Turbofan engine with reduced noise

• US 5,791,138 A
• Filed: 01/11/1996
• Issued: 08/11/1998
• Est. Priority Date: 01/11/1996
• Status: Expired due to Fees

• Current Assignee: Burbank Aeronautical Corporation II
• Original Assignee: Burbank Aeronautical Corporation II
• Inventors: Phillips, Edward J., Matthews, Eugene James, Lillibridge, Robert W., McGuire, Kenneth R.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US08/584,342
• Time in Patent Office: 943 Days
• Field of Search: 60/39.29, 60/39.33, 60/226.1, 60/262, 60/725, 181/213, 181/220, 415/118, 415/119
• US Class Current: 60/262
• CPC Class Codes: F02C 7/045 having provisions for noise suppression
• CPC Class Codes: F02C 7/24 Heat or noise insulation air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00
• CPC Class Codes: F02K 1/386 mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
• CPC Class Codes: F02K 1/48 Corrugated nozzles
• CPC Class Codes: F02K 1/60 by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2220/327 to drive shrouded, high solidity propeller
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A noise reduction kit for modifying a two (2) spool axial flow turbofan engine with multi-stage compressors and fan driven by multi-stage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level. There is a fan at the upstream end of the core engine for generating axial fan air flow through bypass ducts terminating at a common nozzle, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches. A material layer is located in a spacing between a tip of blades for at least some of the fans and a duct for the fans, thereby to reduce a normal clearance between the tip of blades for the fan and the duct. Mixing means for radially diverting fan air and permitting radially outward expansion of exhaust gas is provided coaxially downstream to the core engine. An acoustically dampened light bulb-shaped nose cone is provided for coaxial attachment to an upstream end of the core engine. There is an inlet pressure sensing probe housed in an inlet bullet forwardly of the fans. Alternatively, there is an inlet pressure sensing probe housed at a location of an inlet guide vane forwardly of the fans, the probe being shaped for aerodynamic location in the inlet guide vane. The axial flow front fan is axially separated from the inlet guide vane is extended relatively forwardly.

Claims

1. A noise-reduced turbofan engine comprising:

a) a core engine having axial flow fans, multi-stage compressors and multi-stage reaction turbines and a thrust of at least about 18,000 lbs. at sea level, the fans being at an upstream end of the core engine for generating axial fan air flow;

b) bypass ducts for receiving at least portion of the axial fan air flow from the fans, the ducts terminating at a common nozzle located at the outlet for exhaust gas from the engine, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches; and

c) a material layer located in a spacing between a tip of blades for at least some of the fans and a duct for the fans, thereby to reduce a normal clearance between the tip of blades for the fan and the duct.

2. An engine as claimed in claim 1 wherein the layer is located about the inside wall of the duct.

3. An engine as claimed in claim 1 wherein the layer is located about the inside wall of the duct to a thickness of between about 0.80 to about 0.90 of an inch.

4. An engine as claimed in claim 2 wherein the layer is located about the inside wall of the duct to a thickness of between about 0.050 to about 0.090 of an inch.

9. An engine as claimed in claim 1 including an inlet pressure sensing probe housed at a location of an inlet guide vane forwardly of the fans, the probe being located in the inlet guide vane.

10. An engine as claimed in claim 1 including an inlet pressure sensing probe housed in an inlet bullet forwardly of the fans.

11. An engine as claimed in claim 10 wherein the inlet bullet centerbody has a length of about 36 to about 40", and has a lead end being shaped to be substantially hemispherical.

13. An engine as claimed in claim 1 wherein there are two fans relatively spaced from each other and the axial flow front fan is axially separated by an amount equal approximately to the axial depth of the blades of the fans and wherein an inlet guide vane for the fans is extended relatively forwardly.

