IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0097904
(2011-04-29)
|
등록번호 |
US-8235170
(2012-08-07)
|
발명자
/ 주소 |
- Ertz, Timothy
- Royalty, Chuck
- Sheoran, Yogendra Yogi
|
출원인 / 주소 |
- Honeywell International Inc.
|
대리인 / 주소 |
Ingrassia Fisher & Lorenz, P.C.
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
10 |
초록
▼
Methods integrated tailcone muffler (ITM) is provided for minimizing noise generated while discharging pressurized air from one or more aircraft gas turbine engines. The ITM comprises a tail cone defining a conical backing cavity, the conical backing cavity having a large forward end and a narrow af
Methods integrated tailcone muffler (ITM) is provided for minimizing noise generated while discharging pressurized air from one or more aircraft gas turbine engines. The ITM comprises a tail cone defining a conical backing cavity, the conical backing cavity having a large forward end and a narrow aft end and a porous exhaust liner with a first end and a second end, the first end coupled to an oil cooler eductor discharge plenum of a first gas turbine engine of the one or more gas turbine engines and a second end discharging to atmosphere via the narrow aft end of the conical backing cavity. The ITM further comprises a bleed air discharge conduit configured to discharge pressurized bleed air from the one or more gas turbine engines into the conical backing cavity and a firewall bulkhead defining the large forward end of the conical backing cavity, defining a first aperture passing the cylindrical porous exhaust liner and defining a second aperture passing the bleed air discharge conduit, the firewall bulkhead extending radially from both of the cylindrical porous exhaust liner and the bleed air discharge conduit.
대표청구항
▼
1. A low-noise integrated tailcone muffler (ITM) assembly for use in an aircraft tailcone having a gas turbine engine that exhausts gasses therethrough, comprising: a tailcone defining a conical backing cavity, the conical backing cavity having a large forward end and a narrow extreme aft end;a perm
1. A low-noise integrated tailcone muffler (ITM) assembly for use in an aircraft tailcone having a gas turbine engine that exhausts gasses therethrough, comprising: a tailcone defining a conical backing cavity, the conical backing cavity having a large forward end and a narrow extreme aft end;a permeable exhaust liner with a first end and a second end, the first end coupled to an oil cooler eductor discharge plenum of the gas turbine engine and a second end discharging directly to atmosphere via the narrow extreme aft end of the conical backing cavity;a bleed air discharge conduit configured to discharge pressurized bleed air from the gas turbine engine into the conical backing cavity; anda firewall bulkhead defining the large forward end of the conical backing cavity, defining a first aperture passing the porous exhaust liner and defining a second aperture passing the bleed air discharge conduit, the firewall bulkhead extending radially from both of the porous exhaust liner and the bleed air discharge conduit. 2. The ITM of claim 1, wherein the conical backing cavity is configured to accept the pressurized bleed air discharged from the bleed air discharge conduit until the pressurized bleed air dissipates to the atmosphere through the porous exhaust liner and out the second end of the porous exhaust liner. 3. The ITM of claim 1 wherein, the porous exhaust liner consists of one or more of a group of materials that includes a perforated plate, a metal mesh, or a combination of both the perforated plate and the metal mesh, wherein further the perforated plate and the metal mesh may comprise one of a metal material and a carbon composite material. 4. The ITM of claim 1, further comprising a hard baffle defined by an outer circumference and defining an aperture therethrough to pass the porous exhaust liner, the hard baffle located aft of and substantially parallel to the firewall bulkhead, the hard baffle being situated so as to form a surge plenum configured to accept the pressurized bleed air discharge. 5. The ITM of claim 4, wherein a length of the porous exhaust liner extending between the firewall bulkhead and the hard baffle comprises perforated sheet metal. 6. The ITM of claim 5, wherein the surge plenum is configured to accept the pressurized bleed air discharged from the bleed air discharge conduit until the pressurized bleed air discharge dissipates to the atmosphere through the perforated sheet metal into the porous exhaust liner and out the second end of the porous exhaust liner. 7. The ITM of claim 6, wherein the surge plenum is formed by attaching the outer circumference of the hard baffle to the firewall bulkhead. 8. The ITM of claim 1 further comprising an annular opening in the porous exhaust liner proximate to and downstream from the firewall bulkhead. 9. The ITM of claim 1, wherein the porous exhaust liner comprises a plurality of angled effusion holes in the porous exhaust liner proximate to, and downstream from, the firewall bulkhead. 10. The ITM of claim 7, wherein the porous exhaust liner comprises an annular opening between the firewall bulkhead and the hard baffle. 11. The ITM of claim 1, wherein the bleed air discharge conduit discharges pressurized bleed air directly into the porous exhaust liner immediately abaft the firewall bulkhead. 12. The ITM of claim 1, wherein the bleed air discharge conduit discharges pressurized bleed air directly into the porous exhaust liner distantly abaft the firewall bulkhead. 13. The ITM of claim 1, wherein the bleed air discharge conduit includes a diffuser attached to the bleed air discharge conduit abaft and proximate to the firewall bulkhead. 14. The ITM of claim 13 wherein the diffuser consist of one of a group of diffuser configurations including an open end funnel shaped diffuser, a funnel shaped diffuser with perforated dome shaped cover and a funnel shaped diffuser with a cover plate attached perpendicular to a longitudinal axis of, and spaced away from the bleed air discharge conduit. 15. The ITM of claim 1, comprising a second gas turbine engine exhausting to a second oil cooler eductor discharge plenum. 16. The ITM of claim 15, wherein the gas turbine engine and the second gas turbine engine share the bleed air discharge conduit. 17. A method for minimizing noise generated while discharging pressurized air from one or more aircraft gas turbine engines, the method comprising steps of: creating a conical backing cavity defined by a tail cone of an aircraft having a large forward end and a narrow extreme aft end venting to an ambient atmosphere, wherein the large forward end is defined by a firewall bulkhead;inserting a permeable exhaust liner comprising a first end and a second end through the conical backing cavity, the permeable exhaust liner extending through the aperture in the firewall bulkhead and the second end terminating at the narrow extreme aft end of the conical backing cavity;inserting a pressurized air discharge conduit through a second aperture in the firewall bulkhead into the conical backing cavity; anddischarging pressurized air into the large forward end of the conical backing cavity,wherein a pressure increase from the pressurized air discharged into the conical backing cavity is immediately and partially dissipated by a relatively large size of the conical backing cavity and the pressure of the pressurized air is further reduced as the pressurized air flows through the porous exhaust liner and is discharged to the ambient atmosphere via its second end. 18. The method of claim 17 further comprising, installing a hard baffle, the hard baffle defined by an outer circumference and defining an aperture therethrough to pass the porous exhaust liner, the hard baffle installed aft of and substantially parallel to the firewall bulkhead, the hard baffle being situated so as to form a surge plenum configured to accept the pressurized air, wherein the pressurized air is discharged into the surge plenum and flows into the porous exhaust liner. 19. The method of claim 18, wherein the pressurized air flows either into the conical backing cavity through the porous exhaust liner or flows to the ambient atmosphere via its second end. 20. The method of claim 17, further comprising mounting a diffuser to the pressurized air discharge conduit, the diffuser configured to redirect the pressurized air.
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