Mounting structure for nacelle inner structure

1 . An assembly for an aircraft propulsion system, comprising:

a pylon structure extending axially along an axis;

a nacelle inner barrel extending axially along and circumferentially about the axis, the nacelle inner barrel includes a first inner barrel section and a second inner barrel section;

a nacelle outer structure extending axially along and circumferentially about the nacelle inner barrel;

a bifurcation including a first bifurcation section and a second bifurcation section, the first bifurcation section disposed to a first side of the pylon structure, the second bifurcation section disposed to a second side of the pylon structure that is circumferentially opposite to the first side of the pylon structure, and the first bifurcation section and the second bifurcation section each projecting radially out from the nacelle inner barrel to the nacelle outer structure;

a mounting yoke including a first yoke bracket and a second yoke bracket, the first yoke bracket and the second yoke bracket each pivotally attached to the pylon structure by a yoke pivot connection at a radial outer end of the mounting yoke, the first bifurcation section fixedly attached to the first yoke bracket at a first side of the mounting yoke, and the second bifurcation section fixedly attached to the second yoke bracket at a second side of the mounting yoke that is circumferentially opposite to the second side of the mounting yoke; and

a bypass flowpath extending radially between and formed by the nacelle inner barrel and the nacelle outer structure, the bifurcation extending radially across and circumferentially bifurcating the bypass flowpath;

wherein the mounting yoke, the first inner barrel section and the second inner barrel section are operable to collectively pivot together about the yoke pivot connection.

2 . The assembly of claim 1 , wherein

the bypass flowpath extends circumferentially about the axis and circumferentially along the nacelle inner barrel and the nacelle outer structure from the first bifurcation section to the second bifurcation section.

3 . The assembly of claim 1 , further comprising:

a gas turbine engine including a case, a compressor section, a combustor section and a turbine section, the case housing the compressor section, the combustor section and the turbine section;

the nacelle inner barrel extending axially along and circumferentially about the case;

the pylon structure mounted to the case;

the first bifurcation section axially fixed to the case through a first V-blade coupling; and

the second bifurcation section axially fixed to the case through a second V-blade coupling.

4 . The assembly of claim 1 , wherein

the first yoke bracket and the second yoke bracket are bolted together at a radial inner end of the mounting yoke.

5 . The assembly of claim 1 , further comprising

a first yoke-to-inner barrel hinge fixedly attached to the first inner barrel section and movably coupled to the mounting yoke at a radial inner end of the mounting yoke; and

a second yoke-to-inner barrel hinge fixedly attached to the second inner barrel section and movably coupled to the mounting yoke at the radial inner end of the mounting yoke.

6 . The assembly of claim 5 , further comprising:

a first yoke-to-hinge linkage extending between and pivotally attached to the first yoke-to-inner barrel hinge and the mounting yoke; and

a second yoke-to-hinge linkage extending between and pivotally attached to the second yoke-to-inner barrel hinge and the mounting yoke.

7 . The assembly of claim 1 , further comprising:

a first bifurcation bracket pivotally attached to the pylon structure by a first bifurcation bracket pivot connection at a radial outer end of the first bifurcation bracket, the first bifurcation section fixedly attached to the first bifurcation bracket; and

a second bifurcation bracket pivotally attached to the pylon structure by a second bifurcation bracket pivot connection at a radial outer end of the second bifurcation bracket, the second bifurcation section fixedly attached to the second bifurcation bracket.

8 . The assembly of claim 7 , wherein

the bifurcation extends axially from an upstream end of the bifurcation to a downstream end of the bifurcation; and

the first bifurcation bracket and the second bifurcation bracket are each axially spaced from the mounting yoke towards the downstream end of the bifurcation.

9 . The assembly of claim 7 , further comprising:

a lateral linkage extending between a first end of the lateral linkage and a second end of the lateral linkage;

the lateral linkage pivotally attached to the first bifurcation bracket at the first end of the lateral linkage and a radial inner end of the first bifurcation bracket; and

the lateral linkage pivotally attached to the second bifurcation bracket at the second end of the lateral linkage and a radial inner end of the second bifurcation bracket.

