# US 8,539,748 B2 · Segmented inertial particle separators and methods of assembling turbine engines

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- Number: US 8,539,748 B2
- Document ID: US8539748B2
- Status: Granted
- Kind: B2
- Application number: 11/611,652
- Filed: 2006-12-15
- Published: 2008-06-19
- Granted: 2013-09-24
- Earliest claimed: 2006-12-15
- Assignees: General Electric Company
- Applicants: John Paul Petrowicz; Timothy Joseph Higgins; Walter Jackson Tingle
- Inventors: John Paul Petrowicz; Timothy Joseph Higgins; Walter Jackson Tingle
- Web page: https://patentgrep.com/patent/US8539748B2

## CPC

- F02C 7/05: having provisions for obviating the penetration of damaging objects or particles
- F05D 2230/60: Assembly methods
- Y10T 137/0536: Highspeed fluid intake means [e.g., jet engine intake]
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A method for assembling a turbine engine including a compressor is disclosed. The method includes coupling an inlet including an inertial particle separator (IPS) and a first surface that is defined using a segment angle, to a gas turbine engine, and coupling the first surface substantially flush against a fuselage of an aircraft to reduce drag.

## Claims

### Claim 1

A method for assembling a turbine engine including a compressor, said method comprising:
coupling an inlet to a gas turbine engine, the inlet extending circumferentially about a centerline of the inlet over a predetermined segment angle that is less than 360° and the inlet including:
a bullet nose,
a nacelle spaced radially outwardly from the bullet nose such that an entry passage is defined between the bullet nose and the nacelle,
an inertial particle separator (IPS) positioned within the entry passage and oriented downstream of the bullet nose to define a dirty fluid channel and a clean fluid channel, wherein the dirty fluid channel is positioned downstream from a convex section of the bullet nose and is configured to receive particles separated from the fluid by inertia caused by the fluid flowing past the convex section of the bullet nose, and
a first surface that is defined by the segment angle, the segment angle selected such that the first surface matingly engages a surface of a fuselage of an aircraft when the inlet is installed on the aircraft; and
coupling the first surface flush against the fuselage of the aircraft to reduce drag.

### Claim 2 (depends on 1)

A method in accordance with claim 1 wherein coupling an inlet further comprises selecting an inlet that has a segment angle that establishes a desired length of the first surface and that recovers ram air total pressure into engine inlet static pressure for enhanced performance.

### Claim 3 (depends on 1)

A method in accordance with claim 1 wherein coupling an inlet further comprises coupling an inlet including a first surface that has at least one of a linear, curved and curve-linear contour.

### Claim 4 (depends on 1)

A method in accordance with claim 1 wherein coupling an inlet further comprises coupling an inlet including a first surface that has a contour that substantially conforms to an exterior contour of the fuselage.

### Claim 5 (depends on 1)

A method in accordance with claim 1 wherein coupling an inlet further comprises removably coupling the inlet to the gas turbine engine using a plurality of fasteners.

### Claim 6 (depends on 1)

A method in accordance with claim 1 wherein coupling an inlet further comprises coupling the inlet such that said entry channel extends radially about a center of the inlet through the segment angle.

### Claim 7

A gas turbine engine comprising:
a compressor; and
an inlet coupled upstream from said compressor, said inlet extending circumferentially about a centerline of the inlet over a predetermined segment angle that is less than 360° and that mates flush against an exterior fuselage contour and comprises a bullet nose, a nacelle spaced outwardly from the bullet nose such that an entry passage is defined between the bullet nose and the nacelle, and an inertial particle separator positioned within the entry passage and oriented downstream of said bullet nose, said inertial particle separator comprising:
a clean fluid channel for channeling a fluid from the entry passage to said compressor;
a dirty fluid channel for discharging particles suspended in the fluid from the entry passage to atmosphere, said dirty fluid channel positioned downstream from a convex section of the bullet nose, said dirty fluid channel configured to receive particles separated from the fluid by inertia caused by the fluid flowing past the convex section of the bullet nose; and
a scavenge system coupled to said dirty fluid channel, said scavenge system comprising a scroll vane, a scroll case, a blower scavenge duct, a scavenge blower and a scavenge blower exhaust duct.

### Claim 8 (depends on 7)

A gas turbine engine in accordance with claim 7 wherein said inlet further comprises a first surface having a length defined by a segment angle.

### Claim 9 (depends on 8)

A gas turbine engine in accordance with claim 8 wherein said first surface comprises at least one of a linear, curved and curve-linear shape.

### Claim 10 (depends on 7)

A gas turbine engine in accordance with claim 7 wherein said inlet is removably coupled to said gas turbine engine.

### Claim 11

A segmented inertial particle separator for a turbine engine, said particle separator comprising:
an inlet comprising an entry channel extending between a bullet nose and a nacelle, a splitter positioned within said entry channel and oriented downstream of said bullet nose to define a dirty fluid channel and a clean fluid channel, and an exterior inlet contour, each of said dirty fluid channel and said clean fluid channel in flow communication with said entry channel, said inlet extending circumferentially around a centerline of the inlet through an angle less than 360° wherein said exterior inlet contour is configured to fit flush against an aircraft exterior contour, said dirty fluid channel positioned downstream from a convex section of said bullet nose, said dirty fluid channel configured to receive particles separated from the fluid by inertia caused by the fluid flowing past the convex section of said bullet nose.

### Claim 12 (depends on 11)

A segmented inertial particle separator in accordance with claim 11 wherein said inlet further comprises a scavenge system coupled in flow communication with said dirty fluid channel, said scavenge system comprising a scavenge blower.

### Claim 13 (depends on 12)

A segmented inertial particle separator in accordance with claim 12 wherein said scavenge blower is an accessory gear box powered scavenge blower.

### Claim 14 (depends on 11)

A segmented inertial particle separator in accordance with claim 11 wherein said inlet is removably coupled to a gas turbine engine using a plurality of mechanical fasteners.

### Claim 15 (depends on 11)

A segmented inertial particle separator in accordance with claim 11 wherein said clean fluid channel is removably coupled to an annular inlet of said turbine engine.

### Claim 16 (depends on 11)

A segmented inertial particle separator in accordance with claim 11 wherein said inlet comprises an exterior contour comprising at least one of a linear, a curved and a curve-linear shape.

### Claim 17 (depends on 16)

A segmented inertial particle separator in accordance with claim 16 wherein a length of said exterior contour is defined by a segment angle.