine is greater than 8.0.

20. The gas turbine engine of claim 16, wherein the engine is configured so that the Exhaust Velocity Ratio is in the range when the fan stream exhaust velocity is less than 1175 feet per second.

21. The gas turbine engine of claim 16, wherein the speed reduction ratio is greater than or equal to 2.4.

28. The gas turbine engine of claim 1, wherein the speed reduction ratio is less than or equal to 4.2.

22. A gas turbine engine comprising:

a geared architecture rotatably coupling a fan drive shaft to a fan of a gas turbine engine, the geared architecture having a speed reduction ratio that is less than or equal to 4.2;

a fan stream exhaust of the gas turbine engine; and

a primary stream exhaust of the gas turbine engine, wherein the gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to primary stream exhaust velocity, is approximately in a range of 0.75 to 0.90.

23. The gas turbine engine of claim 22, wherein the engine is configured so that the Exhaust Velocity Ratio is in the range when cruising at 35,000 feet and when operating at a 0.80 Mach number cruise power condition.

24. The gas turbine engine of claim 22, wherein a Fan Pressure Ratio for the engine is less than 1.45 at 35,000 feet and when operating at a 0.80 Mach number cruise power condition.

25. The gas turbine engine of claim 22, wherein a Bypass Ratio of the engine is greater than 8.0.

26. The gas turbine engine of claim 22, wherein the engine is configured so that the Exhaust Velocity Ratio is in the range when the fan stream exhaust velocity is less than 1175 feet per second.

27. The gas turbine engine of claim 22, wherein the speed reduction ratio is greater than or equal to 2.4.

28-1. The gas turbine engine of claim 16, wherein the speed reduction ratio is less than or equal to 4.2.