Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an assembly axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. A retention clip has an intermediate portion connecting a first leg portion and a second leg portion. The intermediate portion is compressible to position the first and second leg portions in the pair of airfoil openings such that the retention clip limits movement of the airfoil relative to the first shroud.

Abstract: A stator assembly of a gas turbine engine according to an example of the present disclosure includes, among other things, a first shroud extending about an assembly axis to bound a flow path. The first shroud defines a first shroud opening. An airfoil has an airfoil body extending from a first end portion. The first end portion is received in the first shroud opening and defines a pair of airfoil openings. A retention clip has an intermediate portion connecting a first leg portion and a second leg portion. The intermediate portion is compressible to position the first and second leg portions in the pair of airfoil openings such that the retention clip limits movement of the airfoil relative to the first shroud.

Abstract: An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.

Abstract: A fixture for assembling a stator vane assembly for a gas turbine engine includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing. An inner locating ring includes a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin defining an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings. An inner locating section supports a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.

Abstract: An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.

Abstract: An example method of assembling a turbomachine airfoil array includes, among other things, securing a partial airfoil array within a fixture, the partial airfoil array having at least one existing airfoil extending radially between an inner and an outer fairing and an open area where at least one existing airfoil has been removed. The method includes mounting a positioning saddle relative to a base of the fixture, the positioning saddle aligned with the open area, holding a replacement airfoil using the positioning saddle, applying a curable material at an interface between the replacement airfoil and the inner and outer fairing, and curing the curable material while maintaining a relative position between the replacement airfoil and the inner and outer fairing.

Abstract: A fixture for assembling a stator vane assembly of a gas turbine engine includes a base which defines a multiple of locators to position each of a multiple of vanes relative to an outer fairing and an inner fairing. A first tangential wedge clamp is receivable in a first aperture located within the base for each of the multiple of vanes. A second tangential wedge clamp is receivable in a second aperture located within the base for each of the multiple of vanes.

Abstract: An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots. The OD shroud is positioned radially outward from the ID shroud. A first stator airfoil extends from the ID shroud to the OD shroud. The first stator airfoil is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A first end of the first stator airfoil has one of a raised tab and an indented notch.

Abstract: A fixture for assembling a stator vane assembly for a gas turbine engine includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing. An inner locating ring includes a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin defining an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings. An inner locating section supports a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.

Abstract: A disclosed fixture for assembling a stator vane assembly for a gas turbine engine includes an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing and an inner locating ring including a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin that define an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings, and an inner locating section supporting a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.

Abstract: A method of assembling gas turbine engine front architecture includes positioning inner and outer fairings relative to one another. Multiple vanes are arranged circumferentially between the inner and outer fairings. A liquid sealant is applied around a perimeter of the vanes to seal between the vanes and at least one of the fairings.

Abstract: An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots. The OD shroud is positioned radially outward from the ID shroud. A first stator airfoil extends from the ID shroud to the OD shroud. The first stator airfoil is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A first end of the first stator airfoil has one of a raised tab and an indented notch.

Abstract: A fixture for assembling a stator vane assembly of a gas turbine engine includes a base which defines a multiple of locators to position each of a multiple of vanes relative to an outer fairing and an inner fairing. A first tangential wedge clamp is receivable in a first aperture located within the base for each of the multiple of vanes. A second tangential wedge clamp is receivable in a second aperture located within the base for each of the multiple of vanes.

Abstract: A disclosed fixture for assembling a stator vane assembly for a gas turbine engine includes an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing and an inner locating ring including a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin that define an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings, and an inner locating section supporting a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.

Abstract: A method of assembling gas turbine engine front architecture includes positioning inner and outer fairings relative to one another. Multiple vanes are arranged circumferentially between the inner and outer fairings. A liquid sealant is applied around a perimeter of the vanes to seal between the vanes and at least one of the fairings.

Abstract: A stator assembly having an inner shroud assembly formed of an inner shroud and rubstrip is disclosed. Various construction details and features are developed which relate to durability and manufacturing feasibility are developed. In one detailed embodiment, at the rubstrip is bonded to the thermoplastic shroud. The method is applicable to joining an elastomer, such as silicone rubber material, to a thermoplastic substrate.