Integrated Environmental Control System Manifold

• US 20170044991A1
• Filed: 09/18/2014
• Published: 02/16/2017
• Est. Priority Date: 02/14/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Suciu, Gabriel L., Chandler, Jesse M.
• Granted Patent: US 10,215,101 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 25/162 Bearing supports
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/052 with dust-separation devices
• CPC Class Codes: F02C 7/25 Fire protection or prevention in general A62
• 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: F04D 29/522 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: F04D 29/5853 heat insulation or conduction
• CPC Class Codes: F04D 29/701 especially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/15 Heat shield

Abstract

A compressor intermediate case for a gas turbine engine includes a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure. Each strut of the plurality of intermediate case struts includes a leading edge. A turning scoop is disposed at the leading edge of each strut of the plurality of intermediate case struts. A plurality of diffusers extends radially outwardly from the compressor intermediate case so that each diffuser of the plurality of diffusers engages with a corresponding turning scoop. A substantially annular structural fire wall extends radially outwardly from the compressor intermediate case. An environmental control system manifold is disposed on the compressor intermediate case. The environmental control system manifold includes an exit port.

Claims

1. An intermediate case for a gas turbine engine compressor, the intermediate case comprising:

a plurality of intermediate case struts joining the intermediate case to an inner engine structure, each strut of the plurality of intermediate case struts including a leading edge;

a turning scoop being disposed at the leading edge of each strut of the plurality of intermediate case struts;

a plurality of diffusers extending radially outwardly from the intermediate case, each diffuser of the plurality of diffusers being engaged with a corresponding turning scoop;

a substantially annular structural fire wall extending radially outwardly from the intermediate case; and

an environmental control system manifold being disposed on the intermediate case, the environmental control system manifold including an exit port.

2. The intermediate case of claim 1, further including a non-structural fairing extending radially outwardly from the intermediate case, the non-structural fairing disposed upstream of the annular structural fire wall to define a 2.5 bleed duct therebetween.

3. The intermediate case of claim 2, further including a 2.5 stability bleed valve in operable association with the non-structural fairing and the 2.5 bleed duct, the 2.5 stability bleed valve operably movable between an open and closed position.

4. The intermediate case of claim 2, wherein the 2.5 bleed duct is arranged to the intermediate case forming a first dirt separator.

5. The intermediate case of claim 1, wherein the turning scoop includes an upstream-facing scoop inlet, the scoop inlet being offset substantially radially inwardly from the intermediate case forming a second dirt separator.

6. The intermediate case of claim 1, wherein the environmental control system manifold is asymmetrical.

7. The intermediate case of claim 6, wherein the environmental control system manifold is formed of a substantially annular first and second collection wall, the first collection wall extends substantially radially outwardly from the intermediate case, the second collection wall extends downstream substantially axially from the structural fire wall, the first and second collection walls intersect to form a smooth bend, the exit port being disposed on the first collection wall, the second collection wall extends a first distance from the fire wall adjacent to the exit port and tapers moving along its circumference until it reaches an area oppositely positioned across the intermediate case, where the second collection wall extends a second distance from the fire wall that is less than the first distance, the first collection wall extends a third distance from the intermediate case adjacent the exit port and tapers moving along its circumference until it reaches the area oppositely positioned across the intermediate case, where the first collection wall extends a fourth distance from the intermediate case that is less than the third distance.

8. A gas turbine engine, the engine comprising:

a compressor intermediate case;

a plurality of intermediate case struts joining the compressor intermediate case to an inner engine structure, each strut of the plurality of intermediate case struts including a leading edge;

a turning scoop being disposed at the leading edge of each strut of the plurality of intermediate case struts;

a plurality of diffusers extending radially outwardly from the compressor intermediate case, each diffuser of the plurality of diffusers being engaged with a corresponding turning scoop;

a substantially annular structural fire wall extending radially outwardly from the compressor intermediate case; and

an environmental control system manifold being disposed on the compressor intermediate case, the environmental control system manifold including an exit port.

