Abstract: The present invention relates to novel trispecific heterodimeric immunoglobulins. More specifically the present invention relates to trispecific heterodimeric immunoglobulins that target human CD3 antigen, human BCMA and human CD38 antigen. The present invention also relates to this novel class of trispecific heterodimeric immunoglobulins for use in the treatment of proliferative diseases and in particular cancers such as hematological cancer. The present invention relates to novel trispecific antibody for use in treating multiple myeloma.

Abstract: A fluid source management system (100) comprising a structure (101) that supports one or more fluid sources (103), sensors (102) that determine the fluid state of the fluid sources (103), at least one common reservoir (108) for storing the fluid, tubing (104) connecting the fluid sources (103) to the common fluid reservoir (108) and a controller (105) that controls the opening and closing of the tubing (104) based upon the fluid state of the fluid sources (103).

Abstract: A method of predicting the responsiveness of a subject with cancer to treatment with a modulator of the HER signalling pathway, wherein the method comprises detecting the level of expression of EGR4-S in a sample of the subject, wherein the subject is likely to be responsive to treatment with the modulator of the HER signalling pathway if EGR4-S expression is at or above a predetermined level in the sample of the subject, and wherein the subject is likely to be resistant to treatment with the modulator of the HER signalling pathway if EGR4-S expression is at or below a predetermined level in the sample of the subject.

Abstract: A brush seal is provided that includes a top plate, a back plate, and a bristle pack. The bristle pack is secured at a joint between the top plate and the back plate. The bristle pack includes a first bristle set extending from the joint, a second bristle set extending from the joint, and a sliding backing plate. The sliding backing plate includes a sliding portion and a support portion. The sliding portion is disposed contiguous with the second bristle set. The support portion has an inner face and a support face. The inner face is in contact with a distal end of the second bristle set. The support face is configured to support at least a portion of the first bristle set. The sliding backing plate is configured to slide relative to the second bristle set.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the second seal section and bias the first and second seal sections away from one another.

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the second seal section and bias the first and second seal sections away from one another.

Abstract: An on-board injector for delivering discharge air toward a turbine rotor of a gas turbine engine. The on-board injector having: a first wall; a second wall spaced from said first wall to define an annular inlet and an annular exit, wherein the first wall has a first length and the second wall has a second length; and a plurality of airfoils extending between the first wall and the second wall to segregate discharge air from the annular inlet, wherein each of the plurality of airfoils extend from the annular inlet and the annular exit and completely across the first length and the second length.

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

Abstract: A gas turbine engine includes a stator vane. A blade outer air seal may be adjacent to the stator vane. A seal assembly may be disposed between the blade outer air seal and the stator vane. The seal assembly may include a first seal disposed between a first airflow path and a second airflow path. A second seal may be disposed between the first airflow path and the second airflow path. The second seal may be disposed in a series arrangement with the first seal.

Abstract: A sealing assembly for a gas turbine engine includes a case, a support arm, a carrier, a vane, a seal, and a gasket. The support arm is connected to and extending radially inward from the case. The carrier is connected to an end of the support arm. A portion of the vane is disposed downstream of the carrier. A portion of the seal is disposed within the carrier. The gasket is disposed adjacent to and abutting the seal. The gasket is also positioned partially between the seal and the carrier and partially between the seal and the vane.

Abstract: A brush seal is provided that includes a top plate, a back plate, and a bristle pack. The bristle pack is secured at a joint between the top plate and the back plate. The bristle pack includes a first bristle set extending from the joint, a second bristle set extending from the joint, and a sliding backing plate. The sliding backing plate includes a sliding portion and a support portion. The sliding portion is disposed contiguous with the second bristle set. The support portion has an inner face and a support face. The inner face is in contact with a distal end of the second bristle set. The support face is configured to support at least a portion of the first bristle set. The sliding backing plate is configured to slide relative to the second bristle set.

Abstract: A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.

Abstract: Aspects of the disclosure are directed to a seal comprising: a first leg that emanates from a center point of the seal and is configured to contact a first component, a second leg that emanates from the center point and is configured to contact a second component that is operative at a temperature that is within a range of 648 degrees Celsius to 1093 degrees Celsius, and a third leg that emanates from the center point.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the second seal section and bias the first and second seal sections away from one another.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the second seal section and bias the first and second seal sections away from one another.

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a substantially radially extending rail and a substantially axially extending leg, such that the seal has a substantially J-shaped cross-section.

Abstract: A method of assembling a gas turbine engine is provided that includes locating a consumable assembly tool within the engine. The consumable assembly tool is attached to another component of the gas turbine engine. The engine is run to vaporize the consumable assembly tool.

Abstract: A sealing assembly for a gas turbine engine includes a case, a support arm, a carrier, a vane, a seal, and a gasket. The support arm is connected to and extending radially inward from the case. The carrier is connected to an end of the support arm. A portion of the vane is disposed downstream of the carrier. A portion of the seal is disposed within the carrier. The gasket is disposed adjacent to and abutting the seal. The gasket is also positioned partially between the seal and the carrier and partially between the seal and the vane.