Nacelle assembly and mounting structures for a turbofan jet propulsion engine

Claim 2

In a structure for mounting a turbofan engine on a aircraft fuselage, said turbofan engine having a high bypass ratio and including a turbine casing housing a turbine engine, the rearward end of a turbine nozzle operably associated with said turbine casing for directing propulsion gases rearwardly from said engine, an annular fan casing surrounding and spaced outwardly from said turbine casing, a low pressure fan mounted within said fan casing and driven by said turbine engine, said fan casing being structurally coupled to said turbine casing, an improved structure for interchangeably mounting said turbofan engine to a plurality of locations on a fuselage comprising: a structural yoke and means for affixing said yoke to the fuselage of an airplane, said yoke extending about a portion of the periphery of said fan casing and being spaced therefrom, said yoke having a central portion, a first end spaced in a first direction from said central portion and a second end spaced in the opposite direction from said central portion, first shock absorbing mounting means associated with the first end of said yoke for releasably coupling the first end to a first location on the periphery of said fan casing, second shock absorbing mounting means associated with the second end of said yoke for releasably coupling the second end of said yoke to a second location on the periphery of said fan casing, said second location being spaced from said first location, a mounting arm and means for affixing said arm to the fuselage of an airplane, said arm having an outer end located adjacent said turbine casing and rearwardly from said yoke, said arm extending in a generally radial direction toward said turbofan engine, third shock absorbing mounting means associated with the outer end of said arm for releasably coupling said outer end to said turbine casing, nacelle means associated with said engine and including inner and outer fan duct walls defining an annular fan duct associated with and extending rearwardly from said fan casing for receiving fan air from said fan and directing said fan air rearwardly relative to said engine, and bifurcation means affixed to said engine and associated with said fan duct for splitting the flow of air therethrough, said bifurcation means extending longitudinally along said duct from a forward location adjacent said fan casing to a location rearwardly thereof, said bifurcation means being located in said fan channel adjacent the central portion of said yoke and having a central channel therethrough communicating between the region inside the inner fan duct wall and the region outside the outer fan duct wall, said mounting arm extending through said central channel, said nacelle means being coupled to said bifurcation means and said engine so as to be isolated from said mounting arm and said yoke when said engine is mounted thereon, and to remain coupled to said bifurcation means and said engine when said engine is released from said yoke and said mounting arm.

Claim 3

The structure of claim 1 wherein said yoke comprises a rigid arcuate member, said means for affixing the central portion of said yoke to said airplane comprising a beam affixed to said yoke and extending outwardly from said yoke in a radial direction relative to said engine, the outer end of said beam being affixed to said fuselage.

Claim 4

The mounting structure of claim 2 wherein said beam is integral with said yoke.

Claim 5

The structure of claim 1 wherein said turbofan engine includes bleed air conduits extending from said turbine casing, through said central channel in said bifurcation means and toward said fuselage.

Claim 6

The structure of claim 1 further comprising conduit means coupled to the top of said casing of said turbine engine and having an inlet so constructed and located to receive bleed air aft of the compressor of said turbine engine, said conduit means extending in a circumferential direction around said turbine casing to a location generally adjacent and between the inner wall of the fan duct and the outer surface of the turbine casing and thereafter through the central channel in said bifurcation means to a location outside said cowl means.

Claim 7

The structure of claim 1 wherein said nacelle means further comprises an outer nacelle wall, said outer nacelle wall being spaced outwardly from said outer fan duct wall to define an annular space therebetween, and wherein said yoke is located between said fan casing and said outer nacelle wall and forwardly from said bifurcation means, said nacelle wall having an opening therein located adjacent the central portion of said yoke and forwardly of said forward location of said bifurcation means, said means mounting said yoke to said fuselage including a beam affixed to said yoke, said beam extending substantially radially outwardly through said opening.

Claim 8

The structure of claim 6 further comprising: an aerodynamic fairing extending between said nacelle wall and said fuselage, said fairing having a channel therethrough placing the central channel in said bifurcation means and said opening in said nacelle wall in communication with said fuselage, said beam and said arm extending through the channel in said fairing.

Claim 9

The structure of claim 1 wherein said fan has a forwardly facing annular inlet, said nacelle means comprising: a first annular wall located forwardly from and coupled to the forward portion of said fan casing, said first wall defining an inlet channel to said fan, a second, generally annularly shaped wall surrounding and spaced outwardly from said first wall and said outer fan duct wall, the rearward end of said second wall merging into the rearward portion of said outer fan duct wall at a location rearwardly from said fan, the forward portion of said second wall being arcuate and merging into the forward portion of said first wall, said first wall and the forward portion of said second wall thereby forming the leading edge of said nacelle means, said bifurcation means extending generally radially between and connected to said inner and outer fan duct walls, said bifurcation means extending longitudinally from a location rearwardly of said fan to a location forwardly of the exhaust nozzle of said turbine.