5. A noise-reduced turbofan engine comprising:

a) a core engine having axial flow fans, multi-stage compressors and multi-stage reaction turbines and a thrust of at least about 18,000 lbs. at sea level, the fans being at an upstream end of the core engine for generating axial fan air flow;

b) bypass ducts for receiving at least portion of the axial fan air flow from the fans, the ducts terminating at a common nozzle located at the outlet for exhaust gas from the engine, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches; and

c) an inlet pressure sensing probe housed in an inlet bullet forwardly of the fans.

12. An engine as claimed in claim 5 including an inlet cowling with a relatively increased diameter inlet cowling, and having a length of about 42" to about 52".

6. A noise-reduced turbofan engine comprising:

a) a core engine having axial flow fans, multi-stage compressors and multi-stage reaction turbines and a thrust of at least about 18,000 lbs. at sea level, the fans being at an upstream end of the core engine for generating axial fan air flow;

b) bypass ducts for receiving at least portion of the axial fan air flow from the fans, the ducts terminating at a common nozzle located at the outlet for exhaust gas from the engine, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches; and

c) an inlet pressure sensing probe housed at a location of an inlet guide vane forwardly of the fans, the probe being located in the inlet guide vane.

7. An engine as claimed in claim 6 wherein an aerodynamic shape includes a width relatively narrower than a length of the probe, the width being determined in a direction transverse the air flow and the length in a direction longitudinal to the air flow.

8. A noise-reduced turbofan engine comprising:

a) a core engine having axial flow fans, multi-stage compressors and multi-stage reaction turbines and a thrust of at least about 18,000 lbs. at sea level, the fans being at an upstream end of the core engine for generating axial fan air flow;

b) bypass ducts for receiving at least portion of the axial fan air flow from the fans, the ducts terminating at a common nozzle located at the outlet for exhaust gas from the engine, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches; and

c) a material layer located about the inside wall of the duct in a spacing between a tip of blades for at least some of the fans and a duct for the fans, thereby to reduce a normal clearance between the tip of blades for the fan and the duct, the thickness of the layer being between about 0.050 to about 0.090 of an inch.

14. A noise-reduced turbofan engine comprising:

a) a core engine having axial flow fans, multistage compressors and multistage reaction turbines, and a thrust of at least about 18,000 lbs. at sea level, the fans being at an upstream end of the core engine for generating axial fan air flow;

b) bypass ducts for receiving at least portion of the axial fan air flow from the fans, the ducts terminating at a common nozzle located at the outlet for exhaust gas from the engine, the common nozzle having a mixing plane area for each of the fan air flow and for the exhaust gas in a range between 700 and 800 square inches;

c) a mixer in the common nozzle disposed axially to receive and exhaust the exhaust gas and fan air, said mixer having an upstream end and an annular mixer wall axially extending downstream therefrom, the wall being formed into a plurality of circumferentially alternating radially inward and radially outward lobes, the radially inward lobes defining cold chutes for radially inwardly diverting fan air and outward lobes defining hot chutes for permitting radially outward expansion of exhaust gas; and

d) a material layer located in a spacing between a tip of blades for at least some of the fans and a duct for the fans, thereby to reduce a normal clearance between the tip of blades for the fan and the duct.

15. An engine as claimed in claim 14 including an inlet pressure sensing probe housed in an inlet bullet forwardly of the fans.

16. An engine as claimed in claim 14 including an inlet pressure sensing probe housed at a location of an inlet guide vane forwardly of the fans, the probe being located in the inlet guide vane.

17. An engine as claimed in claim 14 wherein the mixing plane area for the cold air is in the range of about 750 to 780 square inches, and about 752 square inches, and the plane area for the hot air is about 725 to 760 square inches, and preferably about 727 square inches.

18. An engine as claimed in claim 14 including an acoustically dampened nose cone for coaxial attachment to an upstream end of the core engine, the nose cone having a lead end being shaped to be substantially hemispherical.

19. An engine as claimed in claim 14 wherein there are two fans relatively spaced from each other and the axial flow front fan is axially separated by an amount equal approximately to the axial depth of the blades of the fans and wherein an inlet guide vane for the front fan is extended about 3" to about 5" relatively forward.