Nacelle anti ice system

• US 10,450,955 B2
• Filed: 07/06/2016
• Issued: 10/22/2019
• Est. Priority Date: 07/06/2016
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Goodman, Robert, Zheng, Zhijun, Greenberg, Michael D.
• Primary Examiner(s): Sosnowski, David E
• Assistant Examiner(s): Wolcott, Brian P
• Application Number:
  US15/202,758
• Publication Number:
  US 20180010519A1
• Time in Patent Office: 1,203 Days
• CPC Class Codes: B64D 15/04 Hot gas application
• CPC Class Codes: B64D 2033/0233 comprising de-icing means
• CPC Class Codes: B64D 2033/0286 for turbofan engines
• CPC Class Codes: B64D 33/02 of combustion air intakes air intakes for gas-turbine plants or jet-propulsion plants per se F02C7/04; air intakes for combustion engines in general F02M35/00
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components
• CPC Class Codes: F01D 25/02 De-icing means for engines having icing phenomena
• CPC Class Codes: F01D 25/08 Cooling of machines or engines in general F01P; Heating; Heat-insulation of blade-carrying members, of blades F01D5/00
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• CPC Class Codes: F02C 9/16 Control of working fluid flow F02C9/48 takes precedence; control of air-intake flow F02C7/057
• CPC Class Codes: F05D 2220/32 in gas turbines

Abstract

An anti-icing system of a nacelle inlet of an engine of an aircraft includes first and second direct acting valves and first and second control valve assemblies fluidly connected to the nacelle inlet. The first direct acting valve includes a first inlet, outlet, valve chamber, and piston. The first piston is positioned in the first direct acting valve. The first control valve assembly is fluidly connected to the first valve. The second direct acting valve includes a second inlet, outlet, valve chamber, and piston. The second piston is positioned in the second direct acting valve. The second direct acting valve is fluidly connected to the first direct acting valve in a series configuration. The second control valve assembly is fluidly connected to the second valve chamber.

Claims

1. An anti-icing system of a nacelle inlet of an engine of an aircraft, wherein the anti-icing system comprises:

a valve assembly fluidly connected to the nacelle inlet, wherein the valve assembly comprises;

a first direct acting valve comprising;

a first inlet;

a first valve chamber fluidly connected to the first inlet;

a first internal valve body circumferentially surrounding the first valve chamber, the first internal valve body having a first axial face;

a first outlet; and

a first piston for adjusting a rate of flow of air through the first direct acting valve, wherein the first piston is slidably engaged with the first internal valve body;

a first control valve assembly fluidly connected to the first valve chamber of the first direct acting valve;

a second direct acting valve comprising;

a second inlet;

a second valve chamber fluidly connected to the second inlet;

a second internal valve body circumferentially surrounding the second valve chamber;

a second outlet; and

a second piston for adjusting a rate of flow of air through the second direct acting valve, wherein the second piston is slidably engaged with the second internal valve body, and further wherein the second direct acting valve is fluidly connected to the first direct acting valve in a series configuration such that the second inlet of the second direct acting valve is directly connected to the first outlet of the first direct acting valve; and

a second control valve assembly fluidly connected to the second valve chamber of the second direct acting valve;

a first lip element disposed on an upstream end of the first piston, the first lip element for sealing engagement with first internal valve body of the first direct acting valve, wherein a first axial face of the first lip element extends at an angle θ

_LIP between a first plane extending in an axial direction and the first axial face of the first lip element; and

wherein the first axial face of the first internal valve body extends at an angle θ

_VB between a second plane extending in an axial direction and the first axial face of the first internal valve body, further wherein an expansion angle θ

_EXP equivalent to the difference between angle θ

_LIP and angle θ

_VB comprises an angle from 15°

to 60°

.

2. The anti-icing system of claim 1, wherein the first and second control valve assemblies are electrically connected to a full authority digital engine control of the aircraft.

3. The anti-icing system of claim 1, wherein the first control valve assembly comprises:

a first solenoid valve comprising;

a first ball element;

a first plunger attached to or in contact with the first ball element; and

a first solenoid surrounding the first plunger, the first solenoid for creating a magnetic field to interact with the first plunger; and

a first pintle valve comprising;

a first pintle housing;

a first pintle disposed in the first pintle housing;

a first threadably adjustable biasing element for biasing the first pintle valve, wherein the first pintle valve is directly fluidly connected to the first solenoid valve, and wherein both of the first solenoid valve and the first pintle valve of the first control valve assembly are fluidly connected to the first valve chamber of the first direct acting valve.

4. The anti-icing system of claim 1, wherein the second control valve assembly comprises:

a second solenoid valve comprising;

a second ball element;

a second plunger attached to the second ball element; and

a second solenoid surrounding the second plunger, the second solenoid for creating a magnetic field to interact with the second plunger; and

a second pintle valve comprising;

a second pintle housing;

a second pintle disposed in the second pintle housing;

a second threadably adjustable biasing element for biasing the second pintle valve, wherein the second pintle valve is directly fluidly connected to the second solenoid valve, and wherein both of the second solenoid valve and the second pintle valve of the second control valve assembly are fluidly connected to the second valve chamber of the second direct acting valve.

