A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. Each of the inner seals includes a wing extending radially inward at an oblique angle. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first wing extending radially outward at an oblique angle and a second wing extending radially outward at an oblique angle, the first wing of the side seal sealingly interfaces with the wing of the first inner seal and the second wing of the side seal sealingly interfaces with the wing of the second inner seal.

A panel for a combustor of a gas turbine engine includes a cold side defining at least one convex portion and at least one concave portion. The concave portion is in communication with a passage. A method of operating a combustor section of a gas turbine engine includes: directing an impingement flow toward a multiple of peaks on a cold side of a panel; directing the impingement flow from the multiple of peaks toward a multiple of troughs with a multiple of entrances on the cold side of the panel; and directing the impingement flow through the multiple of entrances and a respective multiple of effusion passages through the panel.

An exhaust system for a gas turbine engine, such as an APU, comprises a pressure vessel having an annular wall circumscribing an exhaust plenum. The annular wall is composed of an arrangement of individual tubes assembled side-by-side around a central axis of the exhaust plenum. The tubes are fed with pressurized cooling air, such as P3 air. A heat exchanger in heat transfer relationship with the exhaust gases flowing through the exhaust plenum receives air from the tubes. The heat transferred from the exhaust gases to the air circulated through the heat exchanger may be used to provide pre-heated air to the engine combustor.

The present disclosure relates to systems and methods useful for power production. In particular, a power production cycle utilizing CO.sub.2 as a working fluid may be combined with a second cycle wherein a compressed CO.sub.2 stream from the power production cycle can be heated and expanded to produce additional power and to provide additional heating to the power production cycle.

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a compressor section including at least a first compressor section and a second compressor section. A power ratio is provided by the combination of the first compressor section and the second compressor section. A method of design a gas turbine engine is also disclosed.

The joint use of a C3 to C6 alkene compound comprising a sole double bond and of at least one molecular sieve for limiting or preventing the isomerization of trans-1-chloro-3,3,3-trifluoropropene to cis-1-chloro-3,3,3-trifluoropropene, and/or for limiting or preventing the degradation of trans-1-chloro-3,3,3-trifluoropropene. Also, a method for heating or cooling a fluid or a body, to a method for producing electricity and to a heat transfer installation.

The joint use of a C3 to C6 alkene compound comprising a sole double bond and of at least one molecular sieve for limiting or preventing the isomerization of trans-1-chloro-3,3,3-trifluoropropene to cis-1-chloro-3,3,3-trifluoropropene, and/or for limiting or preventing the degradation of trans-1-chloro-3,3,3-trifluoropropene. Also, a method for heating or cooling a fluid or a body, to a method for producing electricity and to a heat transfer installation.

A method for energy conversion from pressure energy into electrical energy uses an expansion turbine. In the method, a pressurized, gaseous, first medium is heated before being fed into the expansion turbine. The expansion turbine drives a generator and a compressor. At least one gaseous second medium is compressed by the compressor in a heating arrangement. Heat generated by the compression and preferably also via utilization of ambient heat according to a heat exchanger principle is used for heating the gaseous first medium.

A component of a gas turbine engine having: an internal cooling cavity; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; at least one separating feature located between a pair of ends of a pair of the plurality of trip strips, wherein the plurality of trip strips and the at least one separating feature are spaced from an interior surface of the internal cooling cavity; a plurality of trip strips extending upwardly from the interior surface; and at least one separating feature located between a pair of ends of the plurality of trip strips located on the interior surface of the internal cooling cavity, wherein the plurality of trip strips and the at least one separating feature of the interior surface are spaced from the exterior surface of the baffle insert.

The present disclosure relates to systems and methods useful for power production. In particular, a power production cycle utilizing CO.sub.2 as a working fluid may be combined with a second cycle wherein a compressed CO.sub.2 stream from the power production cycle can be heated and expanded to produce additional power and to provide additional heating to the power production cycle.