High performance convergent divergent nozzle

Patent metadata

Field	Value
Publication number	US-10550704-B2
Application number	US-201414911889-A
Country	US
Kind code	B2
Filing date	Aug 22, 2014
Priority date	Aug 23, 2013
Publication date	Feb 4, 2020
Grant date	Feb 4, 2020

Abstract

A turbofan engine includes a fan section. A core engine section drives the fan section. An outer nacelle surrounds the fan section and defines a radially outer surface of a fan duct. An inner nacelle surrounds the core engine section and defines a radially inner surface of the fan duct. A nozzle is disposed at a terminal end of the outer nacelle that defines an exit area for bypass air flow through the fan duct. The nozzle includes a convergent portion forward of a divergent portion and a turning angle for the divergent portion greater than about 12 degrees. A nacelle assembly and method are also disclosed.

First claim

What is claimed is:

1. A turbofan engine comprising;
an outer nacelle defining a radially outer surface of a fan duct;
an inner nacelle defining a radially inner surface of the fan duct; and
a fixed nozzle disposed at a terminal end of the outer nacelle that defines an exit area for bypass air flow through the fan duct, wherein the fixed nozzle includes a fixed convergent portion forward of a fixed divergent portion and a fixed turning angle for the fixed divergent portion being greater than 12 degrees, the fixed convergent portion extends to a transition point and the divergent portion begins at the transition point and extends uninterrupted to a terminal end of the outer nacelle at the fixed turning angle for the entire distance between the transition point and the terminal end of the outer nacelle, wherein a throat area is defined between the radially outer surface and the radially inner surface at the transition point and the fixed divergent portion defines the exit area between the radially outer surface and the radially inner surface at the terminal end of the outer nacelle and a ratio of the exit area relative to the throat area is less than 1.0025.

2. The turbofan engine as recited in claim 1 , wherein the throat area is an annular region at the transition point and the exit area is an annular region defined at the terminal end.

3. The turbofan engine as recited in claim 1 , wherein a throat radius is a distance between the outer radial surface and an outer surface of the outer nacelle, the throat radius being between 3.25 and 4.00 inches.

4. The turbofan engine as recited in claim 1 , wherein the fixed turning angle is between 15 and 25 degrees.

5. The turbofan engine as recited in claim 1 , wherein the fixed turning angle is between 18 and 20 degrees.

6. The turbofan engine as recited in claim 1 , wherein a core engine section is disposed within the inner nacelle and includes a geared architecture for driving a fan section.

7. A nacelle assembly for a turbofan engine comprising;
an outer nacelle defining a radially outer surface of a fan duct;
an inner nacelle defining a radially inner surface of the fan duct; and
a fixed nozzle disposed at a terminal end of the outer nacelle that defines a fixed exit area for bypass air flow through the fan duct, wherein the fixed nozzle includes a fixed convergent portion forward of a fixed divergent portion and a fixed turning angle for the divergent portion being greater than 12 degrees, the fixed convergent portion extends to a transition point and the fixed divergent portion extends uninterrupted aft from the transition point to a terminal end of the outer nacelle at the fixed turning angle for the entire distance between the transition point and the terminal end of the outer nacelle, wherein a fixed throat area at the transition point between the radially outer surface and the radially inner surface of the fan duct and the fixed divergent portion defines the fixed exit area between the radially outer surface and the radially inner surface at the terminal end of the outer nacelle and a ratio of the fixed exit area relative to the throat area is less than 1.0025.

8. The nacelle assembly as recited in claim 7 , wherein the throat area is an annular region defined at the transition point between the fixed convergent portion and the fixed divergent portion and the exit area is an annular region defined at the terminal end.

9. The nacelle assembly as recited in claim 8 , including a throat radius defined at the transition point between the radially outer surface and the outer surface of the outer nacelle that is between 3.25 and 4.00 inches.

10. The nacelle assembly as recited in claim 7 , wherein the fixed turning angle is between 15 and 25 degrees.

11. The nacelle assembly as recited in claim 7 , wherein the fixed turning angle is between 18 and 20 degrees.

12. A method of controlling airflow exiting a fan duct comprising:
defining a fixed throat area at an end of a fixed convergent portion of a fixed nozzle and an exit area at a terminal end of a fixed divergent portion of the fixed nozzle, wherein a ratio of the exit area to the throat area is less than 1.0025, wherein the fixed throat area is disposed between surfaces of an outer nacelle and an inner nacelle; and
defining a fixed turning angle for the fixed divergent portion of the fixed nozzle to be greater than 12 degrees such that airflow along the fixed divergent portion separates to provide an effective reduction in an exit area without movement of the fixed divergent portion, wherein the fixed divergent portion begins at the end of the fixed convergent portion and extends uninterrupted at the fixed turning angle to the terminal end of the outer nacelle.

13. The method as recited in claim 12 , including the step of defining a throat radius between an outer surface and an inner surface of an outer nacelle at transition point between the fixed convergent portion and the fixed divergent portion to be between 3.25 and 4.00 inches.

14. The method as recited in claim 12 , including defining the fixed turning angle to be between 18 and 20 degrees.

Assignees

• United Technologies Corp

Inventors

• Murphy Michael Joseph
• Petrenko Oleg

Classifications

• F02K1/78

  Other construction of jet pipes · CPC title

• F01D9/02 Primary

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F02C7/36

  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 title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title