Abstract: An impingement cooling system for a gas turbine engine includes an initial impingement surface (10) with a centrally located opening (12). A plurality of channels (14) and plurality of sub-channels (22) extends radially outward from the opening (12) and are formed by a plurality of fixtures (16) and plurality of sub-fixtures (24) that each separates each adjacent channel (14) and sub-channel (22) respectively. The plurality of fixtures (16) and plurality of sub-fixtures (24) each have a rounded upstream end (18) in a plane parallel relative to the initial impingement surface (10). The plurality of fixtures (16) and the plurality of sub-fixtures (24) each have a concave shape along a middle portion (54, 56) of the fixture (16) and sub-fixture (24) along an axis perpendicular to the initial impingement surface (10).

Abstract: An impingement cooling system for a gas turbine engine includes an initial impingement surface (10) with a centrally located opening (12). A plurality of channels (14) and plurality of sub-channels (22) extends radially outward from the opening (12) and are formed by a plurality of fixtures (16) and plurality of sub-fixtures (24) that each separates each adjacent channel (14) and sub-channel (22) respectively. The plurality of fixtures (16) and plurality of sub-fixtures (24) each have a rounded upstream end (18) in a plane parallel relative to the initial impingement surface (10). The plurality of fixtures (16) and the plurality of sub-fixtures (24) each have a concave shape along a middle portion (54, 56) of the fixture (16) and sub-fixture (24) along an axis perpendicular to the initial impingement surface (10).

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of doped nanostructures. The phononic regions modify the behavior of the phonons and control heat conduction.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of anisotropic nanostructures that are oriented in different directions than the bulk of the material forming the gas turbine engine component. The phononic regions modify the behavior of the phonons and manage heat conduction.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of alloys or allotropes of the material. The phononic regions modify the behavior of the phonons and control heat conduction.

Abstract: A ring segment system (100) for a gas turbine engine (10) is disclosed. The ring segment system (100) may be formed from ring segments (50) that circumferentially surround a rotor assembly (40). The ring segments (50) may each include a carrier portion (34) that is coupled to a vane carrier (28), and a heat shielding portion (38) that is detachably coupled to the carrier portion (34). The detachable coupling may allow the heat shielding portion (38) to be uncoupled from the carrier portion (34) and removed from the gas turbine engine (10) axially. The ring segments (50) may further include cooling fluid supply channels (72) that allow cooling fluid to flow from a radially outward facing backside (42) of the ring segments (50) to a radially inward facing front side (46). Additionally, the ring segments (50) may also include ingestion prevention channels (76) that allow cooling fluid to create a barrier over the gap (80) between the ring segments (50) and the adjacent vane (18).

Abstract: A turbine abradable component includes a support surface and a thermally sprayed ceramic/metallic abradable substrate coupled to the support surface for orientation proximal a rotating turbine blade tip circumferential swept path. An elongated pixelated major planform pattern (PMPP) of a plurality of discontinuous micro surface features (MSF) project from the substrate surface. The PMPP repeats radially along the swept path in the blade tip rotational direction, for selectively directing airflow between the blade tip and the substrate surface. Each MSF is defined by a pair of first opposed lateral walls defining a width, length and height that occupy a volume envelope of 1-12 cubic millimeters. The PMPP arrays of MSFs provide airflow control of hot gasses in the gap between the abradable surface and the blade tip with smaller potential rubbing surface area than solid projecting ribs with similar planform profiles.

Abstract: A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes a cooling fluid supply trench having an open top portion and extending radially inwardly from a central recessed portion of the panel. The cooling system further includes a plurality of cooling fluid passages extending from the cooling fluid supply trench to a leading edge and/or a trailing edge of the panel. The cooling fluid passages receive cooling fluid from the cooling fluid supply trench, wherein the cooling fluid provides convective cooling to the panel as it passes through the cooling fluid passages.

Abstract: A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes an elongated intermediate plenum extending parallel to leading and trailing edges of the ring segment, and is located radially between an inner side of the panel and a hook structure extending from an outer side of the panel. A plurality of cooling fluid feed passages supply cooling fluid to the intermediate plenum, and a plurality of convective cooling passages extend through the panel from the intermediate plenum to one of the leading and trailing edges for cooling the inner side of the panel. The intermediate plenum is located in axial alignment with and defines an area of reduced thermal mass receiving impingement cooling adjacent to the hook structure.

Abstract: A method to estimate the fatigue life of a component operable under cyclic stress is provided. A system including testing device for performing a strain controlled test of a component or a representative specimen of the component, to obtain therefrom a first set of data samples including measured stress amplitude values for varying applied strain levels, and a second set of data samples including measured number of cycles to crack initiation for varying applied strain levels is also provided. The system further includes a modeling device for fitting a first low cycle fatigue material curve on the first set of data samples and a second low cycle fatigue material curve on the second set of data samples.

Abstract: A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes a cooling fluid supply trench having an open top portion and extending radially inwardly from a central recessed portion of the panel. The cooling system further includes a plurality of cooling fluid passages extending from the cooling fluid supply trench to a leading edge and/or a trailing edge of the panel. The cooling fluid passages receive cooling fluid from the cooling fluid supply trench, wherein the cooling fluid provides convective cooling to the panel as it passes through the cooling fluid passages.

Abstract: A method to estimate the fatigue life of a component operable under cyclic stress is provided. A system including testing means for performing a strain controlled test of a component or a representative specimen of the component, to obtain therefrom a first set of data samples including measured stress amplitude values for varying applied strain levels, and a second set of data samples including measured number of cycles to crack initiation for varying applied strain levels is also provided. The system further includes a modeling means for fitting a first low cycle fatigue material curve on the first set of data samples and a second low cycle fatigue material curve on the second set of data samples.