9. The gas turbine engine of claim 8, further including a non-structural fairing extending radially outwardly from the compressor intermediate case, the non-structural fairing disposed upstream of the annular structural fire wall to define a 2.5 bleed duct therebetween.

10. The gas turbine engine of claim 9, further including a 2.5 stability bleed valve in operable association with the non-structural fairing and the 2.5 bleed duct, the 2.5 stability bleed valve operably movable between an open and closed position.

11. The gas turbine engine of claim 9, wherein the 2.5 bleed duct is arranged to the compressor intermediate case forming a first dirt separator.

12. The gas turbine engine of claim 8, wherein the turning scoop includes an upstream-facing scoop inlet, the scoop inlet being offset substantially radially inwardly from the compressor intermediate case forming a second dirt separator.

13. The gas turbine engine of claim 8, wherein the environmental control system manifold is asymmetrical.

14. The gas turbine engine of claim 13, wherein the environmental control system manifold is formed of a substantially annular first and second collection wall, the first collection wall extends substantially radially outwardly from the compressor intermediate case, the second collection wall extends downstream substantially axially from the structural fire wall, the first and second collection walls intersect to form a smooth bend, the exit port being disposed on the first collection wall, the second collection wall extends a first distance from the fire wall adjacent to the exit port and tapers moving along its circumference until it reaches an area oppositely positioned across the compressor intermediate case, where the second collection wall extends a second distance from the fire wall that is less than the first distance, the first collection wall extends a third distance from the compressor intermediate case adjacent the exit port and tapers moving along its circumference until it reaches the area oppositely positioned across the compressor intermediate case, where the first collection wall extends a fourth distance from the compressor intermediate case that is less than the third distance.

15. The gas turbine engine of claim 8, further including a v-groove disposed on the structural fire wall, the V-groove securely interfaces with a core engine cowl.

16. The gas turbine engine of claim 12, further including a plurality of guide vanes disposed upstream of each scoop inlet.

17. A method of providing cleaner environmental control system bleed air, which exits a gas turbine engine, so that there is minimal disruption to a core air flow, the method comprising:

joining a plurality of intermediate case struts between a compressor intermediate case and an inner engine structure, each strut of the plurality of intermediate case struts including a leading edge;

disposing a turning scoop at the leading edge of each strut of the plurality of intermediate case struts;

providing a plurality of diffusers extending radially outwardly from the compressor intermediate case, each diffuser of the plurality of diffusers being engaged with a corresponding turning scoop;

providing a substantially annular structural fire wall extending radially outwardly from the compressor intermediate case;

providing a non-structural fairing extending radially outwardly from the compressor intermediate case, the non-structural fairing disposed upstream of the annular structural fire wall to define a 2.5 bleed duct therebetween; and

providing an environmental control system manifold on the compressor intermediate case, the environmental control system manifold including an exit port.

18. The method of claim 17, further including providing an upstream-facing scoop inlet onto the turning scoop, the scoop inlet being offset substantially radially inwardly from the compressor intermediate case forming a second dirt separator.

19. The method of claim 17, wherein the environmental control system manifold is asymmetrical.

20. The method of claim 19, wherein the environmental control system manifold is formed of a substantially annular first and second collection wall, the first collection wall extends substantially radially outwardly from the compressor intermediate case, the second collection wall extends downstream substantially axially from the structural fire wall, the first and second collection walls intersect to form a smooth bend, the exit port being disposed on the first collection wall, the second collection wall extends a first distance from the fire wall adjacent to the exit port and tapers moving along its circumference until it reaches an area oppositely positioned across the compressor intermediate case, where the second collection wall extends a second distance from the fire wall that is less than the first distance, the first collection wall extends a third distance from the compressor intermediate case adjacent the exit port and tapers moving along its circumference until it reaches the area oppositely positioned across the compressor intermediate case, where the first collection wall extends a fourth distance from the compressor intermediate case that is less than the third distance.