A gas turbine engine includes a propulsor and a fan drive turbine. The fan drive turbine drives the propulsor through a geared architecture. The geared architecture includes a sun gear, a ring gear, and intermediate gears supported on journal support pins. The sun gear engages the intermediate gears and the intermediate gears engages the ring gear. The journal support pins include a titanium body and an outer surface outside of the titanium body that has a surface hardness that is harder than the titanium body. The outer surface is provided by a steel sleeve. Oil supply holes extend from a central bore in the titanium body through the steel sleeve. At least one pin extends through the steel sleeve to secure the steel sleeve to the titanium body.

A gas turbine engine includes a propulsor and a fan drive turbine. The fan drive turbine drives the propulsor through a geared architecture. The geared architecture includes a sun gear, a ring gear, and intermediate gears supported on journal support pins. The sun gear engages the intermediate gears and the intermediate gears engages the ring gear. The journal support pins include a titanium body and an outer surface outside of the titanium body that has a surface hardness that is harder than the titanium body. The outer surface is provided by a steel sleeve. Oil supply holes extend from a central bore in the titanium body through the steel sleeve. At least one pin extends through the steel sleeve to secure the steel sleeve to the titanium body.

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.

A planetary gearbox includes a planet carrier, with a planetary gear rotatably disposed on the planet carrier, and a gear that meshes with the planetary gear, as well as a gas turbine engine having such a planetary gearbox. The planet carrier has an oil supply installation including a supply line for oil to an opening. The oil is directed out of the opening in the direction of the planetary gear and/or the gear. The oil supply installation in relation to a primary rotating direction of the planetary gear and/or the gear in front of the opening includes a shielding region which protrudes from an external side of the oil supply installation and which by way of the external side of the oil supply installation on a side that faces the primary rotating direction of the planetary gear and/or the gear, delimits an oil collection groove.

A planetary gearbox includes a planet carrier, with a planetary gear rotatably disposed on the planet carrier, and a gear that meshes with the planetary gear, as well as a gas turbine engine having such a planetary gearbox. The planet carrier has an oil supply installation including a supply line for oil to an opening. The oil is directed out of the opening in the direction of the planetary gear and/or the gear. The oil supply installation in relation to a primary rotating direction of the planetary gear and/or the gear in front of the opening includes a shielding region which protrudes from an external side of the oil supply installation and which by way of the external side of the oil supply installation on a side that faces the primary rotating direction of the planetary gear and/or the gear, delimits an oil collection groove.

Methods, apparatus, systems and articles of manufacture are disclosed to methods and apparatus for gas turbine bending isolation. An example mechanical interface to couple a first section of a gas turbine to a second section of the gas turbine, the mechanical interface comprising a first mating surface disposed on the first section, and a second mating surface disposed on the second section and circumferentially around the first mating surface, wherein the coupling of the first mating surface to the second mating surface enables the first section to rotate about the mechanical interface during operation of the gas turbine.

Methods, apparatus, systems and articles of manufacture are disclosed to methods and apparatus for gas turbine bending isolation. An example mechanical interface to couple a first section of a gas turbine to a second section of the gas turbine, the mechanical interface comprising a first mating surface disposed on the first section, and a second mating surface disposed on the second section and circumferentially around the first mating surface, wherein the coupling of the first mating surface to the second mating surface enables the first section to rotate about the mechanical interface during operation of the gas turbine.

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.46-3.76 inch (87.8-95.5 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.98-2.28 inch (50.2-57.8 mm). The airfoil element includes at least one of a first mode with a frequency of 1056 ± 10% Hz and a second mode with a frequency of 1582 ± 10% Hz.

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.46-3.76 inch (87.8-95.5 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.98-2.28 inch (50.2-57.8 mm). The airfoil element includes at least one of a first mode with a frequency of 1056 ± 10% Hz and a second mode with a frequency of 1582 ± 10% Hz.