Claim 10

The mounting structure of claim 8 wherein said means mounting said yoke extends from said yoke to said fuselage, said mounting arm extending from said engine to said fuselage, said mounting means and said arm forming a strut for mounting said engine on said fuselage, said strut being enclosed in an aerodynamic fairing extending between said nacelle means and said fuselage, and wherein portions of said inner and outer fan duct walls and said second wall are separated at first locations from the respective forward portions thereof along a first plane oriented transversely to the longitudinal axis of said engine, said first plane being located rearwardly from said fan casing, said portions being further separated from any rearward portions thereof at a second plane oriented transversely relative to the longitudinal axis of said engine, said second plane being spaced rearwardly from said first plane, said portions further being separated along a longitudinal line located substantially diametrically opposite from said strut, and extending from said first plane to said second plane, the separated portion of said second wall further being separated from the remainder of said second wall along longitudinall extending lines located on both sides of, but adjacent and offset from, said strut, the portions of said second wall between the latter longitudinal separations being fixed to said engine, said inner and outer fan duct walls further being separated along longitudinal lines adjacent said strut and spaced in the tangential direction relative to the walls on each side of a longitudinally extending diametric plane intersecting said struct and intersecting said first longitudinal separation locations of said second and inner and outer fan duct wall portions, said mounting structure further comprising: a first longitudinally extending wall joining the separated portions of said inner and outer fan duct walls adjacent a first side of said strut, said first longitudinally extending wall being spaced from and substantially parallel to said diametric plane on said first side thereof, a second longitudinally extending wall joining the separated portions of said inner and outer fan duct walls adjacent a second side of said strut, said second longitudinally extending wall being spaced from and substantially parallel to said diametric plane on said second side thereof, a third longitudinally extending wall joining the separated portions of said inner and outer fan duct walls adjacent the longitudinal separation location opposite said strut and adjacent and substantially parallel to one side of said diametric plane, a fourth longitudinally extending wall joining separated portions of said inner and outer fan duct walls at the longitudinal separation location diametrically opposite from said strut and adjacent and substantially parallel to the other side of said diametric plane, means for fixing the separated portions of said inner fan duct wall to and spacing the separated portions of said inner fan duct wall from radially adjacent ones of the separated portions of said outer fan duct wall, said separated portions of said second and said inner and outer fan duct walls thereby forming a pair of D-shaped duct portions that when joined together form said annularly shaped fan duct, said first and second longitudinally extending walls forming a portion of the bifurcation means for splitting the flow through one side of said annular fan duct, said annular fan duct further containing a forwardly extending member forming a forward extension of the portion of the bifurcation means formed by said first and second longitudinally extending walls, and first hinge means for connecting a first one of said D-ducts to said engine for swinging movement between a joined position and a position wherein said ducts are swung outwardly to expose a portion of said engine means, and second hinge means for connecting the second one of said D-ducts to said strut for swinging movement between a joined position and a position wherein said ducts are swung outwardly to expose a portion of said engine means, said bifurcation means including a box-like member securely affixed to said engine and positioned between said first and second longitudinally extending walls, said channel in said bifurcation means being defined within said box-like member, said first and second hinge means coupling respective ones of said D-ducts to said box-like member.

Claim 11

The mounting structure of claim 9 wherein said first and second walls terminate and merge at a location adjacent said second transversely oriented plane.

Claim 12

In a structure for mounting a turbofan engine on an aircraft fuselage, said turbofan engine having a high bypass ratio and including a turbine casing housing a turbine engine, the rearward end of a turbine nozzle operably associated with said turbine casing for directing propulsion gases rearwardly from said engine, an annular fan casing surrounding and spaced outwardly from said turbine casing, a low pressure fan mounted within said fan casing and driven by said turbine engine, said fan casing being structurally coupled to said turbine casing, an improved structure for interchangeably mounting said turbofan engine to a plurality of locations on a fuselage comprising: a rigid, arcuate, structural yoke and means for affixing said yoke to the fuselage of an airplane, said yoke extending about a portion of the periphery of said fan casing and being spaced therefrom, said yoke having a central portion, a first end spaced in a first direction from said central portion and a second end spaced in the opposite direction from said central portion, said means for affixing the central portion of said yoke to said fuselage including a beam affixed to said yoke and extending outwardly from said yoke in a radial direction relative to said engine, the outer end of said beam being affixed to said fuselage, each of said first and second ends of said yoke having bores therein, each of said bores having an axis, the axes of said bores intersecting to define a region in a transverse plane relative to said engine bounded by said axes and said yoke, said engine having a center of mass defined by longitudinal and transverse coordinates relative to the centerline of said engine, said axes of said bores being oriented so that said transverse coordinate falls within said region, said longitudinal coordinate being spaced rearwardly from said region relative to said engine, first shock absorbing mounting means associated with the bore in the first end of said yoke for coupling the first end to a first location on the periphery of said fan casing, second shock absorbing mounting means associated with the bore in the second end of said yoke for coupling the second end of said yoke to a second location on the periphery of said fan casing, said second location being spaced from said first location, a mounting arm and means for affixing said arm to the fuselage of an airplane, said arm having an outer end located adjacent said turbine casing and rearwardly from said yoke, said arm extending in a generally radial direction toward said turbofan engine, third shock absorbing mounting means associated with the outer end of said arm for coupling said outer end to said turbine casing, and nacelle means associated with said engine defining an inlet coupled to said fan casing and defining an annular fan duct extending rearwardly from said fan casing for receiving fan air from said fan and directing said fan air rearwardly relative to said engine.

