A method for operating a gas turbine engine (10), including a first compressor (14), a second compressor (16), and a turbine (20), coupled together in serial flow arrangement. The method includes channeling compressed airflow (53) discharged from the first compressor through an intercooler (50) having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet (26,30) of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.

Methods and apparatus for operating gas turbine engines

A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).

Mounting apparatus for low-ductility turbine shroud

A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

Turbine ring assembly

A hybrid seal for sealing the circumferential gap (11) between a first machine component and a second machine component comprises at least one shoe (16) extending along one of the machine components in a position to create a non-contact seal, at least one spring element (24) connected between one of the machine components and the shoe (16) and a stack of sealing elements (48, 50) located within a slot (22) formed in the shoe (16) wherein a primary seal and secondary seal of the circumferential gap (11) is created by the shoe (16) in cooperation with the spring element (24) and sealing elements (48, 50) respectively

Seal with stacked sealing elements

A blade outer air seal in a gas turbine engine, the BOAS includes a plurality of ring segments secured to a blade ring carrier. An impingement ring forms a pressure vessel within the blade ring carrier and includes a first group of impingement holes positioned over the middle of the blade tip. The ring segments each include a plurality of stiffener ribs forming a plurality of leading edge pockets, trailing edge pocket and middle pockets each with pin fins to enhance the heat transfer effect. A metering plate is secured over the stiffener ribs to form closed pockets over the edge pockets while leaving the middle pockets open. A second group of impingement holes are formed in the metering plate over the edge pockets. Pressurized cooling air supplied to the pressure vessel first passes through the first group of impingement holes and is discharged directly over the middle pockets. The cooling air then flows through the second group of impingement holes and into the closed edge pockets, and then out discharge holes arranged along the leading and trailing edges of the ring segment. The individual pockets can have the impingement holes of varying sizes in order to regulate the amount of cooling air that flows into the specific pocket.

Segmented ring for an industrial gas turbine

The invention concerns a shroud stay sector (14) for minimising working clearances (J) between the summit of the blades (3) and the ring (12) of the high-pressure turbine and mounting clearances of the shroud stay sectors (14) on the high-pressure turbine housing (1). Each shroud stay sector (14) has upstream a tab (20) comprising an end (21) supported on the inner wall (1l) of the high-pressure turbine housing (1) thereby producing a close contact between the parts fixing said shroud stay sector (14) with the corresponding parts of the high-pressure turbine. The invention is applicable to gas turbine engines equipping aircraft.

Stay sector of stator shroud of the high-pressure turbine of a gas turbine engine with clearance control

Le secteur d'entretoise support (14) permet de minimiser les jeux (J) de fonctionnement entre le sommet des pales (3) et l'anneau (12) de la turbine haute pression et les jeux de montage des secteurs d'entretoise de support (14) sur le carter de turbine haute pression (1). The spacer sector carrier (14) minimizes the sets (J) of operation between the vertex of the blades (3) and the ring (12) of the high pressure turbine and the assembly clearances of the spacer sectors support (14) on the high pressure turbine housing (1). Chaque secteur d'entretoise de support (14) possede en amont une languette (20) possedant une extremite (21) s'appuyant sur la paroi interne (1I) du carter de turbine haute pression (1) creant ainsi un contact intime entre les parties de fixation de ce secteur d'entretoise de support (14) avec les parties correspondantes du carter de turbine haute pression (1). Each support spacer sector (14) has upstream a tongue (20) having one end (21) bearing on the inner wall (1I) of the high pressure turbine casing (1) thereby creating an intimate contact between the securing portions of the support spacer sector (14) with the corresponding parts of the high pressure turbine housing (1). Application aux turbomachines equipant les aeronefs. Application to Turbomachinery equipping the aircraft.

Support strut for the stator ring of the high-pressure turbine of a turbomachine provided with clearance compensation

Le secteur d'entretoise support (14) permet
de minimiser les jeux (J) de fonctionnement entre le
sommet des pales (3) et l'anneau (12) de la turbine
haute pression et les jeux de montage des secteurs
d'entretoise de support (14) sur le carter de turbine
haute pression (1). Chaque secteur d'entretoise de support (14)
possede en amont une languette (20) possedant une
extremite (21) s'appuyant sur la paroi interne (1I) du
carter de turbine haute pression (1) creant ainsi un
contact intime entre les parties de fixation de ce
secteur d'entretoise de support (14) avec les parties
correspondantes du carter de turbine haute pression
(1). Application aux turbomachines equipant les
aeronefs.

Jean-Baptiste Arilla

Papers

Stay sector of stator shroud of the high-pressure turbine of a gas turbine engine with clearance control

Support strut for the stator ring of the high-pressure turbine of a turbomachine provided with clearance compensation

Secteur d"entretoise de support d"anneau de stator de la turbine haute pression d"une turbomachine avec rattrapage de jeux