Albert Bell DeceasedDetroit, MI

4862949, Sep 5, 1989

Sep 8, 1987

7/095098

Albert H. Bell - Birmingham MI

General Motors Corporation - Detroit MI

F28D 1900

165 9

A regenerator seal assembly including a flat platform having a wear face slidably engaging a matrix disc and an opposite seal face, a plurality of naturally planar thin and flexible metal strips arrayed in end-to-end overlapping relationship on a bevel surface of the engine adjoining the matrix disc with an outer edge of each strip engaging the platform seal face and forming a gas seal thereat, an elastomeric seal element in a groove in the bevel surface engaging a high pressure side of each metal strip to define a gas seal between the elastomeric element and the metal strips, and a retaining shoe engaging a low pressure side of each metal strip and pressing the latter against the elastomeric element with sufficient force to effect the aforesaid gas seal but with insufficient force to rididly attach the metal strips to the bevel surface. The metal strips slide relative to the bevel surface when the gap between the matrix disc and the engine changes due to thermal distortion of the disc so that stress concentrations in the metal strips are avoided.

4105062, Aug 8, 1978

May 13, 1977

5/796688

Albert H. Bell - Birmingham MI
Richard M. Zeek - Farmington MI

General Motors Corporation - Detroit MI

F28D 1900

165 9

A regenerator seal assembly for use in a rotary regenerator includes a two-stage seal with a peripheral rim seal having a seal leaf turned inside out so that the free end of the leaf is of a smaller radius of curvature than the fixed end of the leaf and wherein the outer peripheral rim seal is made up of a plurality of straight leaf segments formed on chord lines along the outer circumference of the seal assembly with each straight leaf segment being joined by a mitered joint so that the free end of each such leaf segment is deflected without formation of waviness of wrinkles in the seal assembly.

3982390, Sep 28, 1976

Jan 7, 1976

5/647449

Albert H. Bell - Birmingham MI

General Motors Corporation - Detroit MI

F02C 702
F02C 712

60 3916R

A device to produce engine braking on a two-shaft gas turbine engine including an air brake compressor on the power turbine shaft for absorbing energy from the power turbine shaft thereby to control power transfer to a power output shaft. The system includes a variable control assembly to throttle inlet air flow to the air brake compressor so as to regulate the amount of power absorption from the power turbine shaft.

4003199, Jan 18, 1977

Mar 1, 1976

5/662611

Albert H. Bell - Birmingham MI
Hans Egli - Santa Monica CA

General Motors Corporation - Detroit MI

F02C 310
F02C 702

60 3916R

A device to produce vehicle braking from a two-shaft gas turbine engine including an air brake with a centrifugal impeller on the power turbine shaft, the impeller having blades forwardly turned at the impeller exit through an angle greater than sixty degrees for absorbing energy from the power turbine shaft thereby to control power transfer to an output shaft. The system includes a variable inlet control assembly to throttle inlet air flow to the air brake impeller so as to regulate the amount of power absorption from the power turbine shaft.

4825645, May 2, 1989

Sep 8, 1987

7/095006

Albert H. Bell - Birmingham MI

General Motors Corporation - Detroit MI

F02C 310

60 39161

A power turbine and first stage gear reduction assembly for a gas coupled gas turbine engine includes a first stage reduction gear, a tubular pinion shaft carrying a first stage pinion gear, and a power turbine shaft having a power turbine at a turbine end thereof. The first stage pinion gear and the first stage reduction gear are straddle mounted on an engine block of the gas turbine engine for rotation about parallel primary and secondary axes of the engine, respectively, and in meshing engagement. The power turbine shaft is aligned on the primary axis with a power transfer end thereof within and connected to the pinion shaft through a self-holding taper connection so that the power transfer end of the pinion shaft is supported on the engine block for rotation about the primary axis. A third bearing is disposed between the engine block and the power turbine shaft adjacent the power turbine whereby the power transfer end of the power turbine shaft is supported on the engine block for rotation about the primary axis.

4639194, Jan 27, 1987

May 2, 1984

6/606268

Albert H. Bell - Birmingham MI
Jesse F. Johnson - St. Clair Shores MI

General Motors Corporation - Detroit MI

F01D 534

416241B

A hybrid gas turbine rotor having a silicon carbide ceramic turbine wheel portion and a nickel alloy steel shaft portion further includes a hollow silicon carbide ceramic stub shaft integral with the turbine wheel portion having a frustoconical outer surface tapering away from the wheel portion and a tubular end on the shaft portion having an inner frustoconical surface tapering toward the shaft portion at an angle corresponding to the outer surface taper angle. The shaft portion is connected to the wheel portion by shrink fitting the tubular end over the stub shaft so that the shrink fit is the sole medium whereby the wheel portion is supported on the shaft portion and torque is transferred therebetween.

4060337, Nov 29, 1977

Oct 1, 1976

5/728721

Albert H. Bell - Birmingham MI

General Motors Corporation - Detroit MI

F01D 522

416186R

A quick response gasifier spool for an automotive gas turbine engine has a shaft with a turbine wheel connected on one end thereof with a row of turbine blades driven by motive fluid from an engine combustor and further has a low inertia centrifugal compressor impeller with a low mass hub secured to the opposite end of the shaft. The impeller has a plurality of separate, free formed blades each having a root segment integrally formed with the hub; the blades including spaced apart radial tip portions joined by a continuous ring of span splitter elements located on the radial extent of each of the blades to prevent flutter between adjacent free blade radial tips and wherein each element of the continuous ring includes a leading edge and a trailing edge joined by a curved segment located along a flow streamline path between each of the individual blades. The ring and individual free formed blades define an open end back configuration on the centrifugal impeller to reduce fluid shear between the back face of the impeller and its rear closure plate.

5105625, Apr 21, 1992

Nov 23, 1990

7/618338

Albert H. Bell - Birmingham MI
Dan Coffey - Troy MI

General Motors Corporation - Detroit MI

F02C 304

60753

In a gas turbine engine, an annular flange of a ceramic scroll is clamped to an annular shoulder of a gas turbine engine housing by a plurality of nuts on thread rods extending perpendicular to the annular shoulder. A metal sleeve around each rod cooperates therewith in defining a coolant passage which is connected at one end to a source of compressed air and which discharges at the other end into a cooling chamber around the nuts through grooves in a surface of each nut. Air circulating in the coolant passages and through the cooling chamber cools and thermally shields the rods and the nuts.