Thrust efficient turbofan engine

Patent metadata

Field	Value
Publication number	US-10047700-B2
Application number	US-201715450485-A
Country	US
Kind code	B2
Filing date	Mar 6, 2017
Priority date	Mar 15, 2013
Publication date	Aug 14, 2018
Grant date	Aug 14, 2018

Abstract

A disclosed turbofan engine includes a gas generator section for generating a gas stream flow. A speed reduction device is driven by the power turbine. A propulsor section includes a fan driven by the power turbine through the speed reduction device at a second speed lower than the first speed for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The fan includes a tip diameter greater than forty-five (45) inches and an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine for cruise, climb and sea level take-off power conditions.

First claim

What is claimed is:

1. A turbofan engine comprising:
a propulsor section including a fan, the fan having a fan tip diameter greater than 50 inches and less than 160 inches and less than 26 fan blades;
a low speed spool including an inner shaft and a power turbine having a plurality of stages;
a high speed spool including an outer shaft concentric about the inner shaft;
a geared architecture in driving connection between the power turbine and the fan, wherein the geared architecture has a gear ratio greater than 2.3; and
an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of a mass flow rate of air through a bypass flow path, a tip diameter of the fan and a first rotational speed of the power turbine that is less than 0.15 in operation at a sea level takeoff power condition;
wherein the turbofan engine is capable of generating during operation a propulsive thrust between 16,000 lbf and about 120,000 lbf, a mass flow rate of air through the bypass flow path is between 625 lbm/sec and 80,000 lbm/sec and the first rotational speed of the power turbine is between 6200 rpm and 12,500 rpm.

2. The turbofan engine as recited in claim 1 , wherein the EUTP at one of a climb condition and a cruise condition is less than 0.10.

3. The turbofan engine as recited in claim 1 , wherein the EUTP at one of a climb condition and a cruise condition is less than 0.08.

4. The turbofan engine as recited in claim 3 further comprising a gas generator section, the gas generation section including a core flow path portion of the propulsor section, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a part of the power turbine, the gas generator having an overall pressure ratio between entering airflow into the gas generator and exiting gas stream from the gas generator that is between 40 and 80 in operation.

5. The turbofan engine as recited in claim 3 , further comprising a two-stage high pressure turbine, and a ratio between the number of fan blades and the number of stages in the power turbine is between 3.3 and 8.6.

6. The turbofan engine as recited in claim 5 , further comprising a low fan pressure ratio across the fan alone that is less than 1.45 in operation.

7. The turbofan engine as recited in claim 6 , wherein the EUTP in operation at the sea level takeoff power condition is less than 0.10.

8. The turbofan engine as recited in claim 7 , wherein the fan includes less than 20 fan blades, and the fan rotates at a fan tip speed less than 1150 ft/sec in operation.

9. A turbofan engine comprising:
a propulsor section including a fan, the fan having a fan tip diameter greater than 50 inches and less than 160 inches;
a power turbine;

a geared architecture in driving connection between the power turbine and the fan, wherein the geared architecture has a gear ratio greater than 2.3, wherein an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of a mass flow rate of air through a bypass flow path, a tip diameter of the fan and a first rotational speed of the power turbine is less than 0.10 in operation at a cruise condition, wherein the net engine thrust is between 16,000 lbf and 120,000 lbf, the bass flow rate of air through the bypass flow path is between 625 lbm/sec and 80,000 lbm/sec and the first rotational speed of the power turbine is between 6,200 rpm and 12,500 rpm.

10. The turbofan engine as recited in claim 9 , wherein the EUTP at the cruise condition is less than 0.08.

11. The turbofan engine as recited in claim 10 wherein the EUTP at a sea level takeoff power condition is less than 0.15.

12. The turbofan engine as recited in claim 11 , further comprising a low fan pressure ratio across the fan alone that is less than 1.45 in operation.

13. The turbofan engine as recited in claim 12 , wherein the fan rotates at a fan tip speed less than about 1150 ft/sec in operation.

14. The turbofan engine as recited in claim 13 , further comprising a two-stage high pressure turbine, and wherein the fan includes less than 20 fan blades.

15. The turbofan engine as recited in claim 14 , wherein the EUTP at the sea level takeoff power condition is less than 0.10.

16. The turbofan engine as recited in claim 15 , further comprising a gas generator section, the gas generation section including the core flow path portion of the propulsor section, a low pressure compressor, a high pressure compressor, a combustor, the high pressure turbine, and a part of the power turbine, the gas generator having an overall pressure ratio between entering airflow into the gas generator and exiting gas stream from the gas generator that is between 40 and 80 in operation.

17. A turbofan engine comprising:
a propulsor including a fan having a fan tip diameter greater than 50 inches and less than 160 inches and a low pressure ratio across the fan alone that is less than 1.45 in operation;
a power turbine including between three (3) and six (6) stages;
a geared architecture in driving connection with the power turbine and the fan, wherein the geared architecture has a gear ratio greater than 2.3, and wherein an Engine Unit Thrust Parameter (“EUTP”) defined as net engine thrust divided by a product of a mass flow rate of air through a bypass flow path, a tip diameter of the fan and a first rotational speed of the power turbine is less than 0.15 in operation at a sea level takeoff power condition and less than 0.10 in operation at a cruise condition, wherein the net engine thrust is between 16,000 lbf and 120,000 lbf, the bass flow rate of air through the bypass flow path is between 625 lbm/sec and 80,000 lbm/sec and the first rotational speed of the power turbine is between 6,200 rpm and 12,500 rpm.

18. The turbofan engine as recited in claim 17 , wherein the EUTP at a climb condition is less than 0.10.

19. The turbofan engine as recited in claim 18 , wherein the EUTP at the sea level takeoff power condition is less than 0.10.

20. The turbofan engine as recited in claim 19 , further comprising a two-stage high pressure turbine.

21. The turbofan engine as recited in claim 20 , wherein a ratio between the number of fan blades and the number of rotors in the power turbine is between 3.3 and 8.6.

22. The turbofan engine as recited in claim 21 , wherein the EUTP at the sea level takeoff power condition is less than 0.10.

23. The turbofan engine as recited in claim 22 , wherein the EUTP at the cruise condition is less than 0.08.

24. The turbofan engine as recited in claim 23 , wherein the EUTP at the climb condition is less than 0.08.

25. The turbofan engine as recited in claim 24 , wherein the fan includes less than 20 fan blades.

26. The turbofan engine as recited in claim 25 , wherein the fan rotates at a fan tip speed less than 1150 ft/sec in operation.

27. The turbofan engine as recited in claim 25 , further comprising a gas generator section, the gas generation section including the core flow path portion of the propulsor section, a low pressure compressor, a high pressure compressor, a combustor, the high pressure turbine, and a part of the power turbine, the gas generator having an overall pressure ratio between entering airflow into the gas generator and exiting gas stream from the gas generator that is between 40 and 80 in operation.

Assignees

• United Technologies Corp

Inventors

• Sabnis Jayant

Classifications

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F01D15/12

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F04D19/02

  Multi-stage pumps · CPC title

• F04D29/325

  for axial flow fans (blade mountings F04D29/34, blades F04D29/38) · CPC title