Bruce Michael Steinetz

US Patent:

6446979, Sep 10, 2002

Filed:

Jun 27, 2000

Appl. No.:

09/613053

Inventors:

Bruce M. Steinetz - Westlake OH

Assignee:

The United States of America as represented by the United States National Aeronautics and Space Administration - Washington DC

International Classification:

F16J 1510

US Classification:

277630, 277641, 277652, 277654, 277537, 277938, 23926511

Abstract:

A thermal barrier for extremely high temperature applications consists of a carbon fiber core and one or more layers of braided carbon fibers surrounding the core. The thermal barrier is preferably a large diameter ring, having a relatively small cross-section. The thermal barrier is particularly suited for use as part of a joint structure in solid rocket motor casings to protect low temperature elements such as the primary and secondary elastomeric O-ring seals therein from high temperature gases of the rocket motor. The thermal barrier exhibits adequate porosity to allow pressure to reach the radially outward disposed O-ring seals allowing them to seat and perform the primary sealing function. The thermal barrier is disposed in a cavity or groove in the casing joint, between the hot propulsion gases interior of the rocket motor and primary and secondary O-ring seals. The characteristics of the thermal barrier may be enhanced in different applications by the inclusion of certain compounds in the casing joint, by the inclusion of RTV sealant or similar materials at the site of the thermal barrier, and/or by the incorporation of a metal core or plurality of metal braids within the carbon braid in the thermal barrier structure.

US Patent:

6702300, Mar 9, 2004

Filed:

Jan 11, 2002

Appl. No.:

10/046119

Inventors:

Bruce M. Steinetz - Westlake OH

Assignee:

The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

International Classification:

F16J 1502

US Classification:

277642, 277632, 277644, 277646, 277650, 277930, 60770, 23926511, 23926543, 244131

Abstract:

A high temperature sealing system is operative to seal an interface between adjacent hot structures and to minimize parasitic flow between such structures that move relative to one another in-plane or out-of-plane. The sealing system may be used to seal thrust-directing ramp structures of a reusable launch vehicle and includes a channel and a plurality of movable segmented sealing elements. Adjacent ramp structures include edge walls which extend within the channel. The sealing elements are positioned along the sides of the channel and are biased to engage with the inner surfaces of the ramp structures. The segmented sealing elements are movable to correspond to the contour of the thrust-directing ramp structures. The sealing system is operative to prevent high temperature thrust gases that flow along the ramp structures from infiltrating into the interior of the vehicle.

US Patent:

6811154, Nov 2, 2004

Filed:

Feb 8, 2003

Appl. No.:

10/361168

Inventors:

Margaret P. Proctor - Berea OH
Bruce M. Steinetz - Westlake OH

Assignee:

The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

International Classification:

F16J 1544

US Classification:

277355, 277409, 277416

Abstract:

An annular finger seal is adapted to be interposed between a high pressure upstream region and a lower pressure downstream region to provide noncontact sealing along a rotatable member. The finger seal comprises axially juxtaposed downstream and upstream finger elements, each having integrally spaced fingers. The downstream fingers each have a lift pad, whereas the upstream fingers lack a pad. Each pad extends in a downstream direction. Each upstream finger is spaced from the rotating member a greater distance than each pad. Upon sufficient rotational speed of the rotating member, each pad is operative to lift and ride on a thin film of fluid intermediate the rotating member and the pad.

US Patent:

7086648, Aug 8, 2006

Filed:

Aug 22, 2003

Appl. No.:

10/652088

Inventors:

Bruce M. Steinetz - Westlake OH, US

Assignee:

The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

International Classification:

F16J 15/44

US Classification:

277409, 277411, 277412, 277423, 277431

Abstract:

The invention relates to a sealing device having an acoustic resonator. The acoustic resonator is adapted to create acoustic waveforms to generate a sealing pressure barrier blocking fluid flow from a high pressure area to a lower pressure area. The sealing device permits noncontacting sealing operation. The sealing device may include a resonant-macrosonic-synthesis (RMS) resonator.

US Patent:

7497443, Mar 3, 2009

Filed:

May 3, 2005

Appl. No.:

11/121850

Inventors:

Bruce M. Steinetz - Westlake OH, US

Assignee:

The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

International Classification:

F16J 15/02

US Classification:

277644, 277647, 277652

Abstract:

A resilient, flexible, pressure-activated, high-temperature seal is adapted to be interposed between high and low pressure regions to provide sealing between opposing surfaces of adjacent relatively movable structures. The seal comprises at least one C-shaped sheet element. The C-shaped element design enables the seal to be pressure-activated to provide a radially outward biasing force, responsive to a seal-activating pressure differential acting across the seal thereby increasing resiliency. A centrally-located, resilient core structure provides load bearing and insulating properties. In an exemplary embodiment where at least two seal elements are used, each layer has a cutout slot pattern and the remaining strip material pattern. The slots provide flexibility to the seal, enabling the seal to be manually contoured to seal around corners and curves. The strip material of each layer covers the slots in each adjacent layer to minimize leakage through the slots.

US Patent:

49173022, Apr 17, 1990

Filed:

Dec 30, 1988

Appl. No.:

7/292146

Inventors:

Bruce M. Steinetz - Broadview Heights OH
Paul J. Sirocky - Middleburg Heights OH

Assignee:

The United States of America as represented by the United States
National Aeronautics and Space Administration - Washington DC

International Classification:

B64D 3304
F16J 1546

US Classification:

23926511

Abstract:

This device is concerned with sealing the sliding interfaces between structural panels that are roughly perpendicular to each other or whose edges are butted against one another. The gap which the seal element must seal is not uniform along the seal length requiring significant seal flexibility. The seal 10 is mounted in a rectangular groove 14 in a moveable structural panel 16. The seal comprises a plurality of rectangular shaped wafers 12 stacked next to one another and preloaded in the axial direction to minimize leakage between wafers. The wafers are laterally preloaded to maintain sealing contact along the wafer faces which engage the adjacent wall of a sidewall 18 using one of several approaches, such as the pressurized linear bellows 22. The seal accomodates distortions in the adjacent panel by relative sliding between adjacent wafers. Leakage between wafers is further minimized with good wafer surface finishes.

US Patent:

60393254, Mar 21, 2000

Filed:

Apr 9, 1998

Appl. No.:

9/057898

Inventors:

Bruce M. Steinetz - Westlake OH
Lawrence A. Kren - Fairview Park OH

Assignee:

The United States of America as represented by the Administrator of
National Aeronautics and Space Administration - Washington DC

International Classification:

F16J 1502

US Classification:

277633

Abstract:

A resilient braided rope seal for use in high temperature applications includes a center core of fibers, a resilient canted spring member supporting the core and at least one layer of braided sheath fibers tightly packed together overlying the spring member. The seal provides both improved load bearing and resiliency. Permanent set and hysteresis are greatly reduced.

US Patent:

50765906, Dec 31, 1991

Filed:

Nov 26, 1990

Appl. No.:

7/617752

Inventors:

Bruce M. Steinetz - Broadview Heights OH
Paul J. Sirocky - Middleburg Heights OH

Assignee:

The United States of America, as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

International Classification:

F16J 1532

US Classification:

277 53

Abstract:

A high temperature, flexible brush seal comprises a bundle of fibers or bristles held tightly together and secured at one end with a backing plate. The assembly includes a secondary spring-clip having one end anchored to the brush seal backing plate. An alternate embodiment of the seal utilizes a metal bellows containing coolant holes. Another embodiment of the seal uses non-circular cross-sectional fibers which may be square, rectangular or hexagonal in cross section.