Rolls-royce Corporation

Hewlett-packard Development Company, L.p.

Hewlett-packard Company

Mark John Simms

Simon James Jones

Kevin Paul Self

Charles D Smith

Stewart R Wyatt

Julie Catherine Hogan

David J Van Maren

Paul Frederick Bartlett

Paul Antony Davis

R Alexis Takasugi

Andrew James Hurst

Steve Jerman

Fintan Buckley

Robert J Lang

Paula D Repman

Katherine Sophia Piggott

Kimberly K Kroll

Thomas Carter

Edward J Smith

Brad W Culp

Ladawan Johnson

An air cooled component for a turbine stage of a gas turbine engine, comprising: a main body having radially inner main gas path wall and a cooling chamber, the main gas path wall separating the main gas path of the turbine stage and the cooling chamber; at least one flange extending from the main body; a cooling cavity enclosed within the flange; and, an inlet conduit extending between and fluidically connecting the cavity and cooling chamber.

Air cooled component for a gas turbine engine

A wall arrangement for the main gas path of a gas turbine engine, including: a wall segment which defines the main gas path, the wall segment having a gas path side, an outboard side and a support wall extending from the outboard side towards a supporting structure, and a channel member abutting the support wall and having one or more channels defined by the abutment of the support wall and channel member, the one or more channel having radially separated inlet and outlet.

Wall cooling arrangement for a gas turbine engine

There is described a core for an investment casting process, comprising: a core passage which extends between a first point and a second point along a tortuous path having length L, wherein the first point and second point are separated by a direct line of sight distance, S, wherein L is greater than S; and, a core bridge which extends between the first and second points away from the core passage.

Core for an investment casting process

A gas turbine, including: axially adjacent first and second components each having a gas path facing surface within an engine casing, inter-component cavity located between first and second components on the gas path outboard side, an axial-restrictor within the inter component cavity for restricting movement of the first or second component relative to at least one other first and second component or engine casing, wherein the axial-restrictor is radially located in the engine casing or other first and second component and includes a radially facing surface; a retaining element, including a body having circumferential length extending around the gas turbine engine and axial length extending between axially adjacent first and second components when in use; an obstructing portion between the radially facing surface of the axial-restrictor and opposing second radial surface of the other first or second component or engine casing to restrict radial movement of in use axial-restrictor.

Shroud segment retainer

Described is an abradable component for a gas turbine engine that includes a base having an outboard side which receives a supply of cooling air in use and an inboard side with a plurality of walls thereon. The walls intersect one another to define an abradable network of open faced cells on a gas washed surface thereof, and at least one of the walls includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use.

Abradable liner for a gas turbine engine

Described is a shroud arrangement for a gas turbine engine, comprising: a seal segment for bounding a hot gas flow path within the gas turbine engine, the seal segment being attached to a casing of the engine via at least one fore attachment and at least one aft attachment, the fore and aft attachment restricting radial movement of the seal segment relative to the engine casing; and, an axial restrictor which prevents axial movement of the seal segment relative to the engine casing, the axis being the principal rotational axis of the engine, wherein the fore and aft retention features are slidably engaged with a carrier segment or engine casing from a common direction. Also described is a gas turbine engine having the shroud arrangement.

Shroud arrangement for a gas turbine engine

A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine, including: a plate having an inboard hot gas flow path facing side and an outboard side; a bulkhead extending from the outboard side of the plate which defines a fore portion and an aft portion; a first cooling circuit within the plate for cooling a first portion of the plate; a second cooling circuit within the plate for cooling a second portion of the plate; wherein the first cooling circuit is in fluid communication with the fore portion and the second cooling circuit is in fluid communication with the aft portion and the first and second cooling circuits are fluidically isolated from one another. Also described is a method of cooling a seal segment in a gas turbine engine.

An interstage seal is provided for installation between forward and aft stage discs of a turbine section of a gas turbine engine. The seal has a forward annular portion, which extends forward to contribute to an air seal at the outer periphery of the forward stage disc, and an aft annular portion, which extends rearward to contribute to an air seal at the outer periphery of the aft stage disc. The seal has a peripheral slot into which static vane inner rails are loadable. The seal includes a first component, which provides the forward annular portion, and a second component, which provides the aft annular portion. The second component is separably connectable to the first component such that the first and second components, when connected, cooperate to form the peripheral slot. Loading the static vane inner rails into the slot prevents the second component separating from the first component.

Interstage seal

A turbine nozzle guide vanewith passagesleading from a hollow coreto respective seal strip slots, to deliver cooling air to abutment faceson each end of the vane

Nozzle guide vanes

Byte-swapping in a buffer memory system utilizes a byte-swapping register to avoid wasteful unused buffer memory spaces that may result from a data transfer of partial word data, i.e., bytes of data less than the number of bytes in a word, to the buffer memory. When a data transfer request, e.g., a write request, requires a transfer of a partial word, the partial request is written to a word in the buffer memory, and is also stored in the byte-swapping register. In a subsequent data transfer request, the partial word stored in the byte-swapping register is combined and concatenated with sufficient bytes of data of the subsequent data transfer request to produce a complete word. The complete word is written in the word in the buffer memory, replacing the previously stored partial word, and thus fills the previously unused buffer memory space.

Byte-swapping for efficient use of memory

An arrangement includes at least one data storage device, an automation controller, and an enhanced interface. The data storage device is connected to a computer and arranged to perform a plurality of operations in response to one or more commands received from the computer. The automation controller is configured to physically provide the data storage device with at least one data storage media. The enhanced interface operatively couples the data storage device with the automation controller, such that the data storage device can be selectively controlled by the automation controller and the automation controller can be selectively controlled by the data storage device depending on the received commands. The enhanced interface includes a standard serial interface and at least one additional line. The additional line is configured to provide a directing signal from the data storage device to the automation controller. This added capability allows for bidirectional control between the data storage device and the automation controller.

Methods and arrangements for providing bi-directional control between data storage drives and automation controllers

A method and apparatus for storing user data organized into a plurality of data records on tape is provided. User data is first accepted from a host computer. The user data is then organized into data groups independent of the record structure. Records are then assigned to data entities where each data entity has at least one data record. A group index is formed to which information pertaining to the records and/or entities contained within the group is written. Data is then stored on the tape in groups along with each associated group index.

Storing plural data records on tape in an entity with an index entry

A method of appending data to compressed data stored on tape (10) in the form of records (CR.sub.n) wherein compressed data is stored in groups (G.sub.n) independently of the record structure of the data and each group has an associated data structure (4), containing information relating to the group contents in terms of entities (E.sub.n), where an entity can contain more than one record, and means (H) for storing information on the number of records in each entity (E.sub.n) characterised by locating the entity containing the last record to be retained and changing said stored information to indicate the number of wanted records in that entity and writing the data being appended to a subsequent new entity.

Growing community of inventors

Bristol, United Kingdom

Mark John Simms