Claim 13

In a structure for mounting a turbofan engine on an aircraft fuselage, said turbofan engine having a high bypass ratio and including a turbine casing housing a turbine engine, the rearward end of a turbine nozzle operably associated with said turbine casing for directing propulsion gases rearwardly from said engine, an annular fan casing surrounding and spaced outwardly from said turbine casing, a low pressure fan mounted within said fan casing and driven by said turbine engine, said fan casing being structurally coupled to said turbine casing, an improved structure for interchangeably mounting said turbofan engine to a plurality of locations on a fuselage comprising: a rigid, arcuate, structural yoke and means for affixing said yoke to the fuselage of an airplane, said yoke extending about a portion of the periphery of said fan casing and being spaced therefrom, said yoke having a central portion, a first end spaced in a first direction from said central portion and a second end spaced in the opposite direction from said central portion, said means for affixing the central portion of said yoke to said fuselage including a beam affixed to said yoke and extending outwardly from said yoke in a radial direction relative to said engine, the outer end of said beam being affixed to said fuselage, each of said first and second ends of said yoke having bores therein, each of said bores having an axis, the axes of said bores intersecting to define a region in a transverse plane relative to said engine bounded by said axes and said yoke, said engine having a center of mass defined by longitudinal and transverse coordinates relative to the centerline of said engine, said axes of said bores being oriented so that said transverse coordinate falls within said region, said longitudinal coordinate being spaced rearwardly from said region relative to said engine, first shock absorbing mounting means associated with the bore in the first end of said yoke for coupling the first end to a first location on the periphery of said fan casing, second shock absorbing mounting means associated with the bore in the second end of said yoke for coupling the second end of said yoke to a second location on the periphery of said fan casing, said second location being spaced from said first location, a mounting arm and means for affixing said arm to the fuselage of an airplane, said arm having an outer end located adjacent said turbine casing and rearwardly from said yoke, said arm extending in a generally radial direction toward said turbofan engine, third shock absorbing mounting means associated with the outer end of said arm for coupling said outer end to said turbine casing, and nacelle means associated with said engine defining an inlet coupled to said fan casing and defining an annular fan duct extending rearwardly from said fan casing for receiving fan air from said fan and directing said fan air rearwardly relative to said engine.

Claim 14

The structure of claim 11 wherein each of said first and second mounting means comprises a cylindrically shaped, resilient element having an axis of revolution, said elements being positioned coaxially within respective ones of said bores, said resilient elements each having a centrally located bore therein, and means affixing each of said resilient elements to said yoke, said fan casing having first and second brackets thereon, said mounting means further comprising first and second rods connected to respective ones of said brackets, said rods extending toward respective ones of said resilient elements and into the respective bores therein, said rods being affixed to respective ones of said resilient elements, said resilient elements thereby resiliently mounting said engine to said yoke.

Claim 15

The structure of claim 12 wherein each of said bores in said resilient elements is frustoconically shaped and has a central axis, said central axis being oriented transversely to the axis of revolution of the respective bores in said yoke, and wherein each of said rods comprises a conically shaped bolt having means on one end thereof for securing said bolt to a respective one said brackets, and means on the other end thereof for securing said bolt to a respective one of said resilient elements.

