A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a circumferential array of blades, a low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area and a low pressure turbine section. The low pressure turbine section includes a maximum gas path radius, the blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the blades is equal to or greater than 0.35, and is less than 0.55.

A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a high pressure compressor section and a low pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the low pressure compressor section inlet, and a turbine having a high pressure turbine section and a low pressure turbine section driving the fan through a speed reduction mechanism, wherein the low pressure turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a low pressure compressor section and a high pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the a low pressure compressor section inlet, a turbine in fluid communication with the combustor, the turbine having a high pressure turbine section and a low pressure turbine that drives the fan, a speed reduction mechanism coupled to the fan and rotatable by the low pressure turbine section to allow the low pressure turbine section to turn faster than the fan, wherein the low pressure turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is between 0.50 and 0.55, or is greater than 0.55 and less than or equal to 0.65.

An airfoil member having a root end, a tip end, a leading edge, and a trailing edge, the airfoil member including an upper skin; a lower skin; and a support network having a plurality of interconnected support members in a lattice arrangement and/or a reticulated arrangement, the support network being configured to provide tailored characteristics of the airfoil member. Also provided are methods and systems for repairing an airfoil member.

As underwater pumped storage power plant reservoir in a dry but floodable ground depression, comprises a modular arrangement of several individual pressure vessel modules for the intermediate storage of electrical energy from other power plants, wherein the pressure vessel modules each have an outer wall with at least one flow-through opening for letting in and/or letting out water and can each be filled with water and/or pumped empty independently of one another when the dry ground depression is flooded with water, and wherein the modular arrangement of the pressure vessel modules is designed in such a way that the pressure vessel modules are arranged with respect to one another in the dry ground depression with their outer wall face-to face adjacent to one another.

An acoustic core includes an array of resonant cells. The array may include a plurality of coupled resonant cells respectively defining an antecedent resonant space and a subsequent resonant space, with at least one cell wall having one or more wall-apertures defining a pathway between the antecedent resonant space and the subsequent resonant space. The array may include a plurality of high-frequency resonant cells respectively defining a high-frequency resonant space and being matched with respective ones of the plurality of coupled resonant cells. A cross-sectional dimension of the one or more wall-apertures defining the pathway between the antecedent resonant space and the subsequent resonant space may be less than a cross-sectional dimension of the antecedent resonant space and/or a cross-sectional dimension of the subsequent resonant space. The array may include a plurality of partitioned resonant cells that have a partition integrally formed with at least one of a corresponding one or more cell walls and transecting the corresponding resonant space with at least one surface of the partition having an interface angle that is oblique or perpendicular relative to a plane parallel to a top face and/or a bottom face of the array of resonant cells.

A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a first compressor section and a second compressor section, the second compressor section including a second compressor section inlet with a compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, and a turbine having a first turbine section driving the first compressor section, a second turbine section driving the fan through an epicyclic gearbox, the second turbine section including blades and vanes, and wherein the second turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

The invention relates to a concrete construction of modular design, comprising at least two upright precast concrete wall elements (7, 7′, . . . , 7″′) which are arranged next to one another and, where appropriate, above one another and have two narrow sides, an upper and a lower side and a front and a rear side, wherein a first honeycomb support (1) is anchored in one of the narrow sides and the opposite narrow side has a recess or depression (8) in which a further honeycomb support (1′) is anchored in such a way that, when mounting the narrow sides of the two precast concrete wall elements (7, 7′), the two honeycomb supports (1, 1′) can be connected by connecting means (9) with the formation of the vertical joint (16).

Provided is an aerodynamic structure for mounting to a surface of a wind turbine rotor blade, which aerodynamic structure includes a number of comb elements, a comb element including comb teeth arranged in a comb plane, wherein the comb plane of a mounted comb element is essentially perpendicular to the trailing edge of the rotor blade and to the airfoil surface of the rotor blade. A wind turbine rotor blade including at least one such aerodynamic structure, and a method of equipping a wind turbine rotor blade with such an aerodynamic structure, is also provided.

Provided is an aerodynamic structure for mounting to a surface of a wind turbine rotor blade, which aerodynamic structure includes a plurality of rectangular comb elements and/or a plurality of angular comb elements, wherein a comb element includes comb teeth arranged in a comb plane that subtends an angle to the surface of the rotor blade. The embodiments further describe a wind turbine rotor blade including such an aerodynamic structure.