A gas turbine includes a housing and an outer sealing ring. In an assembled state of the housing and the outer sealing ring, a first planar structure of the outer sealing ring is axially moveable with respect to a second planar structure of the housing against a direction of flow through the gas turbine.

A gas turbine engine includes a fan shaft that drives a fan that has fan blades. An outer housing surrounds the fan. A bypass flow path is within the outer housing. A fan shaft support that supports the fan shaft defines a fan shaft support transverse stiffness. A gear system is connected to the fan shaft. The gear system includes a gear mesh that defines a gear mesh transverse stiffness. A flexible support which supports the gear system relative to a static structure defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 11% of the fan shaft support transverse stiffness. The flexible support transverse stiffness is less than 8% of the gear mesh transverse stiffness.

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. The fan delivers airflow to a bypass duct. A fan shaft support supports the fan shaft and defines a support transverse stiffness. A gear system is connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and the flexible support transverse stiffness is less than 20% of the fan shaft support transverse 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.

An assembly for a gas turbine engine includes a first casing, a second casing, and struts extending from the first casing to support the second casing. The assembly further includes a fairing and a multi-piece heat shield assembly. The fairing is disposed between the first casing and the second casing and around each of the struts. The multi-piece heat shield assembly includes a first shield extending between the first casing and the fairing, and a second shield extending between the fairing and the first casing. The multi-piece heat shield assembly further includes a third shield extending between the fairing and the second casing, and fourth and fifth heat shields extending from the third heat shield between the fairing and each of the struts.

A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.

An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.

The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism (80) in a friction fit, and a plurality of ring segments (20.sub.i, 20.sub.1+1), wherein .[.a free axial path length (a.sub.f) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a.sub.1) of a rotation locking member (10) of the outer sealing ring (a.sub.fa.sub.1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a.sub.2) of a radial mounting rail (23) of the outer sealing ring (a.sub.fa.sub.2), and/or an axial offset (a.sub.3, a.sub.4) of a sealing fin (31, 41); and/or.]. a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit .Iadd.and pi is at least as large as a difference between a maximum outer diameter of the outer sealing ring and a minimum inner diameter of the flow channel inlet of the housing.Iaddend..

A method using a gas reservoir and a critical nozzle for determining physical properties and/or quantities relevant to combustion of gas or gas mixtures, the method includes: flowing a gas or gas mixture under pressure from the gas reservoir through the critical nozzle; measuring pressure drop in the gas reservoir as a function of time; determining a gas property factor (*), dependent on physical properties of the gas or gas mixture, based on the measured values of the pressure drop; and determining a desired physical property or quantity relevant to combustion based on the gas property factor (*) through correlation.

An apparatus for extracting power includes a track and an airfoil coupled to the track. The track includes first and second elongate sections, where the first elongate section is positioned above the second elongate section. The airfoil is moveable in opposite directions when alternately coupled to the first elongate section and second elongate section.