Claim 16

In a structure for mounting a turbofan engine on an aircraft fuselage, said turbofan engine having a high bypass ratio and including a turbine casing housing a turbine engine, the rearward end of a turbine nozzle operably associated with said turbine casing for directing propulsion gases rearwardly from said engine, an annular fan casing surrounding and spaced outwardly from said turbine casing, a low pressure fan mounted within said fan casing and driven by said turbine engine, said fan casing being structurally coupled to said turbine casing, an improved structure for interchangeably mounting said turbofan engine to a plurality of locations on a fuselage comprising: a rigid, arcuate, structural yoke and means for affixing said yoke to the fuselage of an airplane, said yoke extending about a portion of the periphery of said fan casing and being spaced therefrom, said yoke having a central portion, a first end spaced in a first direction from said central portion and a second end spaced in the opposite direction from said central portion, said means for affixing the central portion of said yoke to said fuselage including a beam affixed to said yoke and extending outwardly from said yoke in a radial direction relative to said engine, the outer end of said beam being affixed to said fuselage, first shock absorbing mounting means associated with the first end of said yoke for coupling the first end to a first location on the periphery of said fan casing, second shock absorbing mounting means associated with the second end of said yoke for coupling the second end of said yoke to a second location on the periphery of said fan casing, said second location being spaced from said first location, a mounting arm and means for affixing said arm to the fuselage of an airplane, said arm having an outer end located adjacent said turbine casing and rearwardly from said yoke, said arm extending in a generally radial direction toward said turbofan engine, third shock absorbing mounting means associated with the outer end of said arm for coupling said outer end to said turbine casing, nacelle means associated with said engine including an outer annular wall and an inner annular wall, said inner annular wall being spaced outwardly from said turbine casing, said inner and outer annular walls defining an inlet coupled to said fan casing and defining an annular fan duct extending rearwardly from said fan casing for receiving fan air from said fan and directing said fan air rearwardly relative to said engine, bifurcation means associated with said annular fan duct for splitting the flow therethrough, said bifurcation means extending longitudinally along said duct from a forward location adjacent said fan to a location rearwardly thereof, said bifurcation means being located in said fan channel adjacent the central portion of said yoke and having a central channel therethrough communicating between the region inside the inner wall of said fan duct and the region outside the outer wall of said fan duct, said arm extending through said central channel, and a fan bleed air collector mounted in the forward portion of said bifurcation means and having an inlet opening forwardly toward said fan, and conduit means coupled to said collector and located within the channel in said bifurcation means and extending therethrough toward said fuselage, said conduit means for receiving fan air from said inlet and directing it to a location in said fuselage.

Claim 17

In a structure for mounting a turbofan engine on an aircraft fuselage, said turbofan engine having a high bypass ratio and including a turbine casing housing a turbine engine, the rearward end of a turbine nozzle operably associated with said turbine casing for directing propulsion gases rearwardly from said engine, an annular fan casing surrounding and spaced outwardly from said turbine casing, a low pressure fan mounted within said fan casing and driven by said turbine engine, said fan casing being structurally coupled to said turbine casing, an improved structure for interchangeably mounting said turbofan engine to a plurality of locations on a fuselage comprising: a rigid, arcuate, structural yoke and means for affixing said yoke to the fuselage of an airplane, said yoke extending about a portion of the periphery of said fan casing and being spaced therefrom, said yoke having a central portion, a first end spaced in a first direction from said central portion and a second end spaced in the opposite direction from said central portion, said means for affixing the central portion of said yoke to said fuselage including a beam affixed to said yoke and extending outwardly from said yoke in a radial direction relative to said engine, the outer end of said beam being affixed to said fuselage, first shock absorbing mounting means associated with the first end of said yoke for coupling the first end to a first location on the periphery of said fan casing, second shock absorbing mounting means associated with the second end of said yoke for coupling the second end of said yoke to a second location on the periphery of said fan casing, said second location being spaced from said first location, a mounting arm and means for affixing said arm to the fuselage of an airplane, said arm having an outer end located adjacent said turbine casing and rearwardly from said yoke, said arm extending in a generally radial direction toward said turbofan engine, third shock absorbing mounting means associated with the outer end of said arm for coupling said outer end to said turbine casing, nacelle means associated with said engine including an outer annular wall and an inner annular wall, said inner annular wall being spaced outwardly from said turbine casing, said inner and outer annular walls defining an inlet coupled to said fan casing and defining an annular fan duct extending rearwardly from said fan casing for receiving fan air from said fan and directing said fan air rearwardly relative to said engine, bifurcation means associated with said annular fan duct for splitting the flow therethrough, said bifurcation means extending longitudinally along said duct from a forward location adjacent said fan to a location rearwardly thereof, said bifurcation means being located in said fan channel adjacent the central portion of said yoke and having a central channel therethrough communicating between the region inside the inner wall of said fan duct and the region outside the outer wall of said fan duct, said arm extending through said central channel, and a fan bleed air collector mounted in the forward portion of said bifurcation means and having an inlet opening forwardly toward said fan, and conduit means coupled to said collector and located within the channel in said bifurcation means and extending therethrough toward said fuselage, said conduit means for receiving fan air from said inlet and directing it to a location in said fuselage.