5. The anti-icing system of claim 1 further comprising:

a first lock mechanism positioned in the first valve chamber of the first direct acting valve, the first locking mechanism for locking the first piston in a fully open position; and

a second lock mechanism positioned in the second valve chamber of the second direct acting valve, the second locking mechanism for locking the second piston in a fully open position.

6. The anti-icing system of claim 1 further comprising:

a second lip element disposed on an upstream end of the second piston, the second lip element for sealing engagement with second internal valve body of the second direct acting valve, wherein a second axial face of the second lip element extends at an angle θ

_LIP between a first plane extending in an axial direction and the second axial face of the second lip element; and

a second axial face of the second internal valve body, wherein the second axial face of the second internal valve body extends at an angle θ

_VB between a second plane extending in an axial direction and the second axial face of the second internal valve body, further wherein an expansion angle θ

_EXP equivalent to the difference between angle θ

_LIP and angle θ

_VB comprises an angle from 15°

to 60°

.

7. An anti-icing system of a nacelle inlet of an engine of an aircraft, wherein the anti-icing system comprises:

a valve assembly fluidly connected to the nacelle inlet, wherein the valve assembly comprises;

a first direct acting valve comprising;

a first inlet;

a first valve chamber fluidly connected to the first inlet;

a first internal valve body circumferentially surrounding the first valve chamber;

a first outlet; and

a first piston for adjusting a rate of flow of air through the first direct acting valve, wherein the first piston is slidably engaged with the first internal valve body;

a first control valve assembly fluidly connected to the first valve chamber of the first direct acting valve;

a second direct acting valve comprising;

a second inlet;

a second valve chamber fluidly connected to the second inlet;

a second internal valve body circumferentially surrounding the second valve chamber;

a second outlet; and

a second piston for adjusting a rate of flow of air through the second direct acting valve, wherein the second piston is slidably engaged with the second internal valve body, and further wherein the second direct acting valve is fluidly connected to the first direct acting valve in a series configuration such that the second inlet of the second direct acting valve is directly connected to the first outlet of the first direct acting valve; and

a second control valve assembly fluidly connected to the second valve chamber of the second direct acting valve;

a second lip element disposed on an upstream end of the second piston, the second lip element for sealing engagement with second internal valve body of the second direct acting valve, wherein a second axial face of the second lip element extends at an angle θ

_LIP between a first plane extending in an axial direction and the second axial face of the second lip element; and

a second axial face of the second internal valve body, wherein the second axial face of the second internal valve body extends at an angle θ

_VB between a second plane extending in an axial direction and the second axial face of the second internal valve body, further wherein an expansion angle θ

_EXP equivalent to the difference between angle θ

_LIP and angle θ

_VB comprises an angle from 15°

to 60°

.

8. The anti-icing system of claim 7, wherein the first and second control valve assemblies are electrically connected to a full authority digital engine control of the aircraft.

9. The anti-icing system of claim 7, wherein the first control valve assembly comprises:

a first solenoid valve comprising;

a first ball element;

a first plunger attached to or in contact with the first ball element; and

a first solenoid surrounding the first plunger, the first solenoid for creating a magnetic field to interact with the first plunger; and

a first pintle valve comprising;

a first pintle housing;

a first pintle disposed in the first pintle housing;

a first threadably adjustable biasing element for biasing the first pintle valve, wherein the first pintle valve is directly fluidly connected to the first solenoid valve, and wherein both of the first solenoid valve and the first pintle valve of the first control valve assembly are fluidly connected to the first valve chamber of the first direct acting valve.

10. The anti-icing system of claim 7, wherein the second control valve assembly comprises:

a second solenoid valve comprising;

a second ball element;

a second plunger attached to the second ball element; and

a second solenoid surrounding the second plunger, the second solenoid for creating a magnetic field to interact with the second plunger; and

a second pintle valve comprising;

a second pintle housing;

a second pintle disposed in the second pintle housing;

a second threadably adjustable biasing element for biasing the second pintle valve, wherein the second pintle valve is directly fluidly connected to the second solenoid valve, and wherein both of the second solenoid valve and the second pintle valve of the second control valve assembly are fluidly connected to the second valve chamber of the second direct acting valve.

11. The anti-icing system of claim 7 further comprising:

a first lock mechanism positioned in the first valve chamber of the first direct acting valve, the first locking mechanism for locking the first piston in a fully open position; and

a second lock mechanism positioned in the second valve chamber of the second direct acting valve, the second locking mechanism for locking the second piston in a fully open position.

12. The anti-icing system of claim 7 further comprising:

a first lip element disposed on an upstream end of the first piston, the first lip element for sealing engagement with first internal valve body of the first direct acting valve, wherein a first axial face of the first lip element extends at an angle θ

_LIP between a first plane extending in an axial direction and the first axial face of the first lip element; and

a first axial face of the first internal valve body, wherein the first axial face of the first internal valve body extends at an angle θ

_VB between a second plane extending in an axial direction and the first axial face of the first internal valve body, further wherein an expansion angle θ

_EXP equivalent to the difference between angle θ

_LIP and angle θ

_VB comprises an angle from 15°

to 60°

.