Acoustic treatment in geared turbomachine
An example acoustic treatment for a geared turbomachine establishes a portion of the core cowl aft the fan cowl.
1. A geared turbomachine assembly, comprising:
an acoustic treatment establishing a portion of a core cowl aft a fan cowl, the portion providing a radially inner boundary of a bypass flowpath, the acoustic treatment including a perforated face sheet, a backing sheet, and a cellular structure extending therebetween, the perforated face sheet having an open area density that is from 4 percent to 30 percent, wherein the core cowl is formed entirely by the acoustic treatment in some axial areas, wherein the acoustic treatment is in an unducted area of a geared turbomachine.
2. The geared turbomachine assembly of claim 1 , wherein the acoustic treatment extends from a position that is axially aligned with the fan cowl to a portion that is axially aligned with a low-pressure turbine section of the geared turbomachine assembly.
3. The geared turbomachine assembly of claim 1 , wherein the acoustic treatment extends axially to an aftmost end of the core cowl.
4. The geared turbomachine assembly of claim 3 , wherein the acoustic treatment extends continuously from a position that is axially aligned with the fan cowl to the aftmost end of the core cowl.
5. The geared turbomachine assembly of claim 1 , wherein the perforated face sheet comprises a microperforated face sheet having apertures with a diameter that is less than 25 percent of a thickness of the microperforated face sheet.
6. The geared turbomachine assembly of claim 1 , wherein the geared turbomachine assembly has a fan pressure ratio less than 1.45.
7. The geared turbomachine assembly of claim 1 , wherein the acoustic treatment forms a portion of the core cowl that provides a radially outer boundary of a core engine flowpath of the geared turbomachine assembly.
8. A geared turbomachine assembly, comprising:
an acoustic treatment establishing a portion of a core cowl aft a fan cowl, the portion providing a radially inner boundary of a bypass flowpath, the acoustic treatment including a perforated face sheet, a backing sheet, and a cellular structure extending therebetween, the perforated face sheet having an open area density that is from 4 percent to 30 percent, wherein a selected axial portion of the acoustic treatment is not secured to a walled structure, wherein the acoustic treatment extends from a position that is axially aligned with the fan cowl to a portion that is axially aligned with a low-pressure turbine section of the geared turbomachine assembly.
9. The geared turbomachine assembly of claim 8 , wherein the acoustic treatment extends axially to an aftmost end of the core cowl.
10. The geared turbomachine assembly of claim 9 , wherein the acoustic treatment extends continuously from a position that is axially aligned with the fan cowl to the aftmost end of the core cowl.
11. The geared turbomachine assembly of claim 8 , wherein the perforated face sheet comprises a microperforated face sheet having apertures with a diameter that is less than 25 percent of a thickness of the microperforated face sheet.
12. The geared turbomachine assembly of claim 8 , wherein the geared turbomachine assembly has a fan pressure ratio less than 1.45.
13. The geared turbomachine assembly of claim 8 , wherein the acoustic treatment is in an unducted area of a geared turbomachine.
14. The geared turbomachine assembly of claim 8 , wherein the acoustic treatment forms a portion of the core cowl that provides a radially outer boundary of a core engine flowpath of the geared turbomachine assembly.
15. A geared turbomachine assembly, comprising:
an acoustic treatment establishing a portion of a core cowl aft a fan cowl, the acoustic treatment including a perforated face sheet, a backing sheet, and a cellular structure extending therebetween, the perforated face sheet having an open area density that is from 4 percent to 30 percent, wherein the core cowl is formed entirely by the acoustic treatment in some axial areas, wherein the acoustic treatment forms a portion of the core cowl that provides a radially outer boundary of a core engine flowpath of the geared turbomachine assembly, wherein the acoustic treatment is in an unducted area of a geared turbomachine assembly.