10 . The assembly of claim 9 , further comprising:

a diagonal linkage extending between a radial inner end of the diagonal linkage and a radial outer end of the diagonal linkage;

the diagonal linkage pivotally attached to the lateral linkage at the radial inner end of the diagonal linkage and the first end of the lateral linkage; and

the diagonal linkage pivotally attached to the pylon structure at the radial outer end of the diagonal linkage and towards the second bifurcation bracket.

11 . The assembly of claim 7 , wherein the nacelle inner barrel includes a first inner barrel section and a second inner barrel section, and the assembly further comprises:

a first bracket-to-inner barrel hinge fixedly attached to the first inner barrel section and movably coupled to the first bifurcation bracket at a radial inner end of the first bifurcation bracket; and

a second bracket-to-inner barrel hinge fixedly attached to the second inner barrel section and movably coupled to the second bifurcation bracket at a radial inner end of the second bifurcation bracket.

12 . The assembly of claim 11 , further comprising:

a first bracket-to-hinge linkage pivotally attached to the first bracket-to-inner barrel hinge, the first bracket-to-hinge linkage attached to the first bifurcation bracket by a plurality of first bracket pin connections; and

a second bracket-to-hinge linkage pivotally attached to the second bracket-to-inner barrel hinge, the second bracket-to-hinge linkage attached to the second bifurcation bracket by a plurality of second bracket pin connections.

13 . The assembly of claim 1 , further comprising:

a bumper structure fixedly attached to the pylon structure and decoupled from the bifurcation, the bumper structure comprising a first bumper and a second bumper;

the first bumper configured to abut against the first inner barrel section when the first inner barrel section is in a closed position, and the first bumper configured to disengage from the first inner barrel section when the first inner barrel section is in an open position; and

the second bumper configured to abut against the second inner barrel section when the second inner barrel section is in a closed position, and the second bumper configured to disengage from the second inner barrel section when the second inner barrel section is in an open position.

14 . The assembly of claim 1 , further comprising

a crossbar linkage extending between a first end of the crossbar linkage and a second end of the crossbar linkage;

a first linkage-to-inner barrel hinge fixedly attached to the first inner barrel section and pivotally coupled to the crossbar linkage at the first end of the crossbar linkage; and

a second linkage-to-inner barrel hinge fixedly attached to the second inner barrel section and pivotally coupled to the crossbar linkage at the second end of the crossbar linkage.

15 . The assembly of claim 14 , wherein the crossbar linkage is decoupled from and disengaged from the pylon structure and the bifurcation.

16 . The assembly of claim 1 , further comprises

a gas turbine engine including a case, a compressor section, a combustor section and a turbine section, the case housing the compressor section, the combustor section and the turbine section;

the nacelle inner barrel extending axially along and circumferentially about the case;

the pylon structure mounted to the case;

the first inner barrel section axially fixed to the case through a first V-blade coupling; and

the second inner barrel section axially fixed to the case through a second V-blade coupling.

17 . An assembly for an aircraft propulsion system, comprising:

a pylon structure extending axially along an axis;

a nacelle inner barrel including a first inner barrel section and a second inner barrel section, the first inner barrel section disposed to a first side of the pylon structure, the second inner barrel section disposed to a second side of the pylon structure that is circumferentially opposite to the first side of the pylon structure, and the first inner barrel section and the second inner barrel section each extending axially along and circumferentially about the axis;

a nacelle outer structure extending axially along and circumferentially about the nacelle inner barrel;

a bypass flowpath extending radially between and formed by the nacelle inner barrel and the nacelle outer structure;

a bifurcation projecting radially out from the nacelle inner barrel across the bypass flowpath to the nacelle outer structure and circumferentially bifurcating the bypass flowpath, the bifurcation radially and axially covering the pylon structure, and the bifurcation including a first bifurcation section and a second bifurcation section; and

a mounting yoke pivotally attached to the pylon structure by a yoke pivot connection at a radial outer end of the mounting yoke, the first bifurcation section and the second bifurcation section attached to circumferentially opposing sides of the mounting yoke;

a first yoke-to-inner barrel hinge fixedly attached to the first inner barrel section and movably coupled to the mounting yoke at a radial inner end of the mounting yoke; and

a second yoke-to-inner barrel hinge fixedly attached to the second inner barrel section and movably coupled to the mounting yoke at the radial inner end of the mounting yoke;

wherein the mounting yoke, the first inner barrel section and the second inner barrel section are operable to collectively pivot together about the yoke pivot connection.