Air filtration system for gas turbine engine pneumatic system

• US 8,572,985 B2
• Filed: 06/26/2009
• Issued: 11/05/2013
• Est. Priority Date: 06/26/2009
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Waddleton, David
• Primary Examiner(s): SUNG, GERALD LUTHER
• Application Number:
  US12/492,214
• Publication Number:
  US 20100326090A1
• Time in Patent Office: 1,593 Days
• Field of Search: 607/85, 607/95, 607/82
• US Class Current: 60/795
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F05D 2260/607 Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Abstract

A gas turbine engine pneumatic system for controlling an air bleed valve includes a variable orifice device for controllably discharging air from the pneumatic system in order to reduce a maximum air pressure applied to the air bleed valve, to a predetermined level. A filter device is provided to filter the air discharged from the variable orifice.

Claims

1. A gas turbine engine pneumatic system for controlling an air bleed valve, comprising:

an apparatus for generating a maximum air pressure;

a first passage extending between the apparatus and the air bleed valve for applying the maximum air pressure to the air bleed valve to close the air bleed valve against a pressurized air;

a second passage connected to the first passage and a variable orifice device included in the second passage to controllably discharge air from the first passage through the variable orifice device, thereby reducing the maximum air pressure applied to the air bleed valve to a predetermined level; and

a wash filter located in the pneumatic system for filtering the air discharged through the variable orifice device, wherein the wash filter comprises an inlet and first and second outlets, the inlet and first outlet being connected to a main passage of the apparatus to allow an air flow to be introduced into the inlet, a first portion of the air flow passing through the wash filter without filtration and being discharged through the first outlet, and the second outlet being connected to the first passage to allow a second portion of the air flow introduced into the inlet to be filtered and to enter the first passage.

2. The gas turbine engine pneumatic system as defined in claim 1 wherein the wash filter comprises a cylinder defining a central passage between the inlet and the first outlet, surrounded by a filtering medium, the second outlet being in fluid communication with the central passage through the surrounding filtering medium.

3. The gas turbine engine pneumatic system as defined in claim 1 wherein the apparatus comprises an orifice network having an upstream end in fluid communication with a high pressure air source and a downstream end in fluid communication with a low pressure sink.

4. The gas turbine engine pneumatic system as defined in claim 2 wherein the low pressure sink is an ambient air pressure.

5. A gas turbine engine comprising:

an air bleed valve for selectively bleeding air from a contained pressurized air; and

a pneumatic system for applying a maximum air pressure to the air bleed valve to close the air bleed valve against a pressure of the pressurized air;

wherein the pneumatic system comprises a variable orifice device for controllably discharging air from the pneumatic system through the variable orifice device, thereby reducing the maximum air pressure applied to the air bleed valve to a predetermined level; and

wherein the pneumatic system comprises a wash filter for filtering the air discharged through the variable orifice device, the wash filter filtering a first portion of an entire air flow entering the wash filter and directing a second portion of the entire air flow to pass through the wash filter without filtration, thereby forming a washing air flow for cleaning the wash filter.

6. The gas turbine engine as defined in claim 5 wherein the wash filter is included in a main passage of the pneumatic system to thereby allow a dropping orifice network air flow to pass the wash filter as the washing air flow, and wherein a first passage extends between the wash filter and the air bleed valve, and a second passage including the variable orifice device is connected to the first passage, thereby directing the filtered first portion of the air flow to pass through the